NASA Missions

Overview

The objective of the Nano-Satellite Launch Challenge is to bring forth innovations in propulsion and other technologies, as well as operations and management relevant to safe, low-cost, small payload delivery systems for frequent access to Earth orbit.

Deliver a payload with a mass of at least 1 kilogram and dimensions of at least 10x10x11 centimeters to Earth orbit, complete at least one orbit past the launch site and deliver payloads successfully at least two times in one week.

The specified payload matches the standard 1U CubeSat. One orbit past the launch site imposes an absolute minimum orbital velocity requirement and an injection maneuver to achieve orbit. Repeatability within a time constraint deters one-time stunts that would not lead to a useful launch capability. This is anticipated to be a first-to-demonstrate challenge.

Allied Organizations will have to verify that payloads have been placed in orbit via ground tracking or other means, which might be done through partnerships with NASA, the U.S. Air Force, private entities or through sponsorships. Range safety costs and procedures will be a critical issue for competitors, but some existing and new ranges may offer incentives to attract competitors. The Federal Aviation Administration will have an important role in permitting and/or licensing of competitors.

Benefits

The Challenge objective was to bring forth innovations in propulsion as well as operations and management relevant to safe, low-cost, small payload delivery systems for frequent access to Earth orbit.

Overview

The need and demand for long term space missions, such as missions to Near Earth Object’s (NEO’s) and interplanetary missions, is growing rapidly. To satisfy this demand, on-orbit propellant storage and transfer technologies are being developed. The ability to re-fuel a space system, once on-orbit, will provide a means of success for these types of space missions without the need for continual development and advancement of heavy lift vehicles. Additionally, the adaptation of existing technology will allow on-orbit refueling of spacecraft to become a near term reality, cutting the need for advanced heavy launch vehicle development as well as the corresponding cost, time, and manpower.

This effort was awarded an SBIR Phase I in 2019: Spacecraft On-orbit Advanced Refueling and Storage.

Problem Statement 
Currently, the United Launch Alliance (ULA) is developing on-orbit propellant storage and transfer systems that are derived from the Centaur upper stage of the Atlas launch vehicle. Once on-orbit, these systems will be spin stabilized about their major axis while several propellant transfers take place. During these propellant transfers flowing liquid propellant, pressure gradients, and liquid slosh caused by the oscillatory motion of the space system are anticipated to pose a drastic change on the system’s rotational dynamics. To further advance propellant storage and transfer technologies, the dynamics of on-orbit propellant transfers need to be understood.

Technology Maturation 
A successful completion of the proposed microgravity testing will advance the current knowledge of these space systems and raise the Technology Readiness Level (TRL) of cryogenic propellant transfer systems from 4 to TRL 6.


Overview of Flight Test
The Eigen Systems’ SOARS payload flew aboard Blue Origin NS-35, successfully demonstrating autonomous multiphase fluid management and advancing the Gravitational Flow Reactor (GFR) to TRL-7. Building on NASA’s Flight Opportunities maturation pathway, GFR is now positioned for follow-on demonstrations that could align with STMD priorities in Cryogenic Fluid Management and the Lunar Surface Innovation Initiative, while potential applications in biomanufacturing and in-space production applications (InSPA) and future Commercial LEO Destinations (CLD). In the longer term, GFR may also support ESDMD exploration architectures for Artemis, with broad translation opportunities across in-space refueling, ISRU, biomanufacturing, and life support systems.
 

Benefits

Overview

Benefits

Overview

Benefits

Overview

Single-wheel testbeds have been used to evaluate the tractive performance of locomotion and other rover mobility elements in soils simulating lunar regolith. Understanding Wheel-Regolith Interaction for Mobility under Lunar Gravity will develop a small-scale mobility testbed to assess the mobility performance of locomotion elements during parabolic flight tests that simulate lunar gravity. The project will test specific modes of characterization including physical slopes and drawbar pull force measurements. Data collected from these in-flight experiments is expected to characterize the effects of reduced gravity on the dynamic interaction of wheels and lunar soil simulants and improve current predictions on how scaled versions of such locomotion elements will behave on the Moon.

Problem Statement
The current practice for rover wheel testing is to directly scale the applied downforce to match the target environment (e.g., one-sixth of Earth’s gravity for lunar missions). This scaling does not account for the dynamic effects of a partial gravity field within the granular media. Prior research indicates that wheel testing that does not account for a partial gravity field within the granular media may overestimate mobility performance, which impacts how lunar rovers are currently designed and tested. Parabolic flight test results could help verify the proper scaling of wheel-terrain interaction and extrapolate from terrestrial mobility tests to expected lunar mobility performance.

Technology Maturation
Zero Gravity Corporation’s parabolic flight tests simulating lunar gravity will allow for the collection of data while the scaled testbed is performing an emulated 0 degree, up-slope, or down-slope segment. Some parabolas will contribute to study of constant slip traction assessments as well. The effect of partial gravity fields on single-wheel testing is expected to directly inform if current traction assessments and endurance ground testing methods are too conservative. Greater confidence should reduce the margins required for mobility subsystem design and improve how mission operations are conducted in environments with unfamiliar, sloped terrain. These improvements are expected to advance the technology readiness level (TRL) of this ground single-wheel facility to TRL 8.

Benefits

- Improved mobility tools: More accurate testbed for characterizing wheel/regolith interactions 

- Enhanced characterization: Greater understanding of rover capabilities to traverse varied and unknown terrain 

Future Customers 

- Future lunar rovers on NASA and commercial missions

Overview

NASA and commercial missions to the lunar surface will require low-mass, cost-effective, high-reliability sensors. Navigating and landing on the lunar surface is one of the most challenging aspects of lunar exploration. The surface of the Moon has continuously changing lighting conditions – posing unique challenges to the current state-of-the-art optical navigation systems that depend on features being illuminated by sunlight. The Maturation of Robust Landing Lidar System is a dual-mode lidar (light detection and ranging) landing sensor system that uses active Doppler and ranging techniques in conjunction with state estimation algorithms and a lunar terrain database to supply precision knowledge of range, velocity, and terrain-relative position, regardless of lighting conditions. Researchers will integrate multiple functions into a single sensor to reduce size, weight, and power as well as improve performance, robustness, and reliability of the hardware for reusable lunar, planetary, and asteroid landers.

Problem Statement
Continuously changing lighting conditions pose a challenge to conventional optical navigation techniques that depend on observing features illuminated by sunlight. Current precision-landing capabilities use medium-range sensors such as Navigation Doppler Lidar (NDL) and Optical Moon Proximity Sensor (OMPS) for range and velocity measurements up to approximately 3 miles, enabling soft landings. However, terrain relative navigation, usually operated at altitudes higher than 9 miles, require a longer-range lidar sensor. A successful lunar mission will rely on the information from a relative terrain navigation to avoid hazards while also producing a soft landing. Future lunar missions will require new low-mass, low-cost, and high-reliability precision landing and hazard-avoidance technologies that enable successful lunar landings, regardless of location and lighting conditions.

Technology Maturation
A flight test on Blue Origin’s New Shepard reusable suborbital rocket aims to expose the lidar-based landing sensor system to the intended range of operational altitudes and velocities for lunar operations. The sensor systems are designed to perform navigation from altitudes over 9 miles and vehicle velocities over approximately half a mile per second (1000 m/s). The flight test of the sensor system is designed to maximize test coverage over its entire range of performance (i.e. the range and range rates experienced on a typical lunar landing trajectory). By doing so, the flight test will demonstrate the ability to perform real-time navigation under realistic operational conditions.

Benefits

- Efficient: Provides low-mass, low-cost, and high-reliability precision landing and hazard avoidance technology
- Safer: Provides precision knowledge of range, velocity, and terrain-relative position regardless of location and lighting conditions

Future Customers
- Future NASA and commercial lunar missions, such as those through NASA’s Artemis program and Commercial Lunar Payload Services
- NASA and commercial missions requiring landing on other solar system bodies such as Mars and Europa

Overview

Benefits

Overview

Benefits

Overview

The Easy-to-Use Payload Interoperable Integration Carrier (EPIIC) technology designed by Aegis Aerospace is a modular experiment and payload adapter to enable simple, rapid, and interchangeable integration onto host vehicles. EPIIC combines mounting; power; and command, data, and handling in a mass-optimized package. This flight test aims to validate EPIIC’s ability to provide structural support, power, and communications and data handling for the selected payload. The technology was designed to meet a need for an optimized plug-and-play interface that easily integrates laboratory payloads, including scientific instruments and experiments, onto suborbital vehicles, orbital platforms, and planetary landers. The design optimizes mass and volume to lower costs for payload developers. 

Problem Statement 
One of the many complex aspects of spaceflight is the interface design for payloads that fly aboard host vehicles. Currently, there is no easy way to transfer payloads between flight vehicles. It is often ideal to get payloads to flight test as quickly as possible, but the process to ensure that a payload can interface appropriately with the flight vehicle can be complex and time-consuming because there are significant differences in the existing interfaces between payloads and parabolic flight vehicles, sounding rockets, and lunar landers. 

Technology Maturation 
This flight test is expected to validate EPIIC’s ability to provide structural support, power, and communications and data handling for selected payloads. Aegis Aerospace will use flight data to further optimize the EPIIC technology. The company anticipates having the flight-qualified system ready for purchase and use by late 2025.

Benefits

- Simple: Uses only eight components to integrate payloads to flight vehicles - Interchangeable: Plug-and-play interface for suborbital vehicles, orbital platforms, or lunar landers - Optimized: Combines mounting, power, and communications in a minimized package 

Future Customers 
- Potential use in NASA missions for integration of laboratory payloads, including scientific instruments and experiments, onto suborbital vehicles, orbital platforms, and planetary landers 
- Available for commercial flight provider payload integrations

Overview

The Apparatus for Nominal Integration with Minimal Adaptations (ANIMA) is a three-part solution designed by Ecoatoms to address NASA’s need to easily integrate varying space payloads onto different flight vehicles. ANIMA comprises an interchangeable plug on the side of the vehicle, a universal connector, and an on-board computer to integrate the different types of payloads to disparate host vehicles. Designed for a variety of customers, ANIMA is a turnkey solution that aims to bridge the hardware integration gap to make space accessible to commercial, government, and academic users of all backgrounds. These flight tests will be key to validating the Ecoatoms technology in a relevant environment to take the system’s technology readiness level (TRL) to TRL 8.

Problem Statement 
Over the last decade, there has been a dramatic increase in rocket launches but limited and slow access to space for users who are focused on research and development. This is due in part to the lack of a universal solution for integrating diverse payloads onto different flight vehicles. This lack of simple integration is slowing access to space and increasing costs. Through its highly adaptable platform, Ecoatoms’ ANIMA aims to increase the speed and ability to get payloads to flight tests while decreasing costs. The technology is designed to eliminate the need for intermediaries or third-party services and enable the user to directly adapt their technology to their desired flight, reducing total costs. 

Technology Maturation
Flight tests aim to validate ANIMA in a space environment and advance the system to TRL 8. Post-flight outcomes are expected to allow Ecoatoms to optimize ANIMA and reach TRL 9. In this way, ANIMA can become a reliable flight-qualified system for future effective mission operations. A successful mission could provide knowledge that would enable ANIMA to become an important technology between the payload and vehicle, enabling fast and cost-effective access to space for users.

Benefits

- Universal access: Enables users from all backgrounds to engage in space-based R&D - Streamlined process: Eliminates the need for intermediaries or additional services - Cost reduction: Directly adapts technology to flight vehicle, lowering overall flight expenses

Future Customers 
- Academia, industry, and government entities seeking rapid space access 
- Users needing minimal adaptations for payloads on commercial vehicles/stations

Overview

Benefits

Overview

The Sintering End Effector for Regolith (SEER) is a robust and durable robotic end effector designed to enable additive construction on the Moon using concentrated solar energy to melt and fuse lunar regolith into horizontal and vertical structures without the need for additives or binders from Earth. SEER accepts sunlight from a primary solar concentrator and increases solar concentration by between 4x and 11x. The system enables selective solar sintering and selective solar melting of multi-layer structures made exclusively from a lunar regolith feedstock without the need for binders or additives. The highly scalable and versatile technology aims to support NASA’s Artemis program through the utilization of lunar resources to establish permanent infrastructure on the Moon. Structures that can potentially be produced by SEER include landing pads, habitats, and dust-free zones on the lunar surface. 

Problem Statement 

A decades-long problem, rapid overheating and optics failure has prevented the use of secondary solar concentrators in high-temperature space applications. Secondary solar concentrators could be used only for seconds to minutes at a time prior to failure. SEER, however, can operate continuously without the optic overheating. By eliminating the need for additional binders or additives, SEER incorporates a particle feed subsystem to continuously deposit lunar regolith to the end effector for heating and melting to construct lunar structures. This particle feed subsystem prevents clogging, enabling the continuous flow of regolith in lunar gravity and provides direct control over the mass flowrate of regolith feedstock through the system. 

SEER aims to help NASA establish permanent infrastructure on the Moon in support of its Artemis program by minimizing launch mass and the related costs for constructing landing pads, roadways, habitats, and other lunar surface assets.

Technology Maturation 

The continuous, metered flow of poorly graded regolith through the SEER system is highly dependent upon gravity with very little experimental, numerical, or analytical work to help inform design decisions and gauge reliability. Reduced gravity experiments are required to address these technical challenges and to establish appropriate scaling relationships of the system for its ultimate deployment on the Moon. These design, validation, and demonstration experiments will be conducted during these parabolic flight tests under 1/6 g (i.e., lunar gravity) conditions. The experiments are expected to provide critical data on the flowability of regolith in a granular feed system designed for a wide range of lunar operations, which additionally include material sampling applications, additive manufacturing applications utilizing lunar regolith as the feedstock material, and large-scale systems for extracting oxygen from regolith on the Moon. 

The SEER regolith feed subsystem is currently at TRL 5. In order to progress the regolith feed subsystem to TRL 6, parabolic flight testing will be performed to provide the relevant operational environment. This flight testing aims to enable the deployment of the SEER system on the Moon. 

Summary of 5/18/2025 Flight Test
Outward Technologies successfully demonstrated its Sintering End Effector for Regolith (SEER) through controlled experiments under lunar gravity and vacuum conditions during parabolic flights provided by Zero-Gravity Corporation, with funding through NASA Flight Opportunities and the NASA SBIR Phase II-E program. The SEER technology enables the controlled deposition and melting of lunar regolith as the exclusive building material for constructing lunar landing pads, roadways, building foundations, and habitats. Parabolic flight testing was conducted for technology maturation of these systems and methods to enable their ultimate deployment on the Moon for controlled melting of lunar soil with concentrated sunlight in a layer-wise additive construction process. These experiments conducted under lunar gravity and vacuum conditions successfully advanced the regolith deposition subsystem of SEER to Technology Readiness Level 6 by demonstrating controlled and continuous flow of lunar regolith geotechnical simulants in a representative lunar environment.

Benefits

- Robust and durable: Enables additive construction using the Sun and regolith to build structures on the Moon without overheating and failure 

- Scalable and versatile: Uses lunar resources to establish a variety of permanent infrastructures on the Moon (e.g., landing pads, habitats) 

Future Customers 
- Enable ISRU to build necessary structures on the Moon 
- Could be further developed to extract oxygen and metals from lunar regolith, powered by concentrated solar energy.

Overview

Reducing resupply on long-duration space missions by using closed-loop life support requires a different approach to mass transfer than buoyancy-based sparging, a common degassing method used on Earth, that is challenging in microgravity. Metastable nanobubbles may provide gravity-independent, sustained mass transfer with higher transfer rates, closing the life support loop. Also, these nanobubbles have biocidal effects, potentially streamlining spaceflight water purification processes. The Characterizing Production and Stability of Nanobubbles in Variable Gravity experiment aims to advance the state-of-the-art and increase confidence in integrating nanobubble technology into life support systems requiring gas-liquid contacting. 

Problem Statement 

Tomato plants, wastewater processing, carbon dioxide scrubbing, and propellent all have something in common – they require multiphase mass transfer (gas into liquid) to effectively function. Typical terrestrial methods for mass transfer include macro- and microbubble sparging (bubbling gases into liquid). These gas-liquid contacting systems are limited to terrestrial use because they are not mass/power/volume-efficient enough for spaceflight. The current standard for reduced/microgravity environments are rate-limited, diffusion-dominated membranes. Due to this mass transfer gap, current life support systems are partially open loop and require frequent resupply missions. This is not sustainable for missions beyond low Earth orbit (LEO). Attaining loop closure for carbon, oxygen, and water is the only way long-duration spaceflight can be Earth-independent, minimize resupply missions, and thrive on other planetary surfaces (i.e., lunar, Martian). 

Technology Maturation 

Currently, experiments have only used nanobubbles terrestrially and have not studied their production or sustainment in reduced gravity or the survivability of launch loads. Parabolic flight tests are expected to help researchers capture the ability for a ground-validated nanobubble generator to produce nanobubbles in brief periods of microgravity. The subsequent >1-g maneuvers to reset from a parabola will be used to study the survivability of these produced or contained bubbles by using a laser-based bubble tracker. Multiple flights will be used to investigate nanobubble characteristics for various spaceflight-pertinent gases, such as carbon dioxide and oxygen (air). The production of nanobubbles in a spaceflight-relevant environment is expected to advance the system’s technology readiness level (TRL) to TRL 5. 

Summary of Flight Testing 
5/4/2025: The experiments from this flight campaign demonstrated that nanobubble generation technology enhances gas delivery under microgravity conditions. This represents a significant advancement for gas-limited systems in space exploration, with potential applications for in-situ resource generation, autonomous food production, and improved fuel efficiency.

10/28/2025: During this campaign, we successfully demonstrated that nanobubbles generated on Earth maintain stability even under extreme gravity changes, including zero gravity. Our experiments further revealed that nanobubbles can be generated in zero gravity conditions, enabling highly efficient gas-liquid contact processes.

This capability could significantly enhance the performance of systems that depend on gas exchange, reducing both the operational footprint and resource requirements for implementation in space-based applications.

These findings open new possibilities for optimizing life-support and fuel systems in space environments.

Benefits

- Improved life support: Replaces membranes and increases efficiency Minimize resupply: - - Closed-loop systems can reduce resupply needs 

Future Customers 
- Potential applications for closed-loop life support systems in space include: 
- Aquaculture/food production 
- Oxygen recovery from carbon dioxide 
- Wastewater processing 
- Enhanced terrestrial water treatment, aquaculture, and horticulture

Overview

The Space Metal Processing System (SMPS) Microgravity Testing Through Parabolic Flight will support testing of two subsystems prior to SMPS/Modular Space Foundry (MSF) demonstration on the International Space Station. The MSF is designed to process metal in any gravity environment into rods, tubes, sheet metal, wire, metal propellant, and other products through casting, continuous casting, droplet printing, and other mechanisms. Designed for higher throughput and broader capabilities than the current Materials Science Laboratory Electromagnetic Levitator (MSL-EML, or EML), it uses electromagnetic induction to heat, melt, and manipulate metal for the purpose of changing its shape and/or its properties. 

Problem Statement 

The SMPS innovation builds on technology of the EML currently running on the space station. The EML has been used for containerless processing of metals, alloys, and semiconductors on the station since April 2015 to study melting and solidification properties in microgravity. The MSF technology advances in-space metal processing for industrial purposes by enabling melting and manipulation of higher quantities of metal than the current EML, as well as providing continuous casting capabilities to make commercial products. 

Technology Maturation 

The latest prototype MSF has previously been tested on parabolic flights. The expected outcome for these additional two flight tests is to validate key subsystems under microgravity conditions to de-risk future on-orbit testing and to deliver preliminary results that will help guide experimental parameters for testing on the space station. 

Summary of May 8, 2025 Flight Test
CisLunar Industries completed its third parabolic flight to advance the TRL of its metal processing and contactless manipulation technologies for In-Space Manufacturing (ISAM) and Dynamic Space Operations. Through this campaign an aluminum billet was cast and the capability for contactless manipulation of metal objects was demonstrated under microgravity conditions. The electromagnetic manipulation experiment, known as Steer, was deployed as a free-flying experiment to isolate it from small aircraft movements and provide a clean microgravity environment. CisLunar Industries continues to pioneer metal processing and manipulation in microgravity with the goal to enable large-scale metal fabrication off-world.

Summary of November 5, 2024 Flight Test
As part of the NASA Flight Opportunities program, and on a second parabolic flight, CisLunar Industries successfully cast their first full aluminum billet under microgravity conditions. Additionally, an upgraded version of the contactless 3D molten metal manipulation system, known as steer, was tested in microgravity for the first time. These tests pave the way for an upcoming mission to the International Space Station, which will operate key components of a space foundry system that is aimed at enabling large scale fabrication in Earth orbit and beyond.

Benefits

- Commercial advancement: Pursues commercial market for reuse of in-space materials 
- Sustainable: Targets space debris removal/reuse 
- Crosscutting: Offers generic capability for various application domains 
- In-space servicing, assembly, and manufacturing 

Future Customers
- Active debris removal 
- In-situ resource utilization vendors

Overview

Exploring the Impact of Surface Properties on Cryogenic Boiling and Quenching at Reduced Gravity through High-Fidelity Measurements aims to advance cryogenic fluid management (CFM) systems crucial for various missions in space exploration, including nuclear and chemical propulsion systems, fuel depots, and ascent and descent stages. It will investigate surface enhancements to improve performance of quenching and boiling processes during long-term cryogenic storage and transfer while developing computational fluid dynamics (CFD) models for accurate simulation. 

Problem Statement 

Cryogenic systems offer superior performance but require a deep understanding of cryogenic liquid-vapor phase change phenomena and accurate modeling for design optimization. Poor CFM design models can increase risk and result in higher margins and safety factors on insulation and stored mass, leading to higher launch mass and costs. CFD tools adopting mesoscale mechanistic sub-models of these phenomena have the potential to alleviate these issues, but while such mesoscale mechanistic sub-models provide flexible and generalized physics-based closures of the disparate boiling processes, their accuracy and robustness are tied to the availability of data for fundamental boiling parameters and macroscopic parameters. Until such data is available, there will be large uncertainty associated with CFD model predictions of cryogenic fluid storage or transfer in microgravity. 

Technology Maturation 

Experiments will be conducted in reduced gravity conditions using a specialized cryogenic apparatus that enables sophisticated diagnostic techniques of backlit shadowgraphy and phase detection measurements. These experiments are designed to allow the quantification of parameters related to boiling and quenching heat transfer, including nucleation site density, bubble growth time, detachment frequency, and more. The collected data will be utilized to improve mesoscale, mechanistic two-phase heat transfer sub-models, which can be integrated into NASA's CFD codes to simulate complex phenomena such as tank pressurization, liquid acquisition devices (LADs), line chilldown, tank chilldown, and tank filling and transfer. 

Summary of Flight Test
We conducted experiments to study the quenching of cryogenic fluids on different surfaces using specialized diagnostics that enable imaging of the boiling process at the microscale in both time and space. The results of these experiments are crucial for understanding the behavior of cryogenic fuels in microgravity conditions and will support the design and development of future in-space cryogenic storage and transfer systems.

Benefits

- Efficient: Enables more efficient cryogenic fluid management and storage 
- Economic: Allows further mass margin savings in cryogenic propulsion systems 

Future Customers
- CFD modeling tools for cryogenic propulsion system design 
- Commercial launch companies (e.g., Blue Origin)

Overview

FLEW.ID is a revolutionary real-time water and nutrient monitoring system that uses laser-induced breakdown spectroscopy (LIBS) technology to analyze liquid samples instantly. It uses laser light to identify the exact chemical makeup of water or nutrient solutions in less than one second.

The system works by directing a focused laser pulse into flowing liquid, creating a tiny plasma spark that breaks down molecules into their basic elements. This plasma emits light in specific colors that act like chemical fingerprints, allowing sensors to identify and measure nutrients, contaminants, and other substances with laboratory-grade precision. Unlike traditional testing methods that require sending samples to labs and waiting days or weeks for results, FLEW.ID provides instant, continuous monitoring without consuming any chemicals or creating waste.

The technology delivers unprecedented accuracy (detecting substances as low as 10 parts per million) while being 100 times faster than current gold-standard laboratory methods and 10 times more cost-effective per sample. Most importantly, it operates completely autonomously, requiring no human intervention or consumable materials — making it ideal for always-on life-support systems.

Problem Statement 
Current water and nutrient monitoring relies on manual sampling and Earth-based laboratory analysis, which creates critical bottlenecks for space missions. When astronauts need to know if their water is safe to drink or if their food-growing systems have the right nutrients, they currently must collect samples, store them, and wait for analysis back on Earth — a process that can take weeks and provides no real-time feedback for critical adjustments.

This approach is not only impractical for long-duration missions to Mars or lunar bases, but it also fails to provide the immediate, continuous monitoring needed for closed-loop life support systems where small problems can quickly escalate. Additionally, existing methods like inductively coupled plasma mass spectrometry are expensive, require trained technicians, consume significant resources, and cannot easily operate in microgravity environments.

FLEW.ID solves these problems by providing:
• Instant Results: Detection and analysis in under one second versus weeks for traditional methods
• Zero Consumables: No chemicals, reagents, or disposable materials needed
• Autonomous Operation: Requires no human intervention or specialized training
• Continuous Monitoring: Provides 24/7 real-time data for immediate decision-making
• Cost Effectiveness: Reduces per-sample costs by 90% while eliminating transportation and storage expenses 

Technology Maturation 
Flight Opportunities' parabolic flight tests will be crucial for advancing FLEW.ID from TRL 4 to TRL 6, representing the critical transition from laboratory prototype to space-ready system. These microgravity tests will validate three essential aspects of the technology:

Fluid Dynamics Validation: In microgravity, liquids behave differently than on Earth, potentially forming bubbles or behaving unpredictably. These flight tests will ensure the laser can accurately target flowing liquids and maintain precise measurements regardless of gravitational conditions.

Bubble Formation Analysis: Air bubbles in the liquid could interfere with laser accuracy. The flights will test bubble mitigation strategies and confirm that the system maintains precision even when bubbles are present.

LIBS Accuracy Verification: The plasma formation process at the heart of this technology needs validation in space conditions to ensure the same chemical detection accuracy achieved on Earth.

Expected Post-Flight Outcomes:
• Comprehensive performance dataset proving space readiness
• Optimized system parameters for microgravity operation
• Validated integration protocols for International Space Station and future lunar habitats
• Technology demonstration package ready for orbital missions
• Commercial readiness for terrestrial applications, accelerating market entry

Benefits

Overview

This STTR-II-E effort concerns technologies related to cryogenic propellant production, storage, transfer, and usage to support NASA’s in-situ resource utilization (ISRU) goals. They include a broad range of applications, scales, and environments consistent with future NASA missions to Mars and beyond. 

More specifically, the project addresses a well-known gap of cryogenic pool boiling measurements in reduced gravity environments for relevant surfaces and materials, which would ultimately be used to develop a correlation for boiling heat flux versus wall superheat in reduced gravity. The new reduced gravity data will also be available to NASA engineers to anchor their future models. 

The primary reason for launching the STTR study is that cryogens constitute a unique family of low-boiling-point fluids whose thermophysical property trends are distinctly different from those of common fluids such as water, dielectric coolants, and refrigerants, for which the vast majority of data is available in the open literature.

The STTR-II study has been successful at acquiring and amassing cryogenic pool boiling data available in the literature and showed that there is a clear lack of data available in reduced gravity conditions. Additionally, the available data is not relevant for solid surfaces representative of cryogenic tank materials. The data obtained from this study will aid in understanding the effects of reduced gravity on cryogenic pool boiling that will facilitate the creation of a reduced-gravity cryogenic-data anchored correlation for heat flux versus wall superheat, and for possible anchoring of future tools to reduced gravity data.

Problem Statement 
This project aims to address one of NASA Space Technology Mission Directorate’s top priority shortfalls concerning cryogenic propellant storage and transfer in reduced gravity environments. The project is directly related to Topic 1 of the original solicitation: “Supporting Sustainable Lunar Exploration and the Expansion of Economic Activity into Cislunar Space,” second bullet: “Long-term storage and transfer of fuels and processed materials, typically in a cryogenic state, on the lunar surface and in orbit.” This STTR-II-E work constitutes a major improvement from the STTR-II study: Providing the first methodology to predict the effects of reduced gravity (microgravity, Lunar, Martian) on pool boiling heat transfer, which is of paramount importance across multiple NASA systems and applications.

Goals & Objectives 
1. Develop a test matrix for the parabolic flight experiments to ensure adequate coverage of the effects of reduced gravity on pool boiling heat transfer.

2. Devise functional parameters that would enable modifying the correlations developed during the STTR-II project to account for reduced gravity effects.

3. Update the consolidated cryogenic pool boiling database developed during the STTR-II project with the new reduced gravity data. 

4. Retrofit the cryogenic pool boiling correlations developed during the STTR-II project to account for the effects of reduced gravity captured during the flight experiments.

5. Summarize the series of user-friendly correlations for the different regions and transition points of the pool boiling curve. 

6. Combine the correlations to develop a method for generating a complete, continuous pool boiling curve for different cryogenic fluids.

Technology Maturation 

The flight test will enable updating the consolidated cryogenic pool boiling database developed during the STTR-II project with the new reduced gravity data. 

The final correlations would ultimately be used for design and analysis of future space systems as stand-alone correlations, or could be inserted into NASA’s lumped node codes, such as Thermal Desktop or the Generalized Fluid System Simulation Program (GFSSP).
 

Benefits

Overview

The Modular Configurable Electric Power Converter (MCEPC) is a next-generation power processing unit (PPU) designed to deliver high-efficiency, scalable electric power conversion for spacecraft systems. It achieves >95% efficiency — compared to 90–94% for typical commercial converters — and delivers a significant improvement in size, weight, and power (SWaP).” Each modular unit supports 1 kW+ operation, making it ideal for applications such as in-space servicing, assembly, and manufacturing (ISAM), high-power electric propulsion, and advanced logistics missions in low Earth orbit (LEO), geostationary Earth orbit (GEO), and cislunar space.

The system also furthers development of the Adaptive Modular Power Software Interface (AMPSI), a technology that enables interoperability between spacecraft systems and provides automatic resource management (ARM). This allows spacecraft to dynamically allocate, share, and optimize power resources across connected systems during flight.

Problem Statement 
Electric power conversion is required for nearly every spacecraft function, from propulsion to manufacturing. However, most current systems above 1 kW are bespoke, heavy, and costly. These inefficiencies ripple through spacecraft design, forcing larger batteries, solar arrays, and thermal systems, which consume valuable payload mass.
MCEPC directly addresses these issues by:
• Reducing SWaP overhead through ultra-efficient design.
• Providing a modular, interoperable solution that can be reconfigured or updated in-orbit.
• Enabling scalable, standardized high-power conversion rather than custom, one-off systems.

Flight test objectives include:
1. Verify operation of the control board and housekeeping power in a very low Earth orbit (VLEO) environment.” 2. Demonstrate AMPSI capability to exchange data and update PPU operating conditions in flight 3. Obtain flight heritage on PPU hardware (housing, connectors, potting, thermal, coatings) 

Technology Maturation 
This orbital flight will validate MCEPC performance in the challenging VLEO environment, where thermal and radiation effects are significant. It will also demonstrate the ability to perform real-time program updates to the PPU via AMPSI, a capability that enables adaptive mission operations and future servicing scenarios.
Post-flight, CisLunar Industries expects to:
• Advance the TRLfrom 4 to 6, establishing flight heritage.
• Deliver a qualified power subsystem for a Department of Defense project (i.e., the Interoperable Modular Power Unit for Lightweight Scalable Electric (IMPULSE) Propulsion SBIR project with the U.S. Space Force) as well as future NASA, and commercial applications.
• Provide critical data to refine next-generation designs for even higher power levels and extended mission lifetimes.
 

Benefits

Overview

Clothing accounts for approximately one quarter of the non-food supplies delivered to the International Space Station (ISS), representing a significant burden for long-duration missions. Because there are no laundry systems in space, astronauts must frequently receive fresh clothing, which becomes increasingly impractical for deep-space exploration. This proof-of-concept prototype washer-dryer system can wash and dry clothing in a single cycle, eliminating the need for astronauts to wear soiled garments for extended periods.

The technology directly addresses NASA’s critical gap for a compact laundry solution that can operate on the Moon (1/6 g) and Mars (1/3 g), with performance requirements of less than seven hours per 4.5 kg load (cotton, polyester, wool), machine mass below 50 kg, external volume under 0.3 m³, and power consumption below 300 W. Beyond enhancing crew comfort and hygiene, this integrated solution supports multiple NASA life support and habitation systems needs, including:

1518 Logistics Tracking, Clothing, and Trash Management for Habitation 1568 Water and Dormancy Management for Habitation 1613 Surface-based Fluid Management for Sustained Lunar Evolution 1517 Metabolic Waste Management for Habitation

Problem Statement 
Currently, the absence of laundry systems in space requires large allocations of up-mass for clothing resupply. This problem intensifies as missions extend farther from Earth, where resupply becomes less feasible. Existing terrestrial washing and drying methods cannot be adapted directly to space due to size, mass, and power limitations, as well as fluid management challenges in microgravity and partial gravity.

This technology solves this problem by providing a compact, energy-efficient, and gravity-agnostic washer–dryer combination unit. Compared to traditional supply-based approaches, it reduces logistics costs, enhances crew health and comfort, and enables sustainable long-duration missions.

Technology Maturation 
This work aims to increase the TRL of the washer-dryer system designed in Phase II and prepare it for spaceflight applications. Flight Opportunities testing will provide critical validation under relevant gravity conditions (zero g, lunar g, Martian g), enabling system design, controls, and fluid management strategies refinement.

Post-flight, expected outcomes that will significantly advance the system’s maturity include:

• Demonstrated functional performance in microgravity and partial gravity conditions.
• Verified semi-autonomous operation capability.
• Data to inform long-term reliability and life cycle models.
• Pathways for both space deployment and dual-use terrestrial applications.
 

Benefits

Overview

This project investigates microgravity-enhanced annealing of Molybdenum Disulfide (MoS2) semiconductors to overcome current manufacturing limitations. Despite advances in metal-organic chemical vapor deposition (MOCVD) growth techniques, MoS2 films suffer from small grain sizes (20-50 μm), high grain boundary density, excessive adlayer formation, sulfur vacancies, and incomplete substrate coverage. These defects severely limit their use in radiation-hardened electronics for space applications.

This approach employs a specialized four-chamber vacuum furnace system operating at 700 °C and 50% grain size increase, >30% reduction in adlayers, and enhanced uniformity across four-inch wafers.

The parabolic flight campaign provides approximately 30 maneuvers per flight with approximately 20 seconds of microgravity each, accumulating sufficient annealing time while maintaining precise thermal control. This system processes four samples simultaneously with synchronized data collection (temperature, pressure, acceleration, optical imaging), yielding results from eight total samples across two flights. The repeated gravity transitions (0 g to 1.8 g) enable direct comparison of crystallization behavior under different gravitational conditions within the same thermal cycle.

Expected outcomes include: 1. Quantitative material characterization (Raman spectroscopy, atomic force microscopy, transmission electron microscopy) validating microgravity benefits 2. Optimized process parameters linking gravity levels to material quality 3. Advancement from TRL 3 to TRL 5, positioning for demonstration aboard the International Space Station 4. Peer-reviewed publications on microgravity effects on 2D materials 5. Data supporting follow-on proposals to ISS National Laboratory and for commercial space manufacturing 6. Industry engagement for potential technology transfer

This investigation represents the first systematic study of 2D semiconductor annealing in microgravity, potentially revealing new pathways to achieve the material quality required for next-generation electronics while establishing foundational processes for space-based semiconductor manufacturing aligned with NASA's In-Space Production Applications (InSPA) objectives.
 

Benefits

NASA Missions: Improved radiation-hardened MoS2 semiconductors would enhance reliability of electronics for future deep space missions where conventional semiconductors degrade from cosmic radiation exposure. Applications include long-duration lunar surface operations, Mars sample return missions, and outer planet exploration requiring decades of operation. The technology directly supports InSPA objectives by validating semiconductor manufacturing processes for future orbital facilities.

Other Government Agencies: Department of Defense satellites require radiation-tolerant electronics for nuclear event survivability and extended operation in Van Allen radiation belts. The National Oceanic and Atmospheric Administration needs robust semiconductors for weather satellites operating in harsh radiation environments.

Commercial Space Industry: Satellite constellation operators could extend satellite lifetimes with superior radiation-hardened components. Emerging space manufacturing companies gain validated processes for semiconductor production in orbital facilities. Terrestrial semiconductor manufacturers benefit from new insights into defect reduction mechanisms applicable to ground-based fabrication.

National Impact: Advances United States semiconductor manufacturing capabilities per Creating Helpful Incentives to Produce Semiconductors (CHIPS) Act priorities. Establishes technological foundation for space-based semiconductor production, reducing dependence on foreign suppliers for critical space components. Demonstrates feasibility of high-value manufacturing in microgravity, positioning American companies to lead the emerging space economy.

This dual-use technology simultaneously advances space electronics reliability and terrestrial semiconductor manufacturing quality.
 

Overview

The RadPC computer technology provides reliability and performance for small spacecraft that have power and cost constraints. The base version of RadPC implements a RISC-V processing architecture on a commercial-off-the-shelf (COTS) field programmable gate array (FPGA). Using a COTS FPGA provides an inherent level of total ionizing dose (TID) immunity due to the small feature sizes of modern transistors. Single event effects (SEEs), which are the dominant fault mechanism in modern devices, are handled using a set of patented fault-recovery procedures that include redundancy and output voting, redundant CPU register arbitration, memory scrubbing, configuration memory error correction codes, and partial hardware reconfiguration of the FPGA. Implementing the RadPC computer on a COTS FPGA provides increased reliability at a cost-point that is feasible for small spacecraft. 

In order to take advantage of the signal processing capability of an FPGA, the unused hardware resources on the device are bundled into a “coprocessor” block that is coupled with RadPC on the same device. The co-processor can perform rapid signal processing algorithms by taking advantage of massive parallelism and optimized hardware circuitry. When coupled with RadPC, the signal processing coprocessor can be controlled using standard software and RadPC can monitor the coprocessor for faults and initiate recovery procedures in the event of an error. The combined approach of the fault-tolerant RadPC computer on the same FPGA as a fully integrated coprocessor can provide increased on-orbit computation while simultaneously achieving reliability beyond the state of the art in small spacecraft computers.

Problem Statement 
Small spacecraft are, by design, resource and cost constrained. Current small spacecraft computers typically don’t contain fault tolerance because these missions can’t afford the expensive “radiation hardened” processors used in larger missions and don’t have the power availability to implement common fault recovery procedures such as redundancy. This leaves small spacecraft in the situation that they are not tasked with critical applications such as autonomy or with algorithms such as artificial intelligence or machine learning. The RadPC+Coprocessor technology aims to deliver the needed reliability for small spacecraft to take on critical mission tasks while simultaneously achieving a price that is cost feasible for these types of missions. 

Technology Maturation 
The base RadPC computer has been matured through more than a decade of university funding at Montana State University, where it achieved TRL-8 through a lunar demonstration in 2025. The RadPC+Coprocessor technology has been matured to TRL-6 through SBIR funding at Resilient Computing. The hosted orbital flight provided by NASA Flight Opportunities will mature the RadPC+Coprocessor technology to TRL 8 through an in-space demonstration of the technology in its final commercial form processing real image data.

Benefits

Overview

Rego-LIFT is a compact, modular vertical conveyor that gently lifts and transports lunar regolith using a rotating drum and static central screw. By controlling drum speed and scoop geometry, it delivers adjustable throughput while minimizing dust generation and mechanical wear. Rego-LIFT directly addresses critical gaps in in-situ resource utilization (ISRU) for Artemis missions. Conducting a flight test with Rego-LIFT should de-risk and allow scaled operations, supporting NASA’s goals of establishing a long-term lunar presence.

Problem Statement 
Rego-LIFT addresses the persistent issue of efficiently conveying lunar soil under lunar gravity on the moon by leveraging scoops and a static central auger to prevent blockages and maintain consistent throughput. Unlike energy-intensive belt or pneumatic systems, its low-speed rotating drum and fixed screw mechanism significantly cut power requirements and reduce wear, enhancing durability in dusty, abrasive conditions. The gentle handling of material curbs dust generation, safeguarding downstream ISRU units and habitation modules from contamination, a challenge that high-velocity transport methods struggle to overcome. Its lightweight, stackable modules allow straightforward scaling of lift height and capacity to match mission needs without imposing large payload burdens.

Technology Maturation 
Flight Opportunities’ parabolic flights will deliver authentic data by capturing Rego-LIFT’s flow rates, torque profiles, and power draw specifically during lunar gravity phases, enabling us to calibrate our discrete element method (DEM) simulations and refine predictive models. We will visually characterize material behavior at the scoops, through the static auger, and at the conveyor outlet, first using controlled glass beads for calibration and then lunar simulant, to characterize flow patterns and detect any regolith arching or backflow. Real-time validation of our closed-loop control system lunar gravity will allow us to fine-tune motor sizing, and duty cycles for operation. Post-flight, we will produce updated performance maps, validated design parameters, and detailed specifications to support the development of a vacuum-qualified, TRL 5 conveyor prototype.

Benefits

Overview

Ambrosia Space is building scalable in-space biomanufacturing systems for large-scale protein and nutrient manufacturing. The Cell-Sep Technology is able to process large volumes of liquid-based cell culture efficiently in reduced and microgravity environments. This will enable Ambrosia Space to further process and utilize the products made through its biomanufacturing systems to enable nutrient production for astronauts on long duration crewed missions.

Problem Statement 
The Cell-Sep Technology solves the problem of how to turn bioreactor output into usable final products. There is no flight-proven system to perform cell separation out of a bioreactor, and the centrifugation capabilities on space are designed for small samples (2L of broth from the bioreactor. This system is better than existing Earth systems because it is designed for low power and continuous operations – none of the terrestrial systems are designed for the low flow rate, low power, and continuous operations.

Technology Maturation 
Flight Opportunities’ flight tests enable testing of this technology in the microgravity environment. This should improve understanding of the product’s functionality, its useful life, and practice operations for how it would operate on real missions. The lessons learned from the flight, are expected to improve the system design and support flight operations for the first payload to the International Space Station.

Benefits

Overview

Building on previous parabolic flights, the Human Tended Space Biology: Enabling Suborbital Genomics and Gene Expression suborbital flight test effort aims to develop operational concepts and deployment tests for gene expression analyses. Using plants as the test organisms, the project will conduct the first suborbital, human-tended, whole genome gene expression experiments. The tests will utilize fixation tubes from NASA’s Kennedy Space Center for safety containment and operational effectiveness, as well as fluorescent imaging hardware from the University of Florida, to measure the biological response of plants to gravity change.

Problem Statement 

This area of science, adaptation processes in response to transitional g loads to and from microgravity, is completely unknown and unapproached. This situation leaves a large gap in knowledge regarding the changes that occur in biology as organisms adapt to and from microgravity. That gap in knowledge can be richly filled using suborbital vehicles, and can best be filled using tools and technologies that can be deployed by humans within the vehicle, thereby keeping the experiment operations similar to earth bound and ISS experiments.

The technology of the KFTs has been well developed for many spaceflight and spaceflight related operational environments, however they have never been deployed in suborbital vehicles nor have the associated operations plans or associated facilities been developed for suborbital deployments.
Technology Maturation The technology development goal is to examine and test the effectiveness and limitations of deploying KFTs within commercial suborbital vehicles and during typical suborbital flight profiles. The scientific goal is to capture gene expression data from plants at various stages of the flight in order to characterize the rapid and early phases of the adaptation processes that accompany transitions among g-loads.

Summary of Flight Test
2024-08-29 This flight was able to demonstrate the development of research, hardware, and operations for a scientist astronaut to fly their science in space. The ability for a scientist to operate the experiment that was developed into study spaceflight effects of biology, is uniquely important, as the experience that a scientist and the biology they are studying are similar. By interpreting the conditions that the plants experienced, beyond what is recordable by a machine/data logger, will give the scientistastronaut unparalleled insight into the results.

Benefits

• Innovative: First measurement of its kind during sub-orbital flight
• Focused: Research looks at the effect of multiple gravity environments
• Risk-reducing: Optimizes human health in high-altitude and suborbital flight 

Future Customers
• Human space exploration and long-duration crewed missions
• Biological research
• Material sciences
• Fluid physics

Overview

This technology enables reliable in-space propellant transfer by acoustically generating and controlling a secondary ullage bubble directly at the vent port of a spacecraft propellant tank. This method leverages dissolved helium gas in the propellant and phased-array ultrasonic fields to direct bubble nucleation, growth, and migration without the need for gravity or settling burns. The approach eliminates propellant loss through the vent during refueling, allowing efficient, low-risk fluid transfer in microgravity. By addressing a key technological gap, it expands the feasibility of large-scale refueling operations critical for Artemis and Moon-to-Mars missions, orbital servicing, and future commercial propellant depots.

Problem Statement
• Current in-space refueling architectures require settling burns to position ullage gas for venting, which consumes propellant and adds mission risk; this approach eliminates this need.
• This technology ensures ullage gas is reliably located at the vent port in microgravity using modest power input and no tank modification, preserving tank integrity and commodity purity.
• Traditional refueling approaches result in propellant loss rates as high as 20%; this acoustic ullage control reduces liquid expulsion losses to under 5% of tank volume.
• The solution is propellant-agnostic and scalable, enabling application across a broad range of spacecraft designs and mission profiles.

Technology Maturation
• Flight Opportunities tests will demonstrate acoustic ullage formation and control in relevant reduced-gravity environments, validating computational predictions under flight conditions.
• The tests will help optimize ultrasonic transducer array configurations, power requirements, and control algorithms for use with flight-representative fluids and tank geometries.
• Post-flight, the technology is expected to advance to TRL 5, providing NASA and commercial partners with a proven capability for loss-limited propellant transfer in microgravity.
• These results will directly inform the design of flight-qualified hardware for Artemis-related missions, commercial fuel depots, and future orbital servicing platforms.

 

Benefits

Overview

More science experimentation and technology development can be accomplished on nano-satellites than ever before. With this growth in capability, it is highly advantageous to NASA to be able to launch nano-satellites (with mass under 25 kg) as primary payloads into Low Earth Orbit as cost-effectively as possible. AVA (Affordable Vehicle Avionics) is a generic avionics technology that can be easily ported between launch vehicles, and leveraged by several third-party launch service providers. This technology is slated to undergo additional testing aboard an UP Aerospace rocket.

Benefits

The Affordable Vehicle Avionics (AVA) effort is a low-cost avionics system capable of guiding a small launch vehicle into Low Earth Orbit (LEO). UP Aerospace entered a SAA with NASA Ames Research Center for the development and flight testing of the AVA hardware on the SpaceLoft and ultimately on the Spyder launch vehicle. 

The benefits of this effort include reducing the high costs of avionics typically required to operate orbital launch vehicles, and to buy down risk via demonstrations using COTS components. This design could be incorporated for use by small business ventures that can develop a business case for orbital launch capability.

Overview

Ecoatoms' HERMES provides an automated genetic material extraction solution for diverse biological samples, significantly reducing astronaut time spent on research and development procedures. By enabling machine-driven workflows HERMES directly addresses NASA’s General-Purpose Robotic Manipulation shortfall. This innovation advances human-scale logistics and utilization in space, while reducing significant costs allowing astronauts to focus on critical missions while automation handles complex laboratory tasks with precision and consistency.

Problem Statement 
HERMES solves the problem of labor-intensive, manual DNA extraction in space by automating the process, reducing astronaut time and experimental errors in microgravity. Unlike current semi-automated, non-commercial technologies that lack integrated centrifugation, or software, HERMES combines microfluidics and mixing platforms with an onboard computer for user-programmable, precise workflows. This all-in-one system enhances efficiency, accuracy, and cost-effectiveness, enabling routine, high-throughput DNA extraction for space-based genomics research.

Technology Maturation 
NASA’s Flight Opportunities program will advance HERMES’s TRL by validating its automated DNA extraction capabilities through parabolic flight testing. These flights will confirm the system’s microfluidics, centrifugation, and software functionality in microgravity, enabling precise processing of a great number of reagents. Successful testing will demonstrate HERMES’s ability to perform complex laboratory tasks with minimal astronaut intervention, accelerating its readiness and full automation for future space-based genomics research.
 

Benefits

Overview

The IMPRESS (Iterative Mars Penetrator for Subsurface Science) system by Guinn Partners is a way to deploy swarms of small-scale aircraft across the Martian terrain at a low cost. IMPRESS comprises multiple probes that share a shielded entry vehicle. The probes penetrate the planetary surface and use electronic sensors that search for traces of water or microbial life. Each probe deploys radio beacons that map the local geography to help future missions touch down safely. At ~$3,000 per probe, IMPRESS makes subsurface science on Mars affordable for organizations of any scale.

Problem Statement
Previous models of planetary penetrator probes—despite being impressive feats of engineering—were expensive to produce, had little room for modular customization, and were usually intended to be launched in isolation. Guinn Partners’ IMPRESS is a system for launching large swarms of probes across the Martian surface at an affordable cost. Multiple organizations can buy and customize probes in “rideshare” Mars missions. IMPRESS probes also bring several design innovations to the penetrator probe concept, such as aerodynamic airbrakes that regulate terminal velocity and control impact.

Technology Maturation
The goal of flight testing is to assess the IMPRESS probes’ ability to survive impact and flight testing. The insights yielded by Flight Opportunities flight testing will not only improve and validate the IMPRESS system but will help similar subsurface or penetrator projects improve their own high velocity survival as well.

Benefits

Overview

CELS enables broad research capabilities for in-situ cell-based experiments as well as studies involving organoids and microphysiological systems (MPS), also known as organ-on-a-chip technology. The primary technologies in CELS are microfluidic systems and analytical systems for sample handling and mixing, spectrophotometry, and imaging for downstream analysis capabilities. CELS streamlines studies by automating cell culturing, treatment delivery, and analysis without the need for manual intervention or downmass.

Problem Statement
The current state-of-the-art for biological experiments in microgravity is reliant on International Space Station scheduling, astronaut intervention, and downmass. Biological experimentation in space is constrained by turnaround time and cost. CELS, a fully autonomous biological payload enabling sample handling and preparation for microgravity analysis, focuses on ensuring high-quality biological experimentation. By integrating into free-flying satellites, hosted flights, and space stations, CELS fast-tracks access, decreases cost, improves current capabilities, and enhances reproducibility.

Technology Maturation
The Flight Opportunities’ flight test will help achieve baseline space heritage for the systems and components while supporting a simple organoid study. This will allow the team to further refine systems, develop additional technologies, and improve ground handling protocols which then could be adapted to more complex studies in the future.

Benefits

Overview

SpaceWorks and Astral Materials will develop and fly a dedicated microgravity platform for crystal manufacturing that has reentry capabilities. The system integrates a high-temperature crystal manufacturing platform with a thermal management system into SpaceWorks' re-entry device vehicle. This enables autonomous, uncrewed crystal growth experimentation in microgravity and a safe return to Earth.

Problem Statement 
Current terrestrial silicon crystal manufacturing faces inevitable, gravity-induced defects that limit material quality. Microgravity environments offer crystal growth with less defects, enabling superior semiconductor properties. This technology addresses NASA's investments in scalable in-space manufacturing, advanced thermal management systems, and commoditized reentry vehicles. By developing a high-cadence processing and return service, this technology can help both advance scientific discovery and establish a commercial service for in-space manufactured goods.

Technology Maturation 
A successful flight test demonstrates flight heritage for the microgravity crystal growth furnace, integration on a low-cost reentry vehicle, and deployment on a commercial off-the-shelf (COTS) flight service provider. This will advance the combined platform to TRL 8, paving the way to repeatable and high-cadence operations necessary to fulfill needs of commercial markets and other users.

Benefits

Overview

Juno Propulsion is developing a novel high-thrust, high-efficiency propulsion system utilizing rotating detonation rocket engine technology. Our product leverages the 5-10% higher specific impulse of rotating detonation rocket engine (RDRE) technology to be competitive with current hypergolic bi-propellant solutions, enabling a 50% increase in payload capacity, 10% lifespan increase, doubling speed to target, and use of green propellants.

Problem Statement 
New demands for agile in-space operations have driven an increased need for high-thrust, high-efficiency propulsion. The state of the art employs hydrazine and nitrogen tetroxide because of their higher performance and hypergolicity. However, major drawbacks include toxicity, high cost ($1000s/kg), supply chain risks, and inherent complexity due to the need for a pressurant system. By using RDRE technology, Juno’s thruster can improve the specific impulse by up to 5% over the state of the art with non-toxic fuels of nitrous oxide and ethane.

Technology Maturation 
The benefit of an orbital test is performance characterization in a vacuum, low-g environment. To date, RDREs have been almost exclusively tested on the ground and under sea-level atmospheric conditions. Our test will determine thrust delivered, specific impulse, and torque of the flight platform. Finally, demonstration of an RDRE in a space environment provides flight heritage for commercial validation.

Benefits

Overview

The Microgravity Testing of Lightweight, Reliable Cryogenic Screen Channel Acquisition Devices with High Expulsion Efficiency project tests a device designed to advance storage and transfer of cryogenic fuels on the lunar surface and in orbit. This lightweight cryogenic liquid acquisition device (LAD) consists of metal mesh screen channels, a screened sump, and guide vanes. The hybrid capillary structures position the residual liquid in the tank to optimum locations to maintain liquid supply for LAD screen surfaces, enhancing expulsion efficiency. The technology has previously completed a parabolic flight campaign, and the experiments performed through these additional flight tests aim to further improve the quality of test data, allow more comprehensive characterization of LAD performance, and promote further technical maturity. 

Problem Statement 

Technology for refueling liquid propellants in microgravity is required for long-distance spaceflights of vehicles with large payloads. A challenge for refueling cryogenic propellants in space is the acquisition of vapor-free liquid propellant from the supply tank and its subsequent transfer to the receiving tank of a spacecraft. This hybrid LAD addresses this need by synergistically combining screen channel flow structures and lightweight guide vanes. Screen-channel LADs are highly advantageous for systems with high-demand flow rates; however, there are currently no cryogenic LADs qualified for spaceflight. 

Technology Maturation 

These tests, to be performed on four Zero Gravity Corporation parabolic flights, are expected to demonstrate steady liquid propellant acquisition via the screened channel and guide vanes during various flow conditions without breakdown. They will also evaluate the achievable expulsion efficiency as a function of demand flow. Data aims to confirm viability of the technology in microgravity and will also be used to anchor existing LAD design models, including guide vane performance. 

The flight tests aim to advance this technology from technology readiness level (TRL) 5 to TRL 6. It is anticipated that this will enable its infusion into cryogenic propellant transfer systems, including those being developed for NASA’s Artemis program and commercial missions. 

This work is a continuation of previous flight testing under T0311-P and T0337-S. 

Summary of Flight Test
2024-04-15 Creare has successfully demonstrated our innovative hybrid screen channel liquid acquisition device (LAD) for cryogenic propellent transfer in microgravity conditions. The LAD consists of flow structures fabricated from microporous metal mesh using advanced laser welding methods, and lightweight guide vanes to promote high expulsion efficiency. This technology has applications to on-orbit refueling of propellant tanks for future long duration space missions. Funding for the development and testing of this technology was provided by the NASA SBIR program and NASA Flight Opportunities.

Benefits

Overview

The Parabolic Flight Experiments for Measurement of Spray Heat Transfer During Cryogen Chilldown of Receiver Tank aim to support refueling of spacecraft. Through parabolic flight tests, researchers will evaluate cryogenic tank chilldown via spray injection and fill methods that avoid venting precious liquid directly into space. Researchers will use data collected during flight testing for development of experimentally validated universal direct-cryogenic spray correlations. These correlations will potentially be integrated into the design and analysis of future in-space cryogenic transfer systems for use in microgravity and missions to the Moon and Mars.

Problem Statement
Accurate design of cryogenic propellant transfer systems where two-phase cryogenic flow occurs (including transfer lines and propellant tanks) requires reliable correlations at the fundamental level. However, the thermal/fluid design codes currently used to design cryogenic propellant transfer systems do not address all phenomena, such as spray trajectory, droplet heat and mass transfer, and spray boiling at the wall.

Additionally, all available spray boiling correlations are based on room temperature fluids, not cryogens. Therefore, there is a need for direct cryogenic correlations that accurately captures the fundamental heat and mass transfer rates associated with tank chilldown and fill.

Technology Maturation
Parabolic flight experiments with Zero Gravity Corporation will gather lunar, Martian, and microgravity steady-state cryogenic spray heat transfer data over two flight campaigns. By measuring the relationship between spray heat transfer and wall temperature as a function of gravity, mass flow rate, pressure, inlet temperature, and spray droplet parameters, the data are expected to enable the development of experimentally validated reduced gravity cryogenic spray heat transfer correlations. The correlations will be made available for integration into NASA’s lumped node fluid/thermal codes that are used for design and analysis of cryogenic tank chill and fill. These flight test aim to advance the innovation from technology readiness level (TRL) 4 to TRL 5.

This work is a continuation of previous flight testing under T0291-P and T0041-P.

Benefits

- Reduced waste: Improves chilldown and fill methods to avoid venting cryogenic fluid into space
- Efficient refueling: Provides basis for more accurate universal cryogenic spray heat transfer correlations to improve design and analysis of cryogenic tank chill and fill

Future Customers
- Cryogenic propellant management for NASA and commercial space missions, including:
- Nuclear thermal propulsion systems
- Chemical propulsion stages
- Ascent stages
Descent stages
In-space fuel depots

Overview

Colloids (tiny particles suspended in a liquid) occur in many different forms (e.g., milk, muddy water, shampoo, and medicine) in our daily lives. Recently, colloids have shown great potential for additive manufacturing, drug delivery, and constructing colloidal superstructures. The overall objective of this research is to develop and demonstrate novel acoustofluidic platforms that enable two unique capabilities: (i) multifunctional control (e.g., concentration, patterning, and alignment) of micro/nanoparticles, and (ii) printing polymer matrix composites containing patterned micro/nanoparticles under reduced gravity.

Problem Statement
Scientists of the NASA Science Mission Directorate conducted years of research on colloids in microgravity. However, few studies have investigated the effects of acoustic waves on colloids under reduced gravity. Few platforms can actively control the concentration, pattern, assembly, and alignment of tiny particles in liquids under reduced gravity. On the other hand, engineers at NASA Marshall Space Flight Center are very interested in developing in-space manufacturing technologies for long space voyages. To fabricate polymer matrix composites reinforced/functionalized with tiny particles, such as carbon nanotubes (CNTs) and silicon carbide (SiC) whiskers, techniques that can arrange particles suspended in polymer resins are critical. However, no 3D printing platforms have been demonstrated to arrange tiny particles in resins and print polymer matrix composites containing patterned/aligned particles under reduced gravity.

Technology Maturation
The research will be conducted during parabolic flight using previously developed acoustofluidic platforms upgraded and optimized for manipulating particles under reduced gravity. The data collected under different gravity conditions will be analysed and compared to understand the mechanisms of acoustically manipulating particles in liquids under reduced gravity.

Benefits

This study will generate new knowledge about the acoustic effects on micro/nanoparticles mixed in liquids under reduced gravity. It can also lead to a novel acoustofluidic technology and a fully functional platform, which can actively manipulate micro/nanoparticles in reduced gravity environments. The study will contribute to in-space advanced manufacturing by developing, understanding, and demonstrating a novel acoustics-assisted stereolithography 3D printing platform.

Future Customers
This project aligns with the Physical Sciences Program of the NASA Science Mission Directorate by contributing to the research on colloids in microgravity. Moreover, this project aligns with the Advanced Manufacturing Program of the NASA Space Technology Mission Directorate.

Overview

Granular and particulate flows are ubiquitous in our world, from river sediment transport to the formation of planetesimals in a solar system. However, a predictive granular theory and associated model are still out of reach. Because collisions between solid particles are inelastic, a granular system is essentially dissipative and far-from equilibrium, which results in the clustering of particles. There is no consensus about the decay rate of particle kinetic energy in a free cooling state after the occurrence of clustering. In this research, predictions by existing theories will be examined experimentally. The results will validate and improve the theories. 

Problem Statement 
The proposed research will use a novel experimental technology known as magnetic particle tracking (MPT). Since a dense granular flow is usually opaque, advanced optical diagnostic techniques are useless. The magnetic tracking method, in contrast, relies on the magnetic field of a few labeled tracers, which can penetrate commonly used non-ferromagnetic materials. The magnetic tracking method is able to provide the Lagrangian trajectory and orientation of a magnetic particle. Hence, its velocity and kinetic energy can be calculated. The research constructs a payload with automated MPT measurements of a large ensemble of particles distributed in 3D suitable for flight on a reduced gravity aircraft. This aircraft will expose the payload to short periods of microgravity (~20 s) by flying a parabolic path. 

Technology Maturation
The flight tests will collec at least 100 such observations, between which the experiment is reset. The MPT technique will allow for 10 trajectories of particles in each experiment to be reconstructed, allowing computation of the free cooling rate for comparison to theory. Observation and measurement of such a visually obscured particle distribution in microgravity has never been done before.

Benefits

Overview

Benefits

Overview

Benefits

Overview

Benefits

Overview

The Automated Lidar Scanning Topography (A-LiST) demonstration will validate this sensor’s performance and verify its simulation and modeling tools designed for lunar landings. Exploring ice-bearing regions on the Moon calls for landing payloads in challenging lighting conditions and in areas with steep topography. The A-LiST sensor is designed to reduce the size, mass, and cost of precision terrain mapping technology in an effort to enable hazard detection during terminal entry, descent, and landing on the Moon in the dark.

Problem Statement
To further explore dark and shadowed regions on the Moon, a solution is needed for landing payloads under these challenging lighting conditions and in areas with steep terrain. Smaller, lighter weight hazard detection systems will enable safe descents in lunar ice-bearing regions. The A-LiST sensor combines multiple commercially available light detection and ranging (lidar) sensor heads to collect point data across multiple perspectives simultaneously. Combined with a customizable mounting fixture, the A-LiST sensor is designed to achieve 10-centimeter point resolution across a 250-meter diameter target area from an altitude of at least 250 meters. A-LiST then synthesizes the point clouds, which represent shapes or objects in 3D, to create a single high-resolution topographical map for hazard detection, safe landing site selection, and terminal navigation.

Technology Maturation
Flights tests are expected to provide data for validating sensor performance and verifying simulation and modeling tools. These steps are critical to raise the technology readiness level of the sensor in preparation for safely launching it into space and landing on the Moon. The flight tests are expected to provide further evidence of the durability of the sensor and confirm applicability of the technology for use in other space exploration missions as well as in other industries.

Benefits

To achieve further lunar exploration, a solution is needed for landing payloads in low-light conditions and steep terrains. The Automated Lidar Scanning Topography (A-LiST) sensor is designed to facilitate this capability. This has the potential to benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
• NASA or commercial space exploration missions
• Commercial lunar service providers

Overview

The NASA On Demand Manufacturing of Electronics (ODME) overall project goal is to develop and demonstrate the feasibility of a low-gravity, on-demand manufacturing system for flexible hybrid electronic devices on the International Space Station (ISS). Thin film printing methods are necessary to create more intricate electronic devices in a smaller size due to better feature and line resolution. A thin film printing technology that is well suited for performance in microgravity, EHD ink jet printing, needs to be integrated into the multi-materials printer to produce complete devices.

Summary of Flight Test
2024-08-20 The parabolic flight campaign was successful in demonstrating the Advanced Toolplate System (ATS) in a zerogravity environment. Several tools required to enable additive manufacturing of electronic devices were validated during the campaign, including the SmartPump for direct ink write, extrusion-based printing, nPnP for component pick and place functionality, as well as the ultraviolet light and 445nm laser tools.
2024-08-21 The flight campaign achieved valuable results that concluded the capability of the Sciperio EHD printer to perform well under a zero-gravity environment. This conclusion was proved by printing several good silver lines successfully during the zero gravity 30-second period. Another additional achievement is that this printer showed it is the capability of printing another material which is ZnO ink.

Benefits

Overview

The technology under development is tooling for extraterrestrial mining or prospecting machinery that leverages the use of forced, resonant vibration to fluidize soil around the leading edge of a probe or shovel. This allows the tool to then move through a dynamic, fluidized soil making it easier for the tool to progress through the soil with less required force. This technology is inherently different from percussive systems or reciprocating systems that use voice coil actuators or similar. The resonant vibration is continuous, unlike percussive, and has a very small amplitude around 54 μm, unlike reciprocating systems that can achieve centimeters of stroke at low frequencies.

Summary of Flight Test
2024-04-15 NASA Glenn Research Center partnered with Concordia University through an International Space Act Agreement to investigate the use of an ultrasonically vibrating blade in lunar regolith simulant at lunar and Martian gravities. The use of vibratory tools is known to reduce forces between the vibrating tool and the soil on Earth. Reducing tooling forces means that reaction forces experienced by the system are also lowered indicating the potential for system mass savings. This flight set out to establish what magnitude of force reduction can be expected from an ultrasonic tool on the Moon and Mars. Regolith interaction including excavation will be an important part of NASA’s use of lunar and Martian regoliths for resource development to support long duration missions to both bodies.

Benefits

Overview

Researchers at Purdue University are exploring Nucleation of Cryogenic Bubbles in Spacecraft Liquid Acquisition Devices in order to address questions raised during a precursor NASA project on the International Space Station. The previous project found the creation of vapor bubbles during a reduction in test tank pressure. Purdue will fly a liquid-vapor nitrogen system on parabolic flights to explore thermodynamic states and changes relevant to resolving questions raised by the station experiment, with the goal of helping to advance long-term cryogenic propellant storage in the weightlessness of space. 

Problem Statement 
The zero-boil-off tank (ZBOT) experiment on the International Space Station was a remarkable achievement in cryogenic propellant management technology in the weightlessness of spaceflight. However, despite providing many technological answers, ZBOT also produced new questions. Purdue researchers seek to advance the technology for long-term weightless cryogenic propellant storage by exploring one of the questions raised by ZBOT—specifically, the creation of vapor bubbles in or near the flat screen of the ZBOT during a reduction of pressure in the test tank.

Technology Maturation
Researchers will fly a liquid-vapor nitrogen system on a parabolic aircraft with an overboard vent system in operation. The same refrigerant used in ZBOT will be implemented to demonstrate the similarity or difference in behavior of the ZBOT refrigerant and a more representative cryogenic system. Liquid nitrogen is expected to behave much more similarly to liquid oxygen than the much larger molecules in the ZBOT refrigerant did.

Summary of Flight Test
2023-10-16, 2023-11-28, & 2024-04-15: Initial flights of the complex Purdue CryoBubbles experiment were productive. The team was able to identify several improvements in hardware, in-flight operations, and ground operations for the second set of flights dates in the next year. This experiment is a complex system operating at nearly minus 200 Celsius and thus it is important that safety of the design and its basic operations were both verified in this pair of flights.
2025-04-29: The Purdue team on the “CryoBubbles” experiment flew parabolas for two days. Initial indications are that the experiment functioned safely and created the necessary thermodynamic state in the liquid and vaporous nitrogen in the test vessels. Additional flights can produce a wealth of useful data on the phase transition process.

Benefits

Researchers at Purdue University are exploring Nucleation of Cryogenic Bubbles in Spacecraft Liquid Acquisition Devices in order to address questions raised in precursor NASA experiments in cryogenic propellant management on the International Space Station—specifically, the creation of vapor bubbles during a reduction in test tank pressure. Purdue will fly a liquid-vapor nitrogen system on parabolic flights to explore thermodynamic states and changes relevant to resolving questions raised by the station experiment, with the goal of helping to advance long-term cryogenic propellant storage in the weightlessness of space. This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Long-duration lunar and cis-lunar missions utilizing cryogenic propellant
•Space-based cryogenic propellant storage and fuel depots

Overview

The Strategic Tac Radio and Tac Overwatch (STRATO) system is designed to provide real-time fire observations and last-mile communications with firefighters from stratospheric platforms. By providing persistent communications to a wildfire response team for a week or longer, STRATO is expected to offer capabilities beyond the currently used tethered balloons, which have a limited range and coverage area. By achieving station-keeping at altitudes up to 70,000 feet above ground level—to be demonstrated in flight testing—the STRATO will be able to provide communications to incident response teams in areas with no cellphone coverage. 

Problem Statement
Active wildfire management depends not only on real-time observations but also on direct contact with firefighters (i.e., last-mile communications). Response teams often operate in areas with no cellphone coverage, which limits the ability to transmit data in and out. Although FirstNet (the U.S. network for emergency responders and public safety) can extend the communications range via its tethered balloons, the range and coverage are limited.
Researchers are evaluating the technical, operational, and financial feasibility of using stratospheric platforms for providing last-mile communications for wildfires and other remote incidents. The goal is to provide persistent LTE wireless broadband and multiple-input multiple-output (MIMO) radio communications to a wildfire incident response team for a week or longer. To be successful, the stratospheric balloon must achieve station-keeping at altitudes from 50,000 to 70,000 feet above ground level.

Technology Maturation
Flight testing will provide a valuable opportunity to demonstrate the potential for high-altitude, long-endurance imaging and communications with/by end users in an operational environment. The test apparatus includes an LTE transmitter, a Silvus-brand receiver and transmitter, and a microbolometer (i.e., thermal camera) contained on an Aerostar Thunderhead high-altitude balloon system.

Benefits

Persistent coverage through effective station-keeping of a stratosphere-based system can offer real-time fire observations as well as last-mile communications directly with firefighters in areas with no cellphone service. This has the potential to benefit NASA missions, the commercial space industry, other government agencies, and the nation. Flight testing will provide a valuable opportunity to demonstrate the potential for high-altitude, long-endurance imaging and communications with/by end users in an operational environment. The test apparatus includes an LTE transmitter, a Silvus-brand receiver and transmitter, and a microbolometer (i.e., thermal camera) contained on an Aerostar Thunderhead high-altitude balloon system. 

Future Customers 

• National Interagency Fire Center 

• U.S. Forest Service 

• Other firefighting agencies

Overview

Benefits

Overview

The PUFFER-Oriented Compact Cleaning and Excavation Tool (POCCET) demonstration will assess the viability of a miniature dust removal tool designed to mount on small rovers, such as the PUFFER platform developed by NASA’s Jet Propulsion Laboratory. On Mars and the Moon, regolith and dust cover rocky outcrops that must be cleared to provide accurate analysis of the samples beneath. Current dust removal technology is limited, relying on techniques that use physical contact and are ineffective in the vacuum of space. POCCET uses an effective pneumatic dust removal technique to rapidly “blow” dust away at a fractionally small mass. 

Problem Statement 

Regolith and dust cover rocky outcrops on the Moon and Mars that must be cleared to provide accurate analysis of the samples beneath. Most current dust removal technology relies on brushes, rasps, or other removal techniques that use physical contact. In many circumstances, this technology is ineffective due to the dominance of electrostatic forces in vacuum conditions. Ultra-small rovers cannot carry the large batteries and actuators for such operations. To send more spacecraft to new places on the Moon, smaller spacecraft and mobility systems will be used. A miniature tool designed for mounting on small rovers, POCCET uses compressed gas to rapidly remove dust from the scientifically important subsurface of rocks, regolith-covered ices, key equipment such as solar panels, and sealing surfaces. Weighing less than 300 grams with potential for further mass reduction, POCCET could be used not just on the Moon, but on other solar system bodies, such as asteroids, comets, and Mars.

Technology Maturation 

Flight tests are expected to prove dust removal capability in a partial-gravity environment. The researchers will be able to address feedback provided by simulating lunar gravity in suborbital flights and using regolith simulant. With the technology currently at TRL 5, the flight tests will indicate performance in a relevant environment and allow the researchers to make any further design refinements needed.

Summary of Flight Test
2025-02-04 PUFFER-Oriented Compact Cleaning and Excavation Tool (POCCET) – POCCET is designed to explore granular material interactions with a pneumatic system in lunar gravity conditions. The system will demonstrate non-contact pneumatic trenching by blowing air at a known outlet pressure onto a surface of loose kinetic sand and recording the response. The data collected will expand our understanding of possible pneumatic applications as more mass- and power-efficient alternatives to traditional mechanisms.

Benefits

Overview

The Current batteries that provide energy storage on spacecraft are limited by their relatively low energy density, cycle life, and cycle duration. The Non-Flow-Through Fuel Cell (NFTFC) for High-Density Energy Storage system has a high projected energy storage density (>400 Wh/kg) and can be scaled up to accommodate long-duration discharges (e.g., to provide power throughout a 14-day lunar night). The NFTFC uses an integrated gas-liquid separation membrane to passively remove water without excess flow of reactants, which improves fuel utilization and allows for a simpler balance of plant. Flight tests aim to demonstrate system functionality – specifically that of the integrated phase separator – in a space environment. 

Problem Statement 
High-power, high-density energy sources are a key technology development area to enable future lunar surface operations. Incumbent lithium batteries have substantial flight heritage but relatively low energy storage densities (

Benefits

Integrated phase separator: Allows for a simpler system design and higher fuel utilization than conventional fuel cells High-density energy: Provides mass and launch cost reduction relative to state-of-the-art battery technology 

Future Customers
Potential for NASA and commercial aerospace companies for lunar surface and in-space energy storage Applicable to the U.S. Department of Defense, including high-altitude pseudo satellites (HAPS) and satellite energy storage

Overview

Dynamic fluid experiments in space are challenging due to limitations of current syringe-based devices and astronaut time. The VIPER microfluidic control system overcomes those challenges by automating complex biological and chemical mixing experiments. This miniature pump-and-valve system with multiple small fluid reservoirs provides a general-purpose control platform for fluidic experiments in microgravity. It employs time-division fluidic multiplexing, which mimics circadian and diurnal rhythms. Sensors monitor temperature, humidity, and dissolved gas concentrations within fluidics, providing comprehensive information to scientists.

Problem Statement 
This technology is a novel, general-purpose, automated microfluidic experiment control platform optimized for use in volume-limited space vehicles. It is designed to meet the challenge of performing dynamic, small, fluidic volume experiments in space. This test is to demonstrate the robustness and basic functionality of the device and control system for experimental protocols.

Technology Maturation 
The VIPER platform has been extensively tested in ground-based laboratories but has not yet been tested in launch, orbital microgravity, or recovery. Demonstration of its robustness and reliability during and after a suborbital flight will help move the technology into the space-based research and commercial arena.

Benefits

The VIPER system provides micro-volume chambers for up to eight experiments in a compact package. It supports complicated arrays of microbioreactor chambers and executes precise, preprogrammed, computer-controlled protocols. This would benefit future NASA missions and the commercial space industry.

Future Customers
• Tissue chips, stem cell differentiation, and sentinel cell maintenance
• Chemical/Pharmaceutical synthesis
• Tissue engineering (regenerative, repair)
• Combined component crystallization processes

Overview

The High-Precision Continuous-Time PNT Compact Module for the LunaNet Small Spacecraft demonstration will assess the performance of this optomechanical accelerometer under real flight conditions. Accelerometers are motion and rotation sensors that are essential in inertial navigation systems to calculate the location, orientation, and velocity of a spacecraft. Developed in support of the LunaNet positioning, navigation, and timing (PNT) system, this high-precision, chip-scale optomechanical accelerometer improves upon the performance of existing technologies and precisely determines the position of a space vehicle without needing external signals. 

Problem Statement 
Inertial navigation systems (INSs) are important to space exploration as they can calculate the location, orientation, and velocity of a moving object such as a spacecraft. INS devices typically use accelerometers, which are motion and rotation sensors, to communicate with a computer and translate the data into actionable controls. UCLA’s optomechanical accelerometer precisely determines the position of a space vehicle without needing external signals. By operating with noise floor levels close to the thermomechanical theoretical limit, this accelerometer provides an order of magnitude performance increase over existing technologies. It also has internal optical feedback, meaning that there is no need for an electrical feedback loop. Finally, the small size of the optomechanical accelerometer allows for further integration and miniaturization of the navigation sensor assembly. 

Technology Maturation 
Flight tests are expected to demonstrate the technology for the first time on a high-altitude balloon flight, providing the researchers with valuable data on its performance under real flight and environmental conditions. Additionally, the ability to follow a flight trajectory and the integration with the navigation algorithms is expected be assessed.

Summary of September 10, 2025 Flight Test
Without navigation systems such as GPS routinely used on Earth, spacecraft beyond low Earth orbit calculate their position, velocity, acceleration, and orientation state using inertial navigation systems, which include sensors called accelerometers. A new, miniature optomechanical accelerometer designed by UCLA researchers aims to precisely determine the position of a space vehicle without GPS signals. Its low-noise operation has the potential to provide a vast increase in performance and precision.

The September 10, 2025, high-altitude balloon flight operated by Aerostar of Sioux Falls, South Dakota, gave researchers the opportunity to determine whether their miniature accelerometer can obtain accurate position and orientation data during a suborbital flight, allowing them to evaluate its performance and adjust the design, if needed. Developed with support from the University SmallSat Technology Partnerships initiative, this technology has the potential to support NASA’s LunaNet architecture designed to rapidly expand network capabilities at the Moon as well as vehicles flying in cislunar space.

Benefits

A high-precision, chip-scale optomechanical accelerometer is essential for determining the position of a space vehicle without using external signals. This has the potential to benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
• Spacecraft, aircraft, and ship navigation
• Aerospace defense industry (smart ammunition)
• Smartphone location and tracking
• Health tracking

Overview

The Condensate Separator for Microgravity Conditions (COSMIC) technology demonstration will assess a condensate separator with a rotating seal design for humidity control on human spaceflight missions. The current state-of-the-art approach to humidity control has limitations that result in damage to the water processing system and diminished collection efficiency over time. To address these limitations, COSMIC combines condensate capture, removal, and pumping into one compact, low-power unit. It uses rotary inertial separation to efficiently collect liquid condensate from a high-volume gas stream and does not rely on chemical coatings or surface treatments. COSMIC is intended to enable longer duration missions and higher capacity crew environments. Flight tests aim to validate the condensate capture and seal design in relevant environments. 

Problem Statement 

Current approaches to humidity control rely on a hydrophilic surface coating that is fouled by trace contaminants over time, leading to water carryover that causes damage to downstream hardware and the water processing system as well as diminished collection efficiency. 

To address these limitations, COSMIC combines condensate capture, removal, and pumping designs into a single-stage compact unit that installs in-line downstream of a condensing heat exchanger (CHX). It uses rotary inertial separation to efficiently collect liquid condensate from a high-volume gas stream and does not rely on chemical coatings or surface treatments. COSMIC is intended to replace components like the slurper and water separator in the humidity control system currently on the International Space Station with a robust solution that is not affected by the presence of siloxanes or other trace contaminants and functions independently of surface wetting behavior in the CHX. It is designed to eliminate the resulting risk for water carryover that damages downstream components as well as siloxane-related contamination of the collected water and the corresponding degradation of the water processing system. 

Technology Maturation 

Flight tests on aircraft following reduced-gravity profiles are expected to demonstrate the technology’s condensate capture and seal design in relevant environments. The separator is expected to be evaluated during reduced and microgravity phases on parabolic flights inside a watertight enclosure containing a compact air loop with water droplet injection that simulates the outflow from a CHX. Cameras and water detectors are expected to validate condensate capture, liquid removal, and seal performance throughout the flights, allowing assessment of microgravity design features and changes in liquid behavior. The flight tests aim to advance this innovation’s technology readiness level (TRL) to TRL 5. Lessons learned from the performance observations will be incorporated into follow-on flight designs. 

Summary of May 8, 2025 Flight Test
• Within testbed limitations, COSMIC successfully demonstrated microgravity performance.
• Follow-on funding would allow for testbed updates to address water injector shortcomings, testbed condensation, and further investigate misting during hypergravity.
• Test passive water retention features at shutdown during microgravity.
 

Benefits

- Streamlined: Combines condensate capture, removal, and pumping into a compact, lightweight, and low-power unit 
- High performance: Uses rotary inertial separation to efficiently collect liquid condensate from a high-volume gas stream 

Future Customers
- NASA and commercial crewed space missions 
- Commercial low-Earth orbit destinations 
- Water recovery systems as part of or in conjunction with in-situ resource facilities

Overview

Obtaining high spectral resolution spectra of astronomical (or other) targets currently requires large telescopes or a Fourier Transform Spectrometer with moving parts. This presents a challenge to space missions with harsh vibration environments and mass limitations. Spatial Heterodyne Spectroscopy (SHS) is an interferometric technique with no moving parts. It enables obtaining data with the sensitivity of Hubble Space Telescope but over a very narrow bandpass of interest that can be defined to be in any wavelength from UV to IR. SHS is a niche instrument studying targeted spectral lines.

Problem Statement
Traditional high spectral resolution spectrometers are coupled to large aperture telescopes to compensate for their low throughput, which causes significant disadvantages for space probes and the temporal studies of faint, angularly extended sources on the ground. A Spatial Heterodyne Spectrometer (SHS) offers significant advantages in obtaining high spectral resolution and high sensitivity from a narrow wavelength range of interest on board of small aperture telescopes (1-15 cm) more suitable for space platforms.

Technology Maturation
This flight demo will measure the vertical density profiles of hydroxyl (O.H.) in the middle atmosphere at 80 km altitude and will obtain data for the entire duration of the flight. This will enable 1) obtaining data from outside the lab, which will increase the science concept maturity, 2) test, and validate instrument survival and performance in rocket launch conditions (temp/vibrat), 3) advance the spectrometer module.

Benefits

Overview

Benefits

- Intelligent design: Uses robust laser welding processes to create reliable pore structure? - Temperature regulating: Doubles as an interface heat exchanger ? - Enabling: Is designed to meet the complex demand for efficient refueling on long-duration exploration missions

Future Customers
- Lunar ascent and descent
- Fuel depots Nuclear thermal propulsion systems
- Commercial in-space transfer systems
- Phase separators in two-phase reactors
- Fluid management for two-phase thermal control

Overview

The Suborbital Flight Assessment of Preserved Red Blood Cells for Transfusion Therapy in Reduced Gravity experiment will assess a method of red blood cell (RBC) storage in reduced gravity. Although radiation-induced anemia is a hazard to astronauts, whole blood or RBC storage and transfusion capabilities are a challenge due to biological limits on storage duration and the power and mass requirements for storage. The use of dehydrated RBCs prepared pre-flight offers long-term blood storage at ambient spacecraft temperature and rehydration with sterile saline, making the storage, handling, and restoration of the RBC source an option for extended exploration spaceflight and lunar surface operations. Flight tests aim to assess the automated rehydration of RBCs and their physiological status in reduced gravity.

Problem Statement
There is a need to develop a treatment with RBC transfusion technology that is compatible with exploration spaceflight. This technology provides a spaceflight-compatible method to provide blood transfusion therapy by preserving RBCs for long-term storage in a dried stage. It uses sonoporation to load RBCs with the protective compound trehalose. The biomimetic approach allows for the preservation of RBCs without requiring refrigeration. Rehydration is achieved by adding sterile saline to the dried RBCs. After rehydration, these RBCs can be used for transfusion therapy in both standard and austere environments, including the reduced gravity experienced during exploration spaceflight and extended lunar missions.

Currently available methods require the blood to be stored in a refrigerator, and it is only good for 42 days. Dehydrated RBCs can be stored in a plastic bag at room temperature for more than 3 years (longer than a round-trip flight to Mars) and can then be rehydrated 1 minute before starting the transfusion.

Technology Maturation
Flight tests on a suborbital rocket are expected to assess the automated rehydration of RBCs and their physiological status in reduced gravity. The flight tests aim to advance the preserved human RBCs for transfusion therapy to technology readiness level (TRL) 7. After the flight, researchers expect to verify that the rehydrated RBCs can carry oxygen and have regained a shape that can safely move through the blood vessels. This work is a continuation of previous flight testing under T0049-P, T0155-S, and T0287-P.

Benefits

Spaceflight compatible: Preserves dehydrated RBCs

Long-term storage: Can be stored in a plastic bag at room temperature for more than 3 years (longer than a round-trip to Mars) Easy rehydration: Under 1 minute to rehydrate RBCs by adding a sterile saline

Future Customers
- Potential for crew medical officers aboard human-tended spaceflight to use when treating radiation-induced anemia or an in-flight trauma
- For use by physicians in extreme and remote conditions on Earth for transfusion therapy for trauma and other illnesses

Overview

The Satellite for Natural and Artificial Plumes (SNAP) project aims to detect and classify natural and anthropogenic plumes in real time, which could enable timely tracking of short-timescale events (current solutions rely on post-processing of downlinked data). Specific plume cases can be generalized to any event detectable by computer-vision techniques. SNAP will use gimbaled cameras to identify and track plumes. The data from the cameras (visible to mid-infrared [IR]) will be processed by a trained neural network to quickly identify plumes. Plume properties, location, and images will be determined and downlinked. 

Problem Statement 
Current plume detection and classification solutions rely on post-processing of downlinked data and do not actively track events of interest. Real-time detection could enable real-time tracking of short time-scale events and reduce the amount of data that needs to be downlinked. Specific plume cases can be generalized to any event detectable by computer vision techniques. 

Technology Maturation 
Flight tests are expected to provide real-time plume identification, accurate plume geolocation (with accompanying images/video), and real-time event tracking using neural network image processing within a small satellite (i.e., a 3-unit CubeSat with an instrument weighing approximately 6 kg). The flight tests aim to advance this innovation’s technology readiness level (TRL) from TRL 4 to TRL 6.

Summary of Flight Test
2022-08-03 The Texas A&M SEAK Lab team tested their autonomous plume identification and tracking payload in a high-altitude balloon launch. While technical issues prevented complete mission success, the payload was able to collect images and test its capability to track plumes. The team aims to use the information obtained from this test flight to improve the payload for future test flights and implementation.
2023-05-24 The Satellite for Natural and Artificial Plumes (SNAP), developed by Texas A&M’s SEAK Lab, collected valuable multispectral imagery of Earth’s surface. The SNAP payload functioned close to or at expected performance levels, and shows promise for the development of future technologies. The team’s focus after the flight will be on data analysis and improving the payload for its next mission. The team is grateful to NASA Flight Opportunities and Aerostar for their support of the project.

Benefits

This project aims to detect and classify natural and anthropogenic plumes in real time, which could enable timely tracking of short-timescale events (current solutions rely on post-processing of downlinked data). Specific plume cases can be generalized to any event detectable by computer-vision techniques. SNAP will use gimbaled cameras to identify and track plumes. The data from the cameras (visible to mid-infrared [IR]) will be processed by a trained neural network to quickly identify plumes. Plume properties, location, and images will be determined and downlinked. This has the potential to benefit NASA missions, the commercial space industry, other government agencies such as the National Oceanic and Atmospheric Administration (NOAA), U.S. Environmental Protection Agency (EPA), and U.S. Forest Service, as well as the nation.

Future Customers
- Real-time plume identification, geolocation, and event tracking
- Fire, pollution, and volcanic activity monitoring for terrestrial and space-based applications - NASA, National Oceanic and Atmospheric Administration, U.S. EPA, U.S. Forest Service missions and research

Overview

Benefits

Overview

Benefits

Overview

The MoonFALL: Moon Fast and Accurate Lidar Localization demonstration will assess a technology designed to advance terrain-relative navigation. Smaller, lightweight hazard detection systems for landing on the Moon are necessary for further exploration of scientifically interesting and resource-rich areas. MoonFALL uses a fusion of new sensor technologies with artificial intelligence and edge computing to create real-time maps that fill the gaps in traditional terrain mapping and facilitate safe descents into shadowed, unexplored regions. It leverages structured light superimposed over a potential landing area in combination with advanced image processing and lidar.

Problem Statement 
Low lighting and steep topography create ice-bearing regions on the Moon, creating difficult environments for landing in these scientifically interesting regions. The MoonFALL technology could enable landings in shadowed and dark regions without the need for any previous knowledge of the target landing site. The technology is significantly smaller and lighter than existing systems while still providing high-resolution accuracy. The system leverages the advantages of low light conditions to create real-time maps that allow for future exploration of challenging lunar terrain. The combination of a reflective grid map and light detection and ranging (lidar) advances traditional terrain mapping technologies to allow for safe descents in particularly hazardous terrain.

Technology Maturation
Flight tests are expected to provide the relevant environment in which to validate a technology that is traditionally difficult to verify. During a nighttime suborbital test flight that simulates a lunar descent, the researchers expect to generate a three-dimensional map of a lunar surface test field in real-time from an altitude of at least 250 meters. Data generated by the flight tests are expected to allow the researchers to further refine the technology and move closer to its application.

Summary of Flight Test
2024-09-26 During this test campaign the CPP Bronco Space team was able to demonstrate the effective use of the MoonFALL technology for creation of a high resolution DEM. The team spent the last two years developing the first EDL technology to attempt to use structured light to aid in the rapid mapping of an unknow surface. The test flight has provided extremely valuable data to aid in this ongoing research effort to incorporate machine learning depth estimation metholodies into a flight ready terrain mapping system.

Benefits

The MoonFALL: Moon Fast and Accurate Lidar Localization demonstration will assess a technology designed to advance terrain-relative navigation. Smaller, lightweight hazard detection systems for landing on the Moon are necessary for further exploration of scientifically interesting and resource-rich areas. MoonFALL uses a fusion of new sensor technologies with artificial intelligence and edge computing to create real-time maps that fill the gaps in traditional terrain mapping and facilitate safe descents into shadowed, unexplored regions.

Future Customers
• NASA or commercial space exploration missions
• Commercial lunar service providers
• Landing systems required to operate in dark environments

Overview

The NASA On Demand Manufacturing of Electronics (ODME) overall project goal is to develop and demonstrate the feasibility of a low-gravity, on-demand manufacturing system for semiconductor electronic devices on the International Space Station (ISS). As part of that goal, ODME is partnering with various groups (Intel/NAU/Fujifilm/TEL/Axiom Space) on the development of an high-precision inkjet printer. Advance testing on parabolic flights prior to deployment to the ISS in 2024-2025 results in significant risk reduction.

Summary of Flight Test
2023-11-28 & 2024-02-26 While we did not achieve our goals during this flight, the experience has provided us with valuable insights and learning opportunities. These lessons will guide our future efforts and improvements in pursuit of our goals. Our team remains committed to advancing our projects and is already working on strategies to overcome the obstacles encountered.
2024-03-05 Demonstration of electrohydrodynamically-printed insulator and semiconductor upon conducting material.

Benefits

Overview

The Quantum Earth OBServatory (QEOBS) project will use a high-altitude balloon flight to test a 2U CubeSat designed to demonstrate how onboard data processing and machine learning can result in reduced downlink requirements. Using an array of sensors, the test will evaluate quantum and classical machine learning approaches for Earth observation tasks, including atmospheric gravity wave measurements and multispectral image classification and segmentation. The project aims to use a 30-qubit onboard quantum simulator. The ultimate goal is to fly the 2U CubeSat in low-Earth orbit. 

Problem Statement 
Reducing the amount of raw data that needs to be transferred between a spacecraft and the ground has many benefits (e.g., enabling autonomous operations, increasing speed of information transfer). The use of machine learning offers promise in this domain by allowing data processing to happen at the edge of the network (e.g., on the spacecraft), thereby limiting the need to download the data for ground-based processing. 

Technology Maturation 
The aerospace industry is just beginning to apply traditional machine learning models for mission-critical elements. This project aims to test the applicability and the benefits of such onboard, in-flight technology and improve upon it via quantum simulation/computing, which could benefit the entire aerospace industry. The flight test aims to raise the technology readiness level (TRL) to 5 or 6.

Summary of Flight Test
2022-07-28 To our knowledge this was a world-first technology demonstration of a suborbital flight utilizing quantum machine learning on the edge by utilizing both quantum simulators onboard and in flight as well as IBM quantum computers on the ground via remote connection for earth observation and space research tasks. Our successful flight shows that ML and QML algorithms can indeed be used to detect and classify objects from low earth orbit on remote edge platforms. Furthermore, we demonstrated the remote execution and processing of earth observation data while only downloading the results to the ground therefore only requiring a low communications bandwidth.
2023-05-24 The Quantum Earth Observatory (QEOBS) mission was able to complete another successful technology demonstration flight where dams were detected by machine learning algorithm sand confirmed by quantum machine learning algorithms onboard. Additionally, we were able to train new quantum machine learning models in flight with real quantum computers on the ground. QEOBS was also able to detect atmospheric gravity waves which were also confirmed via the respective gravity wave quantum machine learning models onboard during the cloudy days of the mission. We also collected a large number of multi-spectral (RGB+NIR) earth observation images, which can be used for future projects.

Benefits

This project aims to test the capabilities of a quantum machine-learning-enhanced sensor combination for Earth observation (QMLS-EO) versus traditional and hybrid machine-learning applications for selected Earth observation tasks. Onboard processing has the potential to greatly reduce the amount of data that needs to be transmitted to the ground. The project aims to use a 30-qubit on-board quantum simulation. This has the potential to benefit NASA missions, the commercial space industry, other government agencies, and the nation. 

Future Customers 
This technology has a potentially widespread end-user landscape: 
- Public- and private-sector Earth observation 
- NASA, other space agencies, and research institutions (e.g., U.S. Air Force Research Lab)
- National security satellite applications (e.g., U.S. Air Force)

Overview

The Low SWAP-C Nighttime Landing Hazard Detection System (LITTLE OWL) project will test a photogrammetry device that uses the motion of the observing platform to produce very long baseline stereoscopic images in lit and unlit conditions. Nighttime suborbital flight tests will simulate a lunar descent, providing an opportunity to demonstrate the technology’s capabilities.

Problem Statement 
Safe landing on the Moon or other celestial objects requires identifying a location free of hazards including uneven surfaces that preclude spacecraft touchdown. Finding those locations in nighttime conditions or permanently dark environments is especially difficult. Current technologies use lasers or radar to develop 3D point clouds that represent the shapes or objects on the surface. These methods require very high power, complex development, and significant size and weight. This new technology addresses those issues by leveraging advanced image processing techniques and graphics processing hardware along with multi-view monocular photogrammetry. The sensing system is low cost and has very low size, weight, and power needs, which enables its use on small spacecraft. It could be used to support assessment of landing sites by a lander or other platform needing to create 3D point clouds of a scene in low lighting conditions, such as in deep craters or at night.

Technology Maturation 
Suborbital flight tests during a nighttime campaign will simulate a lunar descent in areas of the Moon near to permanently shadowed regions on the Moon, demonstrating the technology’s capabilities. After flight testing, researchers will determine the achievable accuracy and timeliness of the 3D map generation from an altitude of 250 to 500 meters. This technology could enable lunar landing or orbital rendezvous capabilities in the future.

Summary of Flight Test
2024-08-29 Our team was able to rapidly and successfully design from scratch, manufacture, and integrate a gimbaled optical payload with software processing, and be prepared for a suborbital flight in less than nine months. The project was definitely challenging and we were able to gather the data we needed to understand the performance of the system. We are excited to apply the lessons-learned from our first suborbital test flight, share what we learned with others, and improve on our LITTLE OWL prototype design and processing architecture. The short duration of the campaign, low budget, and NASA’s minimal project overhead (inperson reviews every 4 months) really helped our team focus and drive to constantly reduce risk and show demonstrable progress throughout the project.

Benefits

A smaller, lighter, low-power, less expensive hazard-detection system for landing in low-light conditions will enable more spacecraft to visit scientifically interesting and resource-rich places on the Moon and other surfaces. This has the potential to benefit NASA missions and the commercial space industry.

Future Customers
• Lunar exploration missions
• Martian landers
• Other exploration spacecraft needing to land in low-light conditions

Overview

Benefits

Overview

Electrochemical biosensors are simple and affordable analytical point-of-care diagnostics tools that can rapidly and cost-effectively detect a broad range of molecular analytes (e.g., glucose). The In-Space Biosensors Batch Coating Using Self-Assembled Monolayers project aims to whether microgravity allows for the creation of better, more uniform, and smoother coatings that could increase the sensitivity and specificity of these electrochemical biosensors. The test will demonstrate an automated batch system the team has developed for sensor coating and fabrication to address challenges of accuracy and reproducibility. 

Problem Statement 
In order to detect proteins, biosensors need a uniform bottom-up manufacturing process that starts with depositing a coating material that creates a self-assembled monolayer (SAM) on top of the bare electrode. This SAM functionalizes the surface of the electrode allowing for further coating with antibodies that will detect the analyte of interest. Current 1 g manufacturing techniques create rough and uneven surfaces within a SAM that can alter a biosensor’s readability, affecting the reliability and reproducibility of blood biomarker detection. 0 g techniques could improve the uniformity and smoothness of this SAM layer and potentially increase the sensitivity and specificity of the sensor, allowing for improved manufacturing of point-of-care diagnostic tools. 

Technology Maturation 
The automated batch system is currently TRL 4. A successful flight will take this system to TRL 6 and will provide data on the hypothesis of the microgravity environment’s benefit for biosensor coating.

Summary of 9/18/2025 flight test
Ecoatoms successfully achieved the automated and simultaneous coating of 215 biosensors in microgravity with the ARES ((Advanced Reinforced Engineering Structure) payload, demonstrating a significant milestone in sensor technology development. The ARES payload was effectively powered and controlled by Ecoatoms' onboard computer, ANIMA, which executed the coating process flawlessly for experiment 1 and provided critical redundancy for experiment 2 within the payload. This last accomplishment was delivered one year ahead of the projected schedule, underscoring the robustness and efficiency of the integrated systems in meeting mission objectives under microgravity conditions.

Benefits

This project aims to address one of the key factors for reliable and reproducible blood biomarkers detection: the uniformity and smoothness of the real-time biosensor’s self-assembled monolayer (SAM). This work aims to improve current 1 g manufacturing techniques, which create rough and uneven surfaces that alter the biosensors’ readability. 0 g techniques could improve the uniformity and smoothness of the SAM layer and potentially increase the sensitivity and specificity of the sensor, allowing for improved manufacturing of “point-of-care” diagnostic tools.

This has the potential to benefit NASA missions, the commercial space industry, other government agencies and industries using low-gravity deposition, and the nation.

Future Customers
- Point-of-care diagnostics manufacturing in low-Earth orbit
- Real-time sensor manufacturing and biomarker detection during long-duration flight

Overview

NASA’s On-Demand Manufacturing of Electronics (ODME) Advanced Toolplate is a key component of the ODME system for in-space manufacturing of flexible, hybrid electronics and sensors for structural and crew monitoring systems. The Advanced Toolplate has swappable, miniaturized toolheads, providing advanced deposition and processing capabilities to enable the in-orbit fabrication of complex electronic devices and sensors. The Advanced Toolplate will also benefit the On-Demand Manufacturing of Metals (ODMM) project for multi-materials 3D printing via a fabrication laboratory (FabLab).

Problem Statement 

Given the costs and logistics associated with maintaining an inventory of electronics and sensors in space, their in-situ, on-demand fabrication is essential for environmental, structural, and crew health monitoring during space station operations as well as future lunar and exploration missions. The Advanced Toolplate offers eight swappable toolheads for 3D printing complex, multilayer flexible electronics. In addition to ODME, this innovation is designed to be used with the ODMM project’s FabLab custom-designed nScrypt multi-material printer, enabling the creation of electronics and metals with a single printer. In addition, because its toolheads can be swapped out, the Advanced Toolplate can be easily updated as new deposition systems become available. During the parabolic flights, the ODME team will test the microgravity functionality of a direct-write extrusion print head, mill, and pick-and-place component.

Technology Maturation 

Relevant environment testing of the Advanced Toolplate on parabolic flights will reduce the risk of introducing the FabLab’s 3D-printing capability on the International Space Station, where a demonstration is expected for 2024–2025. Specifically, microgravity flight testing will allow ODME to evaluate different electronic ink deposition systems and processing methods, advancing the technology readiness level (TRL) to TRL 6 and significantly mitigating operational risk.

Summary of Flight Test
2023-10-16, 2023-11-28, 2024-02-26 During the February 2024 parabolic flight campaign, the ODME Advanced Toolplate team was able to test a new suite of tools for for future use on the ISS to produce or repair electronics. Among the processes successfully proven during this campaign was the ability to fill vias, accurately dispense dielectric material into gaps surrounding and electrical component, mill, dissipate electrostatic charge from offal and collective a portion of the offal into a filter.
2024-08-20 The flight campaign achieved valuable results that concluded the capability of the Sciperio ATS1 machine to perform EHD printing well under a zero-gravity environment. We achieved fine print lines under 100 micrometers using three materials—Silver, PDMS, and ZnO—marking significant progress in the development of EHD-printed random access memory (RAM).

Benefits

In-space 3D printing of flexible, hybrid electronics and sensors will benefit structural and crew monitoring systems. The Advanced Toolplate contains swappable toolheads for versatility of fabrication and easy updating in the future. This has the potential to benefit NASA missions and the commercial space industry. 

Future Customers 

• International Space Station (demonstration expected in 2024–2025) 

• Commercial in-space manufacturing 

• Lunar missions 

• Long-duration NASA or commercial missions

Overview

Benefits

Overview

Benefits

Overview

Benefits

SPARTA will address what was specifically called out in the 2020 LEAG report to: ”understand regolith densities with depth, cohesiveness, grain sizes, slopes, blockiness, association and effects of entrained volatiles.” These measurements are considered “enabling where trafficability is an issue. SPARTA measurements directly address these.

Future Customers
- In situ lunar missions such as NASA’s Commercial Lunar Payload Services
- Data collection for fundamental science
- Ground truthing for NASA’s in situ resource utilization activities

Overview

The Gamma-Ray and AntiMatter Survey (GRAMS) project will use a balloon-borne liquid argon time projection chamber (LArTPC) detector for the first time to attempt gamma-ray observations in the megaelectron volt (MeV) energy range and perform indirect dark matter searches with antinuclei. Leveraging the long-duration and high-altitude environment provided by the balloon, the flight test aims to validate LArTPC capabilities for particle tracking and gamma-ray detection in flight. The technology could significantly improve sensitivity to astrophysical MeV gamma-ray measurements and aid in understanding extreme astrophysical environments with multi-messenger astrophysics. In addition to astrophysical research applications, GRAMS could explore new parameter space for self-annihilating dark matter and evaporating primordial black holes. GRAMS’ low-energy antideuteron and antihelium measurements will have the potential to support background-free dark matter searches, allowing researchers to probe dark matter parameter space extensively.

Problem Statement
The development of a large-scale, high-resolution, medium-energy gamma-ray detector faces a number of challenges. Central to these challenges is the fact that gamma rays with energies of 0.1–20 MeV tend to primarily undergo Compton scattering – the increase in wavelength of x-rays and other electromagnetic rays that have been scattered by electrons. This effect requires detectors with exceptionally high spatial and energy resolution to reconstruct Compton scatterings and subsequently identify the direction of the gamma-ray source. The GRAMS collaboration aims to break through existing technological barriers and overcome this challenge with a LArTPC detector used as a “Compton camera.” The LArTPC technology has been successfully developed for underground dark matter/neutrino experiments over the last two decades. However, it has not yet been designed and optimized to measure gamma rays in the MeV energy range. Given sufficient energy and position resolution, the LArTPC could provide an affordable, scalable, and full-sky-reach solution for a Compton telescope concept. 

Technology Maturation 

Flight tests are expected to help researchers validate the liquid argon handling techniques and LArTPC capabilities of particle tracking and gamma-ray detection in flight. The GRAMS prototype flight tests aim to advance the technology readiness level (TRL) to TRL 5. Researchers intend to use results from the flight tests to move forward with the first GRAMS science flight with an extended observation time.

Benefits

- Scalable: Offers the potential for an affordable full-sky-reach solution for a Compton telescope concept 
- High-performance: Improves sensitivities to astrophysical MeV gamma-ray measurements needed to understand extreme astrophysical environments with multi-messenger astrophysics and antideuterons and antiheliums to search for dark matter indirectly. 

Future Customers
• Astrophysical research in the relatively unexplored MeV gamma-ray energy range
• New dark matter parameter space exploration with antinuclei measurements

Overview

The Draper Multi-Environment Navigator (DMEN)is a vision navigation system consisting of a suite of sensors, circuitry, a computer, and algorithms to process data into a navigation solution for rocket-powered landing systems. The system has successfully completed a high-altitude balloon campaign. This latest suborbital flight campaign plans to advance the instrument to higher altitudes faster velocity and simulated ground hazards under rocket-powered decent.

Problem Statement
While DMEN continues to show promise as a terrain-relative navigation instrument through Flight Opportunities campaigns, there is a second major function of DMEN that remains untested in flight: vision-based hazard detection. Draper has internally funded the creation of monocular vision, shadow-based hazard detection software compatible with the DMEN hardware. Although a camera-in-the-loop image simulator has been developed to test this software, flight data from a rocket-powered lander vehicle would greatly increase confidence in the software and the system TRL.

With this latest suborbital flight campaign, Draper is following on to the first two DMEN campaigns with rocket-powered lander vehicle testing. In addition to adapting the DMEN hardware to the intended flight vehicle, two flights will be planned to reach an altitude of approximately 500 meters and then execute a lunar-landing-like final approach, including flying over a simulated hazard field.

Technology Maturation
DMEN has achieved high TRL (6-7) for both ground and low-altitude operations. The hazard detection technology is currently at TRL 4. This rocket-based flight campaign, including a hazard field, should allow for the collection of data and validation of algorithms in a relevant environment, advancing the system to TRL 5.

Benefits

As exploration reaches further into our solar system, crewed and robotic spacecraft will need to perform entry, descent,and landing (EDL) to complete their missions. The Draper Multi-Environment Navigator (DMEN) Hazard Detection Campaign aims to advance technology toward this goal. DMEN is a vision navigation system consisting of a suite of sensors, circuitry, a computer, and algorithms to process data into a navigation solution. The system has successfully completed a high-altitude balloon campaign. This latest suborbital flight campaign plans to advance the instrument to higher altitudes and faster velocity for continued testing.This would benefit NASA missions, the commercial space industry, and the nation.

Future Customers
•Space exploration missions with a landing component
•NASA’s Commercial Lunar Payload Services missions
•NASA’s Artemis missions

Overview

MSTIC uses both PVD ( Physical Vapor Deposition) and CVD ( Chemical Vapor Deposition ) processes to deposit conductive material on to a wafer substrate for the purpose of generating thin film semiconductor devices. Manufacturing these films in microgravity may lead to more uniform crystal lattices through minimization of fractal formation from columnar growth and thickness uniformity of the films which improve conductivity and power efficiently and ultimately device performance.

Summary of Flight Test
2023-05-08, 2023-10-16, 2023-11-28, 2024-02-26 MSTIC has generated its first successful samples in microgravity, raised the hardware TRL, burned down risk and gained valuable process information that will applied to the flight hardware that is currently on the ISS. The most notable and potentially revolutionary aspect of MSTIC is its ability to leverage the unique conditions of microgravity for manufacturing. The potential for producing films with superior surface structures and the broad range of applications from energy harvesting to advanced sensor technology are particularly groundbreaking. This represents a significant leap in manufacturing and could herald a new era of technological advancements with wide-reaching implications for both space exploration and terrestrial applications.

Benefits

Overview

The Transport Properties of Fluids for Exploration demonstration seeks to measure heat transfer rates in low gravity and to develop accurate thermal diffusivity values of commonly used fluids in space. To do this, researchers have created unique methodologies that require only a non-timed heat pulse and subsequent temperature measurements in the heated fluid. A suborbital flight test will evaluate the hardware’s performance in a space environment using water and liquid metal as the device’s test fluids.

Problem Statement 

Thermal transport of fluids on the Earth, under terrestrial gravity, occurs due to both conductive transport and convective transport. Convective heat transport dominates for most process or situations on earth. Convection leads to more efficient heat transport, thus in a gravitational field heat energy is transferred at a higher rate than by conduction alone. In low-gravity environments, without convection, heat transfer will be lower, and heat transfer rates inferred from terrestrial measurements cannot be assumed to be valid in a low-gravity environment. Thus, it is important, to confidently understand and model the low-gravity process, to have accurate values of the thermal diffusivity of fluids common to low-gravity environments, or for materials that mimic fluids used in low-gravity environments.

Technology Maturation 

The flight test will validate the applicability of the hardware to future low-gravity missions to support exploration initiatives. The hardware will be tested by determining the thermal diffusivity of water and Galinstan. Water is a fluid used in multiple process in spacecraft, while Galinstan represents an analog to possible heat transfer fluids, such a liquid ammonia, or other liquid metals. The current hardware is at TRL 4-5. At the completion of this project, the TRL will be 6-7.

Summary of Flight Test
2022-09-12 This experiment was to use the test fluid, the liquid metal Galinstan, to establish the utility of using lowercost, commercial suborbital vehicles to determine the conductive only component of heat transport in liquids. The experiment was also to verify the applicability of a simple experimental method for these measurements.
2023-12-19 The Transport Properties of Fluids for Exploration measured the thermal diffusivity of the liquid metal galinstan over 180 seconds of low-gravity. Galinstan is used for heat transfer in nuclear reactors and in flexible electronic circuit. Further data analysis will provide numerical values for use in these and other industrial and scientific applications.
 

Benefits

• High fidelity: Collects thermal diffusivity data that is unaffected by convection
• Predictive: Enables development of models for heat transfer processes in space
• Accurate: Produces more accurate heat transfer measurements than ground-based models

Future Customers
• Heat transfer system designs, particularly those that use water or liquid metal

Overview

The Development of Cryogenic Propellant Storage Tank Inner Surface Coating for Elimination of Cryogen Boiloff in Reduced Gravity project will test the effectiveness of several coating candidates to minimize/eliminate propellant boiloff. Propellant boiloff can occur on a storage tank’s internal surface from external heat leakage. The vapor generation due to boiloff can result in propellant loss. Exploring and developing capabilities of various coating materials and surface finish combinations could help in developing technology to minimize/eliminate boiloff and lead to substantial propellant savings. 

Problem Statement 
Various lunar and cislunar space architecture elements require long-term cryogenic propellant storage. A thin film with low thermal conductivity could discourage or prevent boiling nucleation, potentially leading to substantial propellant savings. 

Technology Maturation 
This project aims to provide 0g experimental data and data analysis on the boiling deterrence/prevention characteristics of the candidate coating material and surface finish combinations. The flight tests aim to advance this innovation’s technology readiness level (TRL) to TRL 5 or higher.

Summary of April 15 to May 8, 2025 Flight Test
During the two weeks of April 25 to May 8, 2025, a team of five graduate students led by Professor Jacob Chung from the University of Florida Space Cryogenic Propellant Thermal-Fluid Management Laboratory completed a reduced gravity parabolic flight campaign on board Zero Gravity Corporation’s G-Force One Boeing 727 aircraft. The team successfully used coating materials, performed the reduced gravity experiment, and collected reduced gravity cryogenic zero-boil-off (ZBO) pool boiling heat transfer data in a simulated propellant storage tank. The team’s experimental system proved viable in extreme temperature changes and maintained integrity in microgravity and high-G forces during the research parabolic flights with ZERO-G Corporation. The data obtained from the reduced gravity experiment will be used to develop the technology for achieving cryogenic propellant storage tank zero-boil-off in space.

In-space cryogenic propellant thermal management will play a vital role in NASA’s return to the Moon and future Mars missions. For this reason, long-term storage of cryogenic propellants in space will be required. Several, if not all, of the NASA lunar architecture elements will require storage and pressurization of cryogenic propellants, specifically the space tug and propellant tanker stages. This project is targeted at addressing the need to minimize and eliminate the propellant boil-off due to boiling in microgravity. As noted in the NASA SSTIP (Strategic Space Technology Investment Plan), storage and transfer of cryogens in space is critical for deep space human exploration, making it one of the six NRC high priorities within the “Launch and In-Space Propulsion” Core Technology Investment.

Benefits

This project will test the effectiveness of several coating candidates to minimize/eliminate propellant boiloff. Propellant boiloff can occur on a storage tank’s internal surface from external heat leakage. The vapor generation due to boiloff can result in propellant loss. Exploring and developing capabilities of the various coating materials and surface finish combinations could help in developing technology to minimize/eliminate boiloff and lead to substantial propellant savings. This has the potential to benefit NASA missions, the commercial space industry, and other government agencies.

Future Customers
Cryogenic propellant storage tank design and fluid management

Overview

The Touch-and-Go (TAG) Guidance System (TGS) for small-body and interplanetary sample collection uses optical sensors (navigation camera, LiDAR) and onboard flight software to estimate a spacecraft’s state relative to its target body in near real-time. TAG performs onboard guidance updates to safely control the vehicle as it approaches the surface, informing the vehicle of surface hazards (e.g., rocks and craters) and hazard avoidance maneuvers.

During these flight tests, TGS will gather images of natural terrain landmarks with its navigation camera and perform range-to-surface LiDAR measurements to estimate the flight test vehicle’s state relative to the ground. The TGS flight software will process measurements in a GPS-enhanced onboard navigation system (GEONS) filter, and the onboard guidance system will plan the maneuvers needed for targeting sample sites.

Problem Statement

To expand NASA’s robotic missions into deep space at distances from Earth that preclude human-in-the-loop intervention, onboard navigation algorithms are needed that can support autonomous planetary landing and TAG sampling from small bodies (e.g., asteroids, comets). This requires onboard rendering (vs. pre-rendered or pre-captured imagery) in order to operate in the dynamic lighting environments and relatively fast rotation rates of these small bodies. There is also a need for onboard terrain-relative navigation (TRN) and hazard avoidance methods that are distinct from, and improve upon, previous visual-only methods. The onboard computer must render images of what the expected terrain will look like to the onboard cameras, which are then compared to actual images for navigation; these computations must be performed rapidly and on the relatively low computational power of the flight avionics.

Technology Maturation

The three flight tests will provide the system-level relevant environment necessary for all sensors to collect real measurements over planetary-analog terrain, simulating the descent a space vehicle would take as it approaches a rocky surface. It is anticipated that TGS will advance from technology readiness level (TRL) 5 to TRL 6.

Benefits

- Rapid calculations: Optical sensors and software measure rapidly changing lighting conditions and dynamics of target small bodies in near real-time.
- Improves landings: Onboard guidance aims to enables safe vehicle control to the surface

Future Customers
• NASA planetary science missions
• Commercial lunar and planetary missions

Overview

The goal of the 5G Array for Lunar Relay Operations – Flight Test (FIGARO-FT) is to advance the TRL of a high-performance, low-cost candidate technology for LunaNet relay nodes that is consistent with the future LTE/ 5G architecture being planned for lunar communications. This flight test is a continuation of prior work funded through the NASA Smallsat Technology Partnership initiative (STP). 

Problem Statement 
5G technology stands to revolutionize terrestrial cellular communications infrastructure. Since 5G spectrum shares common Ka-band frequencies with NASA space communications systems, an opportunity exists to leverage the short timescale development cycles and high volume (and therefore, low cost) production of commercial technologies to create a high-performance data communications network in a low-cost CubeSat form factor that’s capable of serving the lunar surface and orbiting systems. 

Technology Maturation 
The payload will be integrated onto a high-altitude balloon platform to demonstrate relay operations with two unique mobile ground-based users, representative of users on the lunar surface. A minimum flight experiment duration of 8 hours is anticipated to ensure successful generation and acquisition of links. During flight, pointing solutions for the phased array antenna will be calculated from onboard avionics interfaces and user signal locking, with a separate command/control link as backup.

Summary of Flight Test
2024-09-26 The collaborative research work between Antenna and Microwave Laboratory, San Diego State University and NASA Glenn Research Center to design a flat-panel 5G Array for Lunar Relay Operations (FIGARO) started in the year 2020, which resulted in the development of two wideband array architectures. One of these architectures was selected to be integrated as the payload onboard Aerostar International's high-altitude Cyclone balloon system, which was flown to 98,000 ft altitude to test live video streaming and tracking of the payload array by two ground terminals. The balloon was launched from Aerostar International's hangar at Hurley, South Dakota, and the link was established successfully.

Benefits

The 5G Array for Lunar Relay Operations –Flight Test (FIGARO-FT) will advance the TRL of a high performance, low cost candidate technology for LunaNet relay nodes that is consistent with the future LTE/ 5G architecture being planned for lunar communications.

Future Customers
NASA’s LunaNet architecture

Overview

The Reduced-Gravity Laser Welding Experiment to Enable Maturation of Computational Models and Process supports the development of welding in space and on the lunar surface by testing laser welding technology in parabolic flight. Researchers will collect critical process and material data to calibrate and validate computational models of the welding process under variable gravity conditions and in vacuum. Laser welding is a compact and flexible solution for manufacturing, assembly, and repair in space that can support the growing space economy by facilitating the assembly of large structures and providing robust repair methods that enable long-term sustained human presence in space. 

Problem Statement

Welding is used to make approximately 90% of durable goods produced on Earth and is an enabling technology for the Earth-based manufacturing of space flight hardware. Welding and allied technologies such as cutting, surface cleaning, heat treating, and 3D printing are critical for manufacturing, assembly, and repair in space and on the lunar surface. While methods for soldering, brazing, and solidification of metals in low Earth orbit (LEO) have previously been investigated, data on welding in microgravity is lacking. Compact and power-efficient welding and joining processes are essential, especially those capable of working with a variety of metals and alloys. Aluminum alloys, stainless steels, and titanium alloys, widely used in spacecraft, will demand versatile welding capabilities.

Technology Maturation 

Parabolic flight tests will help researchers identify the physical and metallurgical changes that occur when shifting from welding on Earth to the space environment. Welding is a complex physical process that involves extreme temperature gradients and multiple phases of matter over short timescales. This complexity necessitates extensive development cycles to realize robust Earth-based hardware for use in space. Such development is currently not possible in space due to lack of orbital welding platforms. The flight tests aim to advance the technology readiness level (TRL) to TRL 6. 

Summary of August 20, 2024 Flight Test
The team performed the first ever demonstration of high-power fiber laser beam welding under high vacuum and micro- and lunar gravity conditions. In situ temperature metrology and weld pool characterization and ex situ metallurgical characterization are combined to create the first validation dataset of its kind. This dataset will anchor computational models that will enable one-shot critical laser beam welds in space and on the lunar surface. Development of this welding technology will be crucial to manufacturing, assembly, and repair ensuring longterm sustainability between the Earth, Moon, and Mars.
 

Benefits

- Capable: Overcomes launch platform size constraints by supporting in-space welding. 
- Robust: Provides repair methods that enable long-term sustained human presence in LEO, the lunar surface, and beyond. 

Future Customers 
In-space welding will enable In-space Servicing, Assembly and Manufacturing (ISAM) applications including: 
- In-space structures and habitats (e.g. trusses, antennas, solar arrays, sunshades, radiators) 
- Lunar surface infrastructure

Overview

Benefits

Overview

Enable cooperative networks of observations from suborbital platforms that autonomously detect events such as wildfires with severe environmental impacts. This technology demonstration matures a capability for autonomous detection of wildfires. 

Multi-instrument, multi-mission wildfire observing system using high-altitude balloon flights. The system includes a multi-band thermal imager for Fire Radiative Power (FRP) and two in situ smoke sensors. Using a high-bandwidth satellite datalink, the payload can stream FRP imagery and facilitate data-driven forecasting of smoke transport. These observations are highly interoperable with existing satellite measurements and support both active fire and post-fire planning and response.

The thermal imager (developed by Xiomas Technologies and known as TBIRD) is a high performance, low-cost, three-band thermal infrared camera system, suitable for deployment in unmanned airborne systems and CubeSats and capable of mapping thermal features on the surface of the Earth with a high revisit rate and high spatial resolution.

Summary for April 23, 2025 Flight Test
During this stratospheric balloon flight, the collaborative team of Harvard, Xiomas, and NASA-Ames successfully demonstrated an innovative approach to wildfire monitoring that integrates advanced remote sensing with targeted atmospheric measurements. The mission featured an optical particle counter (POPS) integrated via a novel platform-agnostic interface, facilitating seamless instrument deployment across diverse airborne platforms—from balloons to aircraft and potentially satellites. This collaborative effort not only streamlined integration but also enhanced reliability in the harsh stratospheric environment. By working together, the team validated core elements of a proposed multi-platform system in which multi-band thermal imaging could autonomously detect wildfire activity and cue in situ atmospheric instruments to characterize smoke particles at various altitudes. These combined measurements are crucial for improving understanding of how wildfire smoke affects optical corrections for satellite measurements and air quality, especially in light of the repeated, intense wildfire events of recent years. This flight advances technologies that will enhance NASA's ability to monitor, measure, and respond to wildfire events from the stratosphere, paving the way for future collaborative efforts on similar missions.

Benefits

Overview

While commercialization potential for near-Earth asteroids (NEAs) is high, so is the risk of missions to reach them due to poor knowledge of surface behavior and regolith strength. Researchers at Honeybee Robotics are addressing this challenge with their Asteroid Soil Strength Evaluation Tool (ASSET), a simple payload for determining geophysical properties of NEA soil at various densities in microgravity. The technology uses a dual-plunger sealed system and load cell to test regolith resistance to penetration. 

Problem Statement 
Near-Earth asteroids (NEAs) in cislunar space have high potential for commercial activity due due to their low delta-vand abundance of various materials. However, missions to small extraplanetary bodies (including comets) are expensive and engineering intensive. Risk for these missions is high due to poor knowledge of their surface behavior and regolith strength. Soil strength is critical information for any geotechnical design and is a function of two parameters: cohesion and friction angle. Cohesion is normally gravity independent, while friction is gravity dependent (and should be zero if there is no gravity). For asteroid materials (regolith), cohesion is driven by Van der Waal forces and, in turn, can be easily calculated and modeled. However, the friction angle and how it affects bearing capacity and strength of small bodies is very difficult to model or derive from fundamental principles. 

Technology Maturation
This rocket-powered flight campaign aims to address these challenges by helping researchers determine the effect of microgravity on regolith friction angle. This knowledge will help bracket small bodies’ strength, improve scientific understanding of small bodies, and help in future development of optimal sampling and landing approaches.

Summary of Flight Test
2022-09-12 The goal of the ASSET-1 experiment is to observe particle interaction and bulk material compaction within a micro-gravity environment. In conjunction with Coupi Inc., Honeybee Robotics intended to use the collected data to provide empirical data for validation of a simulation model of this phenomena. This information may then be used to further the understanding of interaction with small celestial bodies, such as asteroids or comets.
ASSET-1 was meant to be the first of many subsequent experiments to collect data under a variety of gravity conditions. While the launch did not attain the necessary conditions to enable the execution of the experiment, ASSET-1 was tested multiple times under Earth gravity conditions and should be considered for additional future flight testing opportunties.
2023-12-19 The ASSET-1 experiment, designed and built by Honeybee Robotics, completed its micro-gravity flight campaign on New Shepard. This payload successfully collected data to further understand soil property and particle interaction and may help with interfacing spacecraft to small celestial bodies.
2025-02-04 Asteroid Soil Strength Evaluation Test (ASSET) – The ASSET experiment is designed to help develop an understanding of soil properties and particle interaction within a low- and micro-gravity environments. The device will first compress a simulant to a known density using a compaction stage and then penetrate the simulant while collecting force vs displacement data with a probing stage. The data that was collected will be used to validate and refine granular material behavior simulations, and inform future generations of designs. Honeybee Bubble Excitation Experiment (HBEE) – HBEE will help characterize gas bubble formation and propagation in viscous liquids in lunar gravity. These insights will help better predict how oxygen bubbles will act in regolith /rock that is melted during the in-situ resource utilization (ISRU) process called molten regolith electrolysis (MRE). The data that was collected will be used to inform designs of future ISRU systems.
PUFFER-Oriented Compact Cleaning and Excavation Tool (POCCET) – POCCET is designed to explore granular material interactions with a pneumatic system in lunar gravity conditions. The system will demonstrate non-contact pneumatic trenching by blowing air at a known outlet pressure onto a surface of loose kinetic sand and recording the response. The data collected will expand our understanding of possible pneumatic applications as more mass- and power-efficient alternatives to traditional mechanisms.
Root-Inspired Lunar Anchoring – This payload will demonstrate a low-reaction-force and low-material-displacement approach to anchoring structures to lunar surface regolith.
The experiment will extend, and then retract, a root-inspired inflatable anchoring mechanism in a resettable simulant container under lunar gravity conditions. This lunar anchoring approach has the potential to become a cornerstone architecture of human lunar permanence objectives.

Benefits

While commercialization potential for near-Earth asteroids (NEAs) is high, so is the risk of missions to reach them due to poor knowledge of surface behavior and regolith strength. Researchers at Honeybee Robotics are addressing this challenge with their Asteroid Soil Strength Evaluation Tool (ASSET), a simple payload for determining geophysical properties of NEA soil at various densities in microgravity. The technology uses a dual-plunger sealed system and load cell to test regolith resistance to penetration.This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•NASA mission planning
•Commercial mining and aerospace organizations
•U.S. Geological Survey projects

Overview

Benefits

Overview

This Integrated Acoustic Technology for Boiloff Control, Mass Gauging, and Structural Health Monitoring in Cryogenic Fuel Tanks experiment combines three common mechanisms for monitoring and managing propellant using acoustic fields and ultrasound sensor networks. By combining three technologies that are typically used separately for boiloff control, mass gauging, and structural health monitoring of cryogenic fuel tanks, this innovation dramatically reduces the amount of necessary equipment. Flight tests will evaluate the three subsystems individually as well as their integrated functionality in microgravity.

Problem Statement 
Long-duration space exploration missions require efficient cryogenic propellant storage and management. An important part of maintaining this efficiency is mitigating environmental effects on the propellant state and tank structure, which includes addressing challenges such as boiloff, accurate fluid gauging, and structural damage.

Technology Maturation
Acoustic technology is a proven, highly effective tool for propellant monitoring and management. This flight test will mature each of the three technologiesfor boiloff control, mass gauging, and structural health monitoring independently, which will in turn serve to advance their integrated functionality. The system is expected to reach a TRL of 5.

Benefits

This technology would significantly reduce propellant management costs by combining three critical components for boiloff control, mass gauging, and structural health monitoring into one system. Such a comprehensive system provides a more robust and more accurate means of controlling cryogenic fluid which is crucial for mission longevity and sustainability. This would benefit NASA missions, the commercial space industry, and other government agencies.

Future Customers
•NASA and commercial space exploration missions
•Design of cryogenic fuel management systems

Overview

Benefits

Overview

In-space manufacturing is a key enabling capability for establishing long-duration human presence on the Moon. To support this goal, researchers at West Virginia University are investigating Particle-Based Foam Spraying in Microgravityto combine a cold spray process with 3D printing. The work aims to advance the state of the art of 3D printing in space by strengthening and/or extending the in-service lifetime of preexisting 3D-printed structures to reduce mission costs.

Problem Statement 
With low density and high mechanical strength, ceramic foams have great potential for numerous applications—from radiation shielding to filtration and from photocatalysis to energy storage or heat exchange. Ceramic foam inks can also be combined with direct-write techniques, opening a new route for manufacturing previously unattainable complex, hierarchical, 3D structures of multifunctional materials with no material waste. 

Technology Maturation 
3D direct spraying is a key method for manufacturing parts with controlled properties and to cover large substrates, so researchers plan to study spray deposition of foamed model inks in microgravity. They will be stabilized by solid particles loaded into syringes and then sprayed to coat rigid substrates. Flight testing will enable study of fundamental particle-particle interactions as well as final assembly in microgravity.

Summary of Flight Test
2021-11-16 The West Virginia University Microgravity Research Team flew their nozzle-based microemulsion and cold-spray deposition systems on a parabolic aircraft flight provided by the Zero Gravity Corporation on November 16 and 17, 2021. The microemulsion sprayed formulations were based on TiO2 whereas the cold 3 spray experiment used Cu particles sprayed on aluminum substrates. This was the seventeenth student team from WVU to develop and fly an experiment aboard a microgravity research aircraft. Successful microemulsion printing data were obtained during the flight and are currently being analyzed.
2022-05-16 The West Virginia University Microgravity Research Team flew their nozzle?based microemulsion foam spray and cold?spray Zn particle deposition systems on parabolic aircraft flights provided by the Zero Gravity Corporation on May 16 and 17, 2022. The microemulsion sprayed formulations were based on TiO2, whereas the cold spray experiment used Zn particles sprayed on Mg substrates. This was the eighteenth student team from WVU to develop and fly an experiment aboard a microgravity research aircraft. Successful 4 microemulsion spray deposition data and cold spray deposition were obtained under microgravity conditions during the second flight and are currently being analyzed.

Benefits

In-space manufacturing is a key enabling capability for establishing long-duration human presence on the Moon. To support this goal, researchers at West Virginia University are investigating Particle-Based Foam Spraying in Microgravity to combine a cold spray process with 3D printing. The work aims to advance the state of the art of 3D printing in space by strengthening and/or extending the in-service lifetime of preexisting 3D-printed structures to reduce mission costs. This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Radiation shielding, tool manufacturing, and repair for crewed lunar and planetary missions
•Repair of 3D-printed solar cells, photocatalytic filters, and bio-cell scaffolds

Overview

Benefits

Overview

The Stability of In-Space Cryogenic Systems experiment will study the stability of spacecraft propellant during refueling as it relates to temperature and mechanical disturbances,which are important measurements for preventing flow control failure and equipment damage. Testing on parabolic flights will assess the threshold of heat pulses and vibration at which flow oscillations are triggered. Tests will also evaluate the factors controlling liquid nitrogen flow stability and, if successful, result in a strategy to enhance propellant stability and prevent hydraulic shocks. 

Problem Statement 
The storage and transfer of cryogenic propellants in microgravity is critical for lunar and deep space exploration. Thermal-hydrodynamic instabilities on long-duration missions could make controlling propellant and the propellant transfer process more difficult. More research is needed to determine safety parameters for propellant refueling with heat and mechanical disturbances.

Technology Maturation 
Knowledge gained from parabolic flight tests will advance technology for cryogenic transport operations in space–to which NASA has currently assigned a TRL of 4 –to TRL 6. This demonstration will assess the role of gravity in propellant transport by measuring the contrast in heat and mechanical disturbances between a ground and microgravity environment, supporting the development of propellant stability guidelines.

Summary of Flight Test
2023-05-08, 2023-11-28, & 2024-02-26 Collaborative work of the New Jersey Institute of Technology and Princeton CryoTech teams developed a successful flow system to transport a cryogenic fluid in a low-gravity environment without pumps and high pressure gas cylinders. Results acquired in parabolic flight tests provide critical information for the design of a flow system for refueling of cryogenic propellants in space.

Benefits

This knowledge payload could advance the field of cryogenic storage and transfer overall. In addressing this critical NASA need, this technology will establish guidelines for and reduce the risk of in-space propellant transfer by analyzing the role of gravity in potential propellant disturbances. These guidelines are crucial for sustainable, long-duration space missions as well as ground-based cryogenic management. This would benefit NASA missions and the commercial space industry.

Future Customers
•Long-duration space exploration missions
•Ground-based cryogenic applications

Overview

Benefits

Overview

The Zero-g Slosh Model Technology: Knowledge Payload gathers data to develop accurate prediction models of loads on the propellant tank (e.g., liquid pressure, viscous shear) from non-linear contact line motion. When a spacecraft accelerates, the induced pressure gradient generally dominates capillary effects and slosh behavior is nearly as simple as it is on Earth. This research gathers data on propellant behavior during and after spacecraft movement events in order to develop computer prediction models. The data from this demonstration will develop a simulation technology that could lead to more fuel-efficient designs.

Problem Statement 

Non-linear contact line motion has been known since the 1960s to be able to have a large effect, such as a factor of six, on the fundamental natural frequency (presumably on harmonics too). When acceleration exists for the spacecraft, such as during an orbit-raising burn or a trajectory acceleration or correction burn, the acceleration-induced pressure gradient generally dominates over capillary effects and slosh is nearly as simple as one-g slosh on Earth. Two considerations, one old and one new, create a need for gathering data on the low-g response, such as propellant (or coolant, water, or other liquid in use in a spacecraft) settling after a maneuver or docking event or motion of a robotic servicing vehicle: first, little data exists for this common event in spaceflight and thus few models for computation and design exist, and second, the new trend towards smaller satellites reduces uncertainty from scaling up data from these small fluids payloads to true scale.

Summary of Flight Test
2022-09-12 We have designed, built, and ground-tested an original zero-gravity capillary-dominate fluids slosh experiment to acquire new data for use in developing computer models of non-linear contact line motion in weightlessness. The geometry of the liquid test vessels in the experiment creates a two-dimensional flow field in the build of the liquid mass that permits computation power in modeling to be focused on the contact line region. Such models are important for the design of water management in life support systems, refrigeration loops, and some rocket propellant management or refueling systems.
2023-12-19 This tech maturation payload operated as designed on December 19, 2023 and acquired data from liquid sloshing in the weightlessness of spaceflight, which even 65 years into the space age is an uncommon set of data. All four combinations of liquid properties and wettability of the solid walls of the test vessels produced high-resolution video data of the liquid positioning and motion in zero-gravity. Analysis of the data is underway.

Benefits

• Improves modeling: Liquid response (i.e., slosh) data gathered during flight will facilitate two-dimensional computational modeling
• Enabling: More precise models will improve design and fuel efficiency
• Innovative: Supports green propellant advancements that will impact small satellites and robotic servicing missions 

Future Customers
• New green propellant systems
• Closed-loop life support missions
• Robotic servicing missions
• Agencies needing simulations including NASA and Department of Defense
• Commercial space organizations

Overview

The purpose of the Non-invasive Detection of Liquid Propellant Location During Microgravity Transfer project is to facilitate the transfer and storage of cryogenic and storable propellants in microgravity. The method utilizes piezoelectric sensors adhered to the outside of a propellant tank while acoustic excitation is applied to the tank and the sensors translate the tank’s vibrations into electric voltages. It is expected that the frequency of these signals can be used to establish total liquid volume and that the amplitudes can be used to reconstruct the instantaneous location and motion of the liquid-free surface. 

Problem Statement 
The proposed orbit of the Lunar Gateway is unstable and will require occasional station-keeping, and therefore refueling of its power and propulsion element. Visiting spacecraft and lunar ascent modules will also require refueling in order to realize the sustainable human presence required by the Gateway. This challenge requires both microgravity liquid propellant gauging as well as knowledge of equilibrated liquid surface distributions within tanks. Neither technology currently has a sufficient technology readiness level (TRL) for Gateway infusion. 

Technology Maturation 
Flight tests are expected to help verify sensor operation in a relevant space environment, correlating liquid free surface position and motion with sensor amplitudes. This technology is designed to enable the transfer and storage of cryogenic and storable propellants in microgravity, a key component of the refueling of the power and propulsion element necessary for Lunar Gateway station-keeping. The flight tests aim is to advance this innovation to TRL 6.

Summary of September 18, 2025 Flight Test
The MUD payload experiment seeks to demonstrate the ability to non-invasively determine the location of the liquid-vapor interface in a model propellant tank under microgravity conditions. On the New Shepard P15 flight, the team was able to detect the liquid-vapor interface inside a propellant tank partially filled with propellant simulant.

Summary of March 5, 2024 Flight Test
The Microgravity Ullage Detection experiment is technology demonstration for elements of in-space propellant transfer. Our March parabolic flight campaign provided crucial video data and model calibration data for an upcoming flight test on a suborbital rocket. We also use the parabolic flight program to test procedures, hardware performance in microgravity, and assess our team’s data analysis workflow.

Benefits

The purpose of the Non-invasive Detection of Liquid Propellant Location During Microgravity Transfer project is to facilitate the transfer and storage of cryogenic and storable propellants in microgravity. The method utilizes piezoelectric sensors adhered to the outside of a propellant tank while acoustic excitation is applied to the tank and the sensors translate the tank’s vibrations into electric voltages. It is expected that the frequency of these signals can be used to establish total liquid volume and that the amplitudes can be used to reconstruct the instantaneous location and motion of the liquid-free surface. This has the potential to benefit NASA missions, the commercial space industry, and other government agencies.

Future Customers
- Commercial satellite providers
- Military satellite providers
- Launch services providers
- Commercial and NASA programs developing on-orbit fuel depots

Overview

The Honey Bubble Excitation Experiment for Lunar Molten Regolith Analog Demonstration is a simple system designed to test the physics of transporting granular material into bubbles formed within viscous material. The system uses honey as a viscous simulant for molten regolith and compressed gas for evolved oxygen. The system is designed to improve upon current methods to extract oxygen from regolith, an important oxygen source on the Moon. Its aim is to enable researchers to test extraction methods in partial gravity, using a safe, simple, and cost-effective platform. This has the potential to benefit NASA missions and the commercial space industry. 

Problem Statement 
Regolith is an important oxygen source on the moon. An expected best practice for extracting oxygen from lunar soil is molten regolith electrolysis (MRE), which relies on oxygen bubble generation within molten regolith. However, partial gravity experiments haven’t yet been conducted. Because bubble behavior is significantly different in low gravity, development of a continuous MRE process to recover lunar oxygen requires study of viscous bubbling. This system aims to provide a simple, safe, and cost-effective platform for such study. 

Technology Maturation 
A successful flight test is expected to help researchers validate current data models and obtain additional data to inform new, more robust instrument designs needed for deep space exploration missions. The flight tests aim to advance this innovation’s technology readiness level (TRL) to TRL 5.

Summary of Flight Testing
2025-02-04 and 2025-09-18 Honeybee Bubble Excitation Experiment (HBEE) – HBEE will help characterize gas bubble formation and propagation in viscous liquids in lunar gravity. These insights will help better predict how oxygen bubbles will act in regolith /rock that is melted during the in-situ resource utilization (ISRU) process called molten regolith electrolysis (MRE). The data that was collected will be used to inform designs of future ISRU systems.Summary of Flight Testing
2025-02-04 and 2025-09-18 Honeybee Bubble Excitation Experiment (HBEE) – HBEE will help characterize gas bubble formation and propagation in viscous liquids in lunar gravity. These insights will help better predict how oxygen bubbles will act in regolith /rock that is melted during the in-situ resource utilization (ISRU) process called molten regolith electrolysis (MRE). The data that was collected will be used to inform designs of future ISRU systems.

Benefits

Overview

The primary objective of this flight demonstration on Blue Origin is to develop and test an external environment access payload accommodation facility. The enhancement consists of the JANUS integration platform modified with an aerogel collector system to be mounted on the upper ring of the Propulsion Module (PM).

Problem Statement 
To date, relatively little in situ observations and sampling exist for suborbital space at 80-100 km altitudes despite this being a critical region where the atmosphere (collisional) transitions to space (non-collisional). What little data exists was derived from infrequent and relatively expensive sounding rockets. Once established, this capability will open up a new era of discovery in this region by providing unprecedented insight into suborbital space impacting many Earth based and geoscience missions requiring scientific measurements.

Technology Maturation 
The key test objectives are to successfully mount the payload on the vehicle, successfully fly and retrieve it, and record and analyze (for suitability of external access location) temperature, vibration/acceleration and particle distribution.

Benefits

• Utility: Works across multiple science and engineering measurements
• Innovative: Allows technologies to be demonstrated in an in-space environment
• Efficient: OTS components allow for low cost 

Future Customers 
Instrument development/testing and technology demonstration programs supporting Earth based missions but also all planetary missions and commercial ventures where this environment is at least partially applicable. Virtually any mission or commercial application that requires external access at 100 km altitudes or below will be enabled.

Overview

Spyder’s high-efficiency upper-stage solid rocket motors are designed to increase performance and support a bigger rocket, enabling heavier payloads to go higher and faster. Compared to the company’s SpaceLoft sounding rocket, which can carry a 60-pound payload to altitudes of 100-120 km (about 70 miles high) with 3 minutes of microgravity, Spyder can carry 400 pounds with increased diameters while providing the same amount of microgravity time.

Problem Statement 
UP Aerospace developed the Spyder hypersonic launch system as a low-cost vehicle to enable enhanced suborbital missions and planetary re-entry test environments. Spyder was designed to support hypersonic missions reaching speeds of Mach 10. 

Technology Maturation 
As UP Aerospace continues development of its new sounding rocket, Spyder’s next mission will integrate guidance and control systems. Future Spyder developments include a maximum performance booster motor and multiple upper-stage variants capable of achieving altitudes approaching 300 km to support a wide variety of hypersonic mission objectives.

Summary of June 13, 2025, Flight Test
Spyder’s maiden flight took place on June 13, 2025, at White Sands Missile Range, which provided the photo above. This flight test was to advance re-entry capsules by enabling evaluation of stability, control, and thermal management systems during hypersonic flight. During the flight, Spyder reached the hypersonic speed threshold and successfully deployed the Los Alamos National Laboratory’s payload test vehicle.

Benefits

Overview

The Spaceflight Testing of FEMTA Micropropulsion System for Interplanetary Smallsat project supports the development of a film-evaporation MEMS tunable array, or FEMTA. FEMTA is a non-toxic micropropulsion alternative for precision attitude control for small spacecraft missions. With a mass and thrust-to-power ratio significantly below current industry models, the technology uses deionized water as propellant and leverages surface tension to produce highly tunable thrust. This suborbital flight testing will demonstrate in-space operation of the FEMTA thruster with the vapor-pressure driven propellant management system.

Problem Statement 

FEMTA utilizes microscale effects in fluid surface tension and advanced MEMS microfabrication to achieve a highly tunable micropropulsion at a thrust-to-power ratio of 200 µN/W using pure water as propellant. Technical objectives of flight testing include (i) develop a spaceflight rated micropropulsion module; (ii) prove the operability of the propulsion module in spaceflight operating conditions (iii) verify the integrity of the FEMTA thruster under spaceflight loading conditions. 

Technology Maturation 

The flight testing will be carried out on New Shepard Launch Vehicle in an external payload locker exposed to vacuum. During ascent and while the ambient pressure is less than 10 kPa, the zero-g tank will vent to equalize with the environment. Once in zero-g, a valve will open to allow propellant to flow from the propellant tanks to a collection chamber. The FEMTAs will be powered during this time to simulated operation.

Summary of Flight Test
2025-02-04 The Film Evaporation MEMS Tunable Array (FEMTA) is a microthruster that uses liquid water as propellant for attitude control of small satellites. The FEMTA suborbital flight experiment served as a testbed for evaluating the FEMTA thruster and a vapor-pressure-driven propellant tank in microgravity. The mission was successful in gathering valuable operational data, which will be used as a benchmark for validation of simulations and ground testing of the zero-G propellant tank and FEMTA thruster. The FEMTA Suborbital Experiment was the first demonstration of FEMTA system components in a space environment, advancing the technology from TRL-4 to TRL-6.

Benefits

Overview

The Reduced Gravity Experiments to Measure Cryogenic Two-Phase Heat Transfer Coefficients for Future In-Space Transfer Systems will develop highly accurate models for the prediction of flow boiling rates. Specifically, the demonstration’s objective is to obtain the first microgravity steady state cryogenic heat transfer coefficient (HTC) data. It will also measure HTC during parabolic flight as a function of gravity level, mass flux, and other geometrical and flow parameters.Data collected will inform new steady state HTC models for microgravity that improve predictive capabilities for in-space propellant transfer systems. 

Problem Statement 
Highly accurate flow boiling models are required to predict a spacecraft’s propellant consumption and determine the maximum allowable heating rates of the fluid. Currently, no cryogenic flow boiling data exists in the microgravity steady state.

Technology Maturation 
The cryogenic steady state flow boiling data collected will be used to develop new heat transfer coefficient correlations. The data will improve the technology’s predictive capabilities, bringing it to TRL 5.

Summary of Flight Test
2022-06-27 Our test rig is undoubtedly a new national asset, capable of providing critically needed cryogenic heat transfer data in microgravity, which are crucial for design and performance analysis of important NASA space applications such as Low Earth Orbit (LEO) fuel depot and Nuclear Thermal Propulsion. Another dual-use benefit of our work is better understanding of flow boiling in tubes, through which PU-BTPFL investigators successful achieved electric vehicle ultra-fast charging in less than 5 minutes, a world record that eclipses all advanced charging technologies in use today.
2022-11-02 Purdue University Boiling and Two-Phase Flow Laboratory (PU- BTPFL) and NASA Glenn successfully operated cryogenic flow boiling experiments in parabolic flight, acquiring nucleate boiling datapoints and three full boiling curves comprised of 420 steady state heat transfer datapoints along with video recordings of flow regime transitions and interfacial behavior in microgravity. Cryogenic steady-state flow boiling has never been measured in microgravity before, giving this flight campaign extraordinary novelty and ability to acquire two phase flow physics and heat transfer knowhow essential to NASA’s near-future space applications such as Low Earth Orbit (LEO) fuel depot and Nuclear Thermal Propulsion. Results from this project will optimize the design factors of space fuel transfer system by providing accurate understanding of propellant’s two-phase flow and heat transfer behaviors. Ultimately, the enhanced design of fuel transfer system will economize the entire process of space missions. Another dual-use benefit of our work is better understanding of flow boiling in tubes, through which PU-BTPFL investigators successful achieved electric vehicle ultra-fast charging in less than 5 minutes, a world record that eclipses all advanced charging technologies in use today.
2023-12-04 & 2024-03-05 Purdue's BTPFL and NASA Glenn have successfully conducted groundbreaking cryogenic flow boiling experiments during parabolic flights, collecting crucial heat transfer data points under Lunar, Martian, and Microgravity conditions. This pioneering effort marks the first-ever steady-state testing of cryogenic flow boiling in such extreme gravitational environments, providing unprecedented insights into cryogenic two-phase heat transfer and flow physics. The results of this experiment hold immense value for NASA's forthcoming space architectures, including LEO fuel depots and Nuclear Thermal Propulsion technology. By optimizing the design factors of space fuel transfer systems, based on accurate understanding of cryogenic propellant's two-phase flow and heat transfer behaviors, this research promises to significantly enhance mission efficiency and economize space exploration endeavors. Additionally, the project's findings contribute to a better understanding of flow boiling in tubes, paving the way for breakthroughs such as electric vehicle ultra-fast charging, achieved in less than 5 minutes, setting a new world record.

Benefits

Highly accurate, data-anchored models for cryogenic flow boiling rates can be used to design and analyze in-space propellant transfer systems. Improved propellant system models reduce unnecessary propellant costs and load and also optimize system efficiency.This would benefit NASA missions and the commercial space industry.

Future Customers
•NASA missions like Artemis, particularly for lunar and Martian ascent and descent stages
•In-space cryogenic fuel depots
•Nuclear thermal propulsion systems
•In-space commercial transfer systems

Overview

The evaluation of Computed Axial Lithography (CAL) for rapid, Volumetric Additive Manufacturing (VAM) under low-gravity conditions experiment will test a new additive manufacturing technique that enables contactless printing of biomaterials and engineering resin using the principles of computed tomography. The objective for a parabolic flight test is to successfully print both biomaterial and engineering components in the same machine during microgravity conditions. The data from this flight test – including fluid flow velocity refractive index and printing accuracy – will demonstrate the technique’s scalability.

Problem Statement 
Additive manufacturing in space allows astronauts to efficiently build or repair needed items during a mission without having had to bring those items with them from Earth. Some additive manufacturing techniques can even be used to fabricate parts of human organs, which could be critical for a crew member with organ damage on a long-duration mission.This technology could improve current space-based bioprinting techniques, which have the potential to alter cell growth or are not readily adaptable with a wide variety of materials. 

Technology Maturation 
Parabolic flight tests will explore the effects of reduced gravity on the technology’s sedimentation, resin flows, print fidelity, and degree of conversion, with a particular focus on low-viscosity resins that are more challenging to print under normal gravity conditions.Overall, testing in microgravity aims to mature CAL to TRL 6. Doing so will advance its scalability, modularity, and versatility in printing both biomaterial and engineering components in the same machine.

Summary of Flight Test
2022-05-09 Our UC-Berkeley group successfully managed to manufacture over 120 3D printed parts in a microgravity environment. Some parts took as little as 10 seconds to create, with a max time of 24 seconds. Not only did this process work in a microgravity environment, but early evidence shows that it functioned better than in a traditional gravity effected environment. This technology could be used to print O-rings for sealing, cell tissue for medical treatment, repair broken items by conjoining them, on top of manufacturing many traditional mechanical tools and parts.
2022-11-15 This experiment showed in greater depth the possibilities of what Computed Axial Lithography (CAL) in microgravity can do, from printing higher quality parts, to becoming a popular research platform for the field.
Additionally a new test was conducted that demonstrated the post processing of parts in a microgravity environment.
2024-06-08 SpaceCAL has successfully printed and post-processed multiple parts in space! It fully validates the technology for a spaceflight hardware environment.

Benefits

This user-friendly, highly efficient additive manufacturing technique demonstrates the potential to significantly advance in-space 3D printing capabilities as well as in situ resource utilization.Computed axial lithography could provide critical life support for astronauts through bioprinting organ and could also fabricate vital mechanical components to perform spacecraft repairs. This would benefit NASA missions, the commercial space industry, and the nation.

Future Customers
- Producing flexible components like gaskets and seals
- Tissue modeling research
- Bioprinting human organs
- Printing dental components

Overview

The Investigation of Non-condensable and Autogenous Unsettled Cryogenic Pressurization Schemes in Reduced Gravity will demonstrate the pressure control capability of a cryogenic liquid storage tank in reduced gravity. It will examine pressurization directly to the ullage (the top of the liquid’s surface) as well a ssubsurface pressurization. Over three parabolic flights, researchers will investigate the performance of both a non-condensable and autogenous gas in these two schemes. This data is crucial for predicting pressure control capabilities of cryogenic liquid storage tanks.

Problem Statement
Cryogenic tank pressurization is an important architectural element of a future lunar base. Currently, the effect of reduced gravity on pressurant consumption and pressure rise rate is not firmly known. This data is necessary to compare direct and subsurface pressurization schemes with both non-condensable and autogenous gases.

Technology Maturation
Parabolic flight tests will acquire the data needed to develop and validate reduced gravity cryogenic pressurization models, which can improve the design of propulsion and cryogenic transfer systems. Specifically, this demonstration will advance the technology’s readiness for unsettled helium and subsurface pressurization, which are currently at TRL 4 and 5 respectively.

Benefits

Quantifying differences in pressurization performance across different schemes is crucial for optimal, long-term design of cryogenic liquid storage tanks in reduced gravity. This demonstration would collect the data necessary to improve thermodynamic predictions as well as model tank pressurization and boiloff rates. This would benefit NASA missions and the commercial space industry.

Future Customers
•Nuclear thermal propulsion systems
•In-space fuel depots
•Liquefaction systems on the Moon and Mars

Overview

Benefits

No details available.

Overview

Flight testing of the Dust In-situ Manipulation System (DIMS) aims to determine the system’s ability to create and control clouds of dust in microgravity. This technology builds on previous testing to develop an orbital platform for the scientific investigation of dust particles, which is crucial to understanding the environments of planetary bodies. DIMS will create a 3D image of a dust cloud using high-speed cameras from two different angles. It is designed to overcome current limitations related to the levitation of dust clouds in microgravity including size sorting, preferential particle orientation, hardware constraints, and residual accelerations.

Problem Statement 
The study of dust particles in the universe is relevant to numerous fields of research, including astronomy, planetary and atmospheric sciences. In particular, the levitation of dust clouds, for the study of their evolution or interaction with light, is crucial to the understanding of many environments in space (protoplanetary disks, interstellar medium, etc.). However, the challenges of levitating dust clouds in 1g include size sorting due to gravity and preferential particle orientation due to the levitating medium. Cloud levitation in microgravity is also limited by hardware constraints (cell walls) and residual accelerations of the flight platform. The Dust In-situ Manipulation System (DIMS) technology builds on past experiments in order to offer a flexible, long-term microgravity platform for future dust experiments.

Technology Maturation 
DIMS will allow for the observation of an undisturbed (no physical contact between grains and test cell walls) dust cloud for several minutes (no cloud shifting), which has never been demonstrated yet. The objective of the test flight with Blue Origin is the demonstration of DIMS functionality and operation under several minutes of microgravity.

Benefits

• Innovative: Creates a cloud of dust in micro-g for study
• Focused: Allows study of dust behavior in micro-g
• Risk-reducing: Technology development for surface systems will rely on data generated by this research

Future Customers
• Solar system exploration and utilization programs for NASA and the commercial space industry
• Research in astrophysics, astrobiology, chemistry, planetary sciences, and atmospheric sciences 

 

Overview

NASA’s space exploration plans are increasing the need for more detailed understanding of the behavior of dust and regolith on the surfaces of planetary bodies, including how those surfaces respond to disturbances and the subsequent effect on reduced-gravity operations. The University of Central Florida’s Strata-2P: Characterizing Sensor-Regolith Interactions in Reduced Gravityexperiment will enable testing of technologies for investigating the formation and interaction of small particles and layered structures in low-gravity environments to inform robotic and human in-situ exploration.

Problem Statement 
NASA’s planned lunar and planetary missions are driving the rapidly increasing need for a more detailed understanding of the behavior of dust and regolith on the surfaces of small, airless bodies, how those surfaces respond to disturbances, and what effects these environments will have on reduced-gravity operations. Strata-2P builds off of previously flown International Space Station and suborbital flight experiments and complements an ongoing station experiment. With successful testing, its technologies could be leveraged for detailed investigations into the formation and interaction of small particles and layered structures in low-gravity environments, informing robotic and human in-situ exploration activities. 

Technology Maturation 
Testing Strata-2P on a parabolic flight is expected to advance the TRL by enabling evaluation of the performance of the mechanical devices in variable-gravity environments and comparing to performance in ground-based experiments. In order to meet current and long-term technological and scientific goals, researchers will characterize measurements of regolith penetration and flow with in-situ measurements.

Summary of Flight Test
2021-12-07 The Strata-2P experiment builds from previously flown projects in a family of experiments that explore regolith interactions at variable gravity. The experiment hardware has down been demonstrated to be versatile to be used across parabolic, suborbital, and ISS flights. This flight campaign demonstrated a new use with additional sensors and tool testing, focused on tools of use for characterizing geotechnical properties in simulated lunar regolith. Initial sensor results will be used to advance designs for lunar regolith probe suites for use on rovers and landers. The flights demonstrated unique challenges to operating some mechanisms in the variable gravity environment with the fine regolith simulant, which is pertinent for future operations in the dusty lunar environment.
2023-05-08, 2023-12-04, 2024-04-15 The Strata-2P experiment (UCF/SWRI) is designed to explore the behavior of lunar regolith simulants in varied reduced gravity environment, specifically under different compaction/porosity conditions. Sensors embedded in the regolith measured thermal and electrical conductivity throughout the flight, under primarily lunar and martian gravity-levels. Significant advancements were made on a penetrometer subsystem, capable of measuring the bearing strength and sheer stresses in the upper-most layers of lunar regolith. This system achieved a successful flight demonstration abord the Zero-G reduced-gravity aircraft, demonstrating repeated operations in several gravity levels without jamming. Our automated

Benefits

NASA’s space exploration plans are increasing the need for more detailed understanding of the behavior of dust and regolith on the surfaces of planetary bodies, including how those surfaces respond to disturbances and the subsequent effect on reduced-gravity operations. The University of Central Florida’s Strata-2P: Characterizing Sensor-Regolith Interactions in Reduced Gravity experiment will enable testing of technologies for investigating the formation and interaction of small particles and layered structures in low-gravity environments to inform roboticand human in-situ exploration. This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Lunar in-situ resource utilization
•Science missions for characterizing the surface of the Moon, asteroids, and other planetary surfaces

Overview

The Testing a Novel Technology for a Key Material Property Measurement-Application to Advanced Manufacturing in Space project will assess a novel method for manufacturing metals and alloys in microgravity. Specifically, this technique will evaluate electrostatic resonance conditions caused by oscillatory electric fields at two different levels of gravity. This resonance is correlated with interfacial tension and can be used as a method of measurement to predict the efficacy of printing metals and alloys in space. Data collected during parabolic flights will ultimately advance high-temperature interfacial printing systems.

Problem Statement 
An accurate knowledge of surface tension is required for effective additive manufacturing on a lunar base, especially for fabricating metals and alloys. Current state of the art for measuring surface tension is limited in scope and challenging in high-temperature environments. 

Technology Maturation 
Flight tests will evaluate the onset of resonance conditions by employing alternating electrostatic fields across the interface of two liquids and observing instabilities through imaging.The critical voltage difference to create the resonant state–which is strongly influenced by gravity level –is then correlated to the interfacial tension.Flight data will be compared with data from ground testing and predictions from current theoretical models, advancing the system to TRL 5 or 6.

Summary of Flight Test
2021-12-07 A technology using Faraday resonance with electrostatic forcing was successfully tested on the first flight campaign. This technology will be used to determine a key thermophysical property needed for efficient advanced manufacturing in space.
2022-05-16 A technology using Faraday resonance with electrostatic forcing was successfully tested on the first flight campaign. This technology will be used to determine a key thermophysical property needed for efficient advanced manufacturing in space.
2024-08-20 Two technogies using Faraday resonance with electrostatic forcing were successfully tested on the first reflight flight campaign.
The first technology used a liquid metal in contact with an encapsulant. This was the first time that such a system was tested in microgravity and the successful operation of the apparatus was proven. This technology will be used to determine a key thermophysical property needed for efficient advanced manufacturing in space.
The second technology is a novel means of electrostatic resonance in liquids for enhancing heat transfer in microgravity. This campaign was the first set of flights to test this technology.
 

Benefits

Robust capabilities for additive manufacturing in microgravity are crucial for building a lunar base. This precise method for measuring surface tension would advance the ability to reliably print metals and alloys on the Moon. It could also be used for crystal growth and directed energy deposition, making the system versatile and highly innovative. This would benefit NASA missions and the commercial space industry.

Future Customers
•Producing metals and glasses for space-and ground-based applications
•Crystal growth
•In-space manufacturing

Overview

Earth, Moon, and Mars imaging satellites depend on rapid and accurate pointing maneuvers, which can be affected by fluid behavior. In particular, vehicles using liquid propellants require accurate prediction of loads on the propellant tank (from liquid pressure and viscous shear) and the rate of damping of liquid motion. To better understand fluid behavior and its effect on spacecraft pointing, researchers have developed a Spacecraft Pointing Control and Zero-Gravity Slosh Knowledge payload, the data from which will provide unique comparison cases and may help enable highly fuel-efficient designs.

Problem Statement 

Expansion of space commerce requires optimal satellite performance for pointing rapidly and repeatedly for imaging as well as for achieving high fuel efficiency enabled by precise guidance, navigation, and control (GNC) models of the liquid response. The objectives of this experiment are to gather design parameter data for technology development and then to enter it into the NASA Physical Sciences Informatics System.

Technology Maturation 

This technology is currently at TRL 4 and is expected to advance to TRL 5 via testing that aims to acquire damping data in zero-gravity spaceflight. 

This work is a continuation of previous flight testing under T0216.

Summary of Flight Test
2024-06-08 Flight of Purdue’s NASA-sponsored “Rotational Slosh” experiment on Virgin Galactic’s Galactic-07 mission was successful, producing unique new measurements of the sloshing of liquids, such as rocket propellants in propellant tanks, in the weightlessness of spaceflight. Specifally, the slosh created by rotations of spacecraft, such as required for docking maneuvers. This type of measurement is impossible on Earth because capillary effects (wetting of surfaces and surface tension) often dominate liquid positioning and motion in spaceflight.

Benefits

This technology is designed to gather data that may lead to precise GNC models of liquid response and deliver zero-gravity measurements to update existing models, which may enable improved fuel efficiency. This would benefit NASA missions, other government agencies, and the commercial space industry.

Future Customers
• Large and small satellites
• Commercial Earth imaging
• Docking and pointing 

 

Overview

Landing on and leaving the lunar surface requires the control of lunar ejecta – or high-speed particles – that are blown off the surface by rocket-powered landers. Erosion and damage caused by the lander plumes could reduce the scientific value of the landing surface and surrounding area. To address this issue, the Tethered Lander Operation of Ejecta Backscattered Laser Albedo and Sizing Tracker (EjectaBLAST) will deploy a lander-mounted active laser light-scattering system to determine particle size distribution in the energetic dust clouds created by rocket plumes. With this instrument, researchers aim to help solve the outstanding challenge about the transport physics of dust liberated by lunar landings and place constraints that can be used to calibrate NASA’s existing plume-surface interaction (PSI) predictive software. The system determines laser beam propagation decay lengths at multiple wavelengths from images of light scatter, and it determines particle size distribution from those values as a function of position and time.

Problem Statement
Current physics models of soil erosion in supersonic, low-gravity environments require additional, high-quality data to increase their accuracy. Given that lunar dust clouds contain a broad distribution of particle sizes and relative velocities, the spatiotemporal variation is particularly important to comprehensive modeling. Knowledge of the particle size distribution created by landers will be vital to the success of future lunar missions – such as NASA’s Artemis and Gateway missions – for predicting and preventing damage to future vehicles landing on the lunar surface. Lunar lander ejecta can damage surface and orbital assets. The lunar surface can also be compromised from the erosion caused by the landers. Empirical data on ejecta particle size distributions and behavior is needed to inform models that will enable safer lunar landings, which is difficult to achieve with existing imaging technology and bulk detection methods.

Technology Maturation
The tethered flight test on Astrobotic’s Xodiac vertical takeoff vertical landing (VTVL) vehicle will be used to simulate the lunar landing profiles. Landing surfaces will be covered with lunar simulant to reproduce lunar landing conditions and relevant plume effects. Researchers expect to validate the scientific instrument, capture images of laser propagation through a cloud of lunar-simulant dust disturbed by the Xodiac’s engine plume, and mature the data processing algorithms. The flight test aims to advance this innovation’s technology readiness level (TRL) to TRL 6. This work is related to flight testing under T0242.

Benefits

- Safer: Improved models of lunar ejecta particles could enable safer lunar landings and launches.
- Advance state of the art: Data from a unique set of measurements from a relative environment is expected to validate parts of modeling predictions.

Future Customers
- Commercial lunar landers, such as NASA’s Commercial Lunar Payload Services (CLPS) providers
- Planetary science missions

Overview

Benefits

Overview

Human spaceflight to the Moon and beyond will require a wealth of health care-related technologies, potentially including those to aid surgery in the uniquely challenging environment of space. Researchers at Purdue University, in collaboration with the University of Louisville and Orbital Medicine, Inc., are advancing methods for Integrating Microgravity Medical Suction and a Microgravity Surgical Facility. The work combines previously flown hardware—an aqueous immersion surgical system and medical suction device—along with a new component to deliver a combined system prototype for suborbital testing. 

Problem Statement 
Durational human spaceflight carries with it the risk of medical emergencies. Unfortunately, terrestrial surgical systems will not work inspace in the same way they do here on Earth—a fact requiring new space-based innovations to address potentially life-threatening emergencies in zero gravity. In particular, treatment of the pneumothorax and hemothorax may be of particular importance. Surgery in space will require advanced control of liquids (blood and other fluids) as well as separation of blood and air. 

Technology Maturation
Various components included in this work are currently at TRL 4, 5, or 6; the combined system is currently at TRL 4. Successful parabolic flight testing should advance the TRL of the combined system to 6. Follow-on longer duration testing in zero gravitymay be needed. This work is a continuation of previous flight testing under T0049, T0155, andT0162.

Summary of Flight Test
2021-12-07 This first test of the integration of Orbital Medicine’s and Purdue’s passive capillary zero-gravity-blood-air separator and University of Louisville’s proven zero-gravity surgical glovebox and fluid management at the wound has been successful. Two types of wound bleeding were created in simulated wounds and the human-operated surgical tools delivered proper containment of liquids in weightlessness while enabling the surgeon to properly manipulate a variety of tools to test suction capability while in weightlessness.
2022-11-15 This testing in weightlessness furthered our design of zero-gravity surgical tools, facilities, and supporting equipment for future long-duration spaceflight far from Earth. Maintaining control of the blood and serum in weightlessness, aiding the patient, and separating the recovered blood and air, both vital resources in a spacecraft, are all steps towards a complete system. In addition to the actual hand-operated surgical procedures on model wounds, a separate experiment tested the performance of the actual physics for the blood-air separation for a wide range of blood and air mixtures and success was found at all mixture ratios.

Benefits

Human spaceflight to the Moon and beyond will require a wealth of health care-related technologies, potentially including those to aid surgery in the uniquely challenging environment of space. Researchers at Purdue University, in collaboration with the University of Louisville and Orbital Medicine, Inc., are advancing methods for Integrating Microgravity Medical Suction and a Microgravity Surgical Facility. The work combines previously flown hardware—an aqueous immersion surgical system and medical suction device—along with a new component to deliver a combined system prototype for suborbital testing. This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Crewed NASA space exploration missions
•Crewed commercial space exploration mission

Overview

The CubeSounder: Flying a Novel 3D Weather Imaging Sensor on a High-Altitude Balloon demonstration will mature a low SWaP-C (size, weight, and power-cost) microwave sounding technology to improve weather forecasting.Through two flights on a high-altitude balloon from World View Enterprises, this novel millimeter-wave filter bank technology will collect three-dimensional images of atmospheric temperature and humidity. Data collected during the flights will be used to validate performance at high-altitudes and ultimately address limitations of current mixer sensors.

Problem Statement 
Weather forecasting requires consistent collection of global temperature and humidity data. Current weather satellite sensors rely on high-SWaP-C components that are difficult to replace. CubeSounder allows for state-of-the-art atmospheric sounding capabilities to be integrated into CubeSats, which would allow for significant improvements in weather forecasting accuracy, as well as the more efficient deployment of weather sensing technology.

Technology Maturation 
Maturing this low-SWAP-C technology will fill an important weather forecasting need as many current U.S. weather satellites reach the end of their service lives. The CubeSounder high-altitude balloon flight will advance sensor capabilities that are lower cost, provide more spectral channels, and a higher level of stability. Having already demonstrated functionality in a lab setting, flight testing will advance the TRL of the millimeter-wave filter bank technology from TRL 4 to 6.

Summary of Flight Test
2021-10-06 The NASA-supported CubeSounder mission just completed its first test flight of a novel weather imaging payload. On the morning of October 6th, 2021, World View Enterprises launched the CubeSounder payload along with several other payloads on their Stratollite vehicle on a high-altitude balloon from their launch pad in Tucson, Arizona. After a successful ascent the flight ended later that day. This was shorter than the expected flight duration, but the vehicle landed successfully, and the payload has been recovered to the World View facility in Tucson. The CubeSounder team hopes to retrieve the data stored on the recovered payload to support preparations already underway to enhance the payload for a second test flight in 2022. Each test flight is a key step on the path towards commercializing the CubeSounder technology.
2022-04-08 The NASA-supported CubeSounder mission just completed a test flight of a novel weather imaging payload. On the morning of April 9th, 2022, World View Enterprises launched the CubeSounder payload along with other payloads on their Stratollite vehicle on a high-altitude balloon from their launch pad in Tucson, Arizona. The flight lasted over 100 hours on a flight path that traversed several states before terminating in Nebraska. Despite some damage to the payload due to a challenging launch and landing, data taken in flight shows promising sensor performance. We are continuing to analyze the flight data to prepare for our next test flight with an improved payload. Each test flight is a key step on the path towards commercializing CubeSounder weather imaging technology.
2023-08-16 The NASA-supported CubeSounder mission just completed its third test flight of a novel weather imaging payload. On the morning of August 16th, 2023, World View Enterprises launched the CubeSounder payload along with other payloads on their Stratollite vehicle on a high-altitude balloon from their launch pad in Page, Arizona. The flight unfortunately was terminated early after a few hours to safely avoid restricted airspace. Despite this setback, data taken in flight shows promising sensor performance. We are continuing to analyze the flight data to prepare for our next test flight which will hopefully achieve a long 30+ day duration. Each test flight is a key step on the path towards commercializing CubeSounder weather imaging technology.
2024-08-31 The NASA-supported CubeSounder mission just completed its fourth test flight of a novel weather imaging payload. On the morning of August 31st, 2024, World View Enterprises launched the CubeSounder payload along with other payloads on their Stratollite vehicle on a high-altitude balloon from their launch pad in Page, Arizona. The launch was successful and the flight is currently ongoing. We hope the rest of the nominally 30- day flight continues to go well, and we look forward to recovering and analyzing the data stored in our payload at the end of flight. Each test flight is a key step towards commercialing CubeSounder weather imaging technology.

Benefits

The CubeSounder system has the potential to significantly improve global weather forecasting accuracy by integrating state-of-the-art atmospheric sounding sensors into CubeSats. It leverages components that are low cost, weight, and power. This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Commercial Earth observation satellites
•Other flight-based environmental monitoring applications

Overview

The Electrophysiology Recording of Neuronal Networks During Suborbital Spaceflight demonstration will assess the ability of an electrophysiological measurement system to monitor live neuronal networks in space. During a Blue Origin suborbital rocket flight, a commercial electrophysiology measurement platform will monitor a culture of neurons and collect data for post flight analysis. The objectives of the experiment are to validate the measurement platform in space and also to analyze the electrophysiology data collected in various gravity conditions.

Problem Statement 
Understanding the effects of spaceflight on human cells and organ systems is crucial to preserving human health through prolonged space travel. Current studies of electrically active cells are limited to an assessment of the whole organism before, during, and after flight. This technology provides the continual monitoring of electrically active human cell cultures through the variable gravity conditions of spaceflight.

Technology Maturation 
This electrophysiology data collection platform is expected to mature to TRL 7 after validation during suborbital flight. The demonstration will also create a preliminary dataset to assess the effects of microgravity on neuronal network function.

Summary of Flight Test
2023-12-19 Imec’s electrophysiology platform, Neuropixels, allows for high density recordings in a compact form factor. Together with our implementation partner, Space Tango, the Neuropixels hardware was combined with a controlled cell culture environment to enable electrical recordings of cells during spaceflight. Our research collaborator at the University of Texas at El Paso provided neuronal cell samples in fluidic devices to study electrically active cells in spaceflight environments.

Benefits

This electrophysiological measurement platform offers a more detailed and robust assessment of human cells in space than current systems. It has the potential for infusion aboard the International Space Station and on various space-based “tissue chip” research missions.This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Neuroscience, cardiology, and electrophysiology research
•Lab-on-a-chip research for organs and tissues
•Stem cell biology and regenerative medicine
•Drug development and drug toxicity screening

Overview

Understanding how yeast adapts to spaceflight may provide a window into more detailed understanding of how other biological organisms—including humans—adapt as well. Researchers at Montana State University are Developing Autonomous Hardware for Use in Suborbital Flight to Evaluate the Impacts of Launch and Landing on Candida Albicans Adaptation to Spaceflight. While these phases of spaceflight may represent fractional experiences in terms of exposure time, the cellular responses are important for a comprehensive understanding of the total biological experience. 

Problem Statement 
Crew member reports and biological sample analyses have made evident that launch, transition to microgravity, and landing have cellular and physiological effects on biological organisms. Researchers can look at the cellular responses of various biological organisms to understand these effects. Candida albicans (an opportunistic pathogenic yeast), for example, can serve as a model system to predict and inform the responses of more complex organisms. Researchers have already demonstrated that C. albicans grown in microgravity responds with differential gene expression, morphologic changes, and increased resistance to an antifungal agent.Research and technology development in this area on commercial suborbital flights requires versatile, reliable, and autonomously functioning hardware and equipment. Once developed, such equipment and hardware can be more readily adapted for use on the Lunar Gateway as well as lunar and Mars expeditions. 

Technology Maturation 
This project involves developing modifications of BioServe Space Technology’s MOBIAS and PLASM automated culture hardware systems to support experiments that subject yeast to appropriately scheduled and autonomously initiated cell activity, analyzing its response to isolated windows of the flight experience—namely, launch, landing, and brief microgravity.

Summary of Flight Test
2023-12-19 This flight allowed development, test, qualification and successful flight and science demonstration of this new spaceflight technology in a high vibration and shock environment.

Benefits

Understanding how yeast adapts to spaceflight may provide a window into more detailed understanding of how other biological organisms—including humans—adapt as well. Researchers at Montana State University are Developing Autonomous Hardware for Use in Suborbital Flight to Evaluate the Impacts of Launch and Landing on Candida Albicans Adaptation to Spaceflight. While these phases of spaceflight may represent fractional experiences in terms of exposure time, the cellular responses are important for a comprehensive understanding of the total biological experience. This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Moon-and Mars-based bioscience research

Overview

Because remote sensing from outside a space vehicle is expected to enable new science measurements, researchers are developing the Integrated Remote Imaging System – Ultraviolet (IRIS-UV) to operate in an external space environment. Mounted on a launch vehicle’s booster, IRIS-UV is designed to sense when the capsule has separated from the propulsion module, power itself on, and then gather spectral data of atmospheric brightness and transmission in UV. Temperature, vibration/acceleration, and contamination data will help researchers determine the suitability of the external access location.

Problem Statement
Currently, remote sensing in the environment outside of air/spacecraft is extremely difficult. Information provided by IRIS-UV would be instrumental to understanding the range of measurements practical from suborbital platforms, including requisite solar elongation for daytime observations from altitude. Measurements and analysis from this demonstration will be used to characterize the amount and distribution of solar illumination scattered by the atmosphere throughout flight.

Technology Maturation
In demonstrating remote sensing from an external payload on a commercial suborbital platform, the technology’s ending TRL is anticipated to be 7.

Benefits

The Integrated Remote Imaging System - UltraViolet (IRIS-UV) operates in external environments at altitudes up to 100 km (i.e., in the absence of ozone). It serves to identify the range of practical measurements from suborbital platforms. This would benefit future NASA missions and the commercial space industry.

Future Customers

• Planetary science and astronomy

• Earth science

• Instrument development

• Mission planning and development

Overview

The in-space assembly of spacecraft and spacecraft subsystems provides a way to improve the aperture size, decrease complex deployment risk (JWST) and assemble systems that exceed the size constraint of launch vehicle payload volume. An area that has been lacking in technology development is the ability to provide multi-functional coatings to spacecraft system components – most importantly, the ability to coat large area telescope mirrors in the vacuum of space. Concepts have been proposed to address the need to grow optical substrates in space via additive manufacturing (AM) ranging from small mosaic tiles to large multi-meter segments. Ultimately, the functionalization of these mirrors to achieve specific wavelength science requirements will have to be deposited on these mirrors in-space. This flight experiment addresses this need by developing a bench scale verification unit that will produce coated mirror coupons specifically Aluminum oxide (Al2O3) during the microgravity portion of the test campaign using the Atomic Layer Deposition (ALD) technique.

Problem Statement 
Atomic Layer Deposition (ALD) is a cost-effective nanoadditive-manufacturing technique that allows for conformal coating of substrates with atomic control in a benign temperature and pressure environment. Using paired precursor gases, thin films can be deposited on flat or textured surfaces ranging from glass, polymers, aerogels, and metals. Through atomic layer control, where single layers of atoms are deposited, fabrication of metal transparent films, nano-laminates, and coatings of nano-channels and pores is achievable. Reaction mechanisms in ALD are normally self-limiting, allowing for atomically accurate control of nanometer (nm) thicknesses. It is the simplicity in the ALD process that allows for a simple reactor design encompassing a reactor volume and electro-pneumatic valves to allow gas pulsing and thus it can be readily tested in-space.

Benefits

Overview

The Microgravity Test of Autonomous Multiple Cycle Farming (AMFC) Systemdemonstration will evaluate theoperation of the system’s components in microgravity. The AMCF incorporatesa growing system, software, and graphical user interface to growplants with little human interventionover multiple cycles. It delivers seeds through a robotic arm and usescapillary forces to supply a hydrating nutrient solution to the seeds. Data will be collected on multiple parabolic flight teststo validate the mechanical system and offer a pathway toward scaling the technology for large-scalein-situ spacefarming.

Problem Statement
As space exploration missions increase in duration, solutions for growing food autonomously and reliably in microgravity become increasingly important. Food growth systems need to also operate without compromising valuable time or energy from other spacecraft functions in order to maximize efficiency.

Technology Maturation
The AMCF has already successfully completed ground testing. Parabolic flight testingwill demonstrate the capabilities of the seed tray, effector, and water delivery system in microgravity. It will also provide data to scale the system for future use on the Moon. The technology will be at TRL 8 after testing.

Benefits

This autonomous plant incubator has the potential to advance large-scale, in-situ space farming. It removes the need for astronauts to tend to plant growth and allows for the growth of multiple crop types. A food growth system with a minimal resource strain could be highly valuable on long-duration missions, extended stays on the Moon, and aboard the International Space Station. This would benefit NASA missions and the commercial space industry.

Future Customers
•Future NASA missions such as the Artemis program
•Extended stays on the Moon and aboard the International Space Station
•Commercial space industry

Overview

Lander design often requires that the lander’s leg placement reside within an area affected by the rocket plume during decent. This can cause the lander’s legs to overheat. Researchers at Purdue University are seeking to monitor this phenomenon with the Lander-Style Vehicle Plume-Structure Heat Transfer Monitoring: Knowledge Payload. Measurements taken on a vertical takeoff and vertical landing (VTVL) vehicle are expected to enable knowledge acquisition, helping researchers understand the heat transferred during different conditions—from high thrust to idle and from centerline thrust to hard-over gimballed operations. 

Problem Statement 
Lunar and planetary landers—especially the newest generation of commercial lunar landers—often have legs placed close to their rocket plume. The heat that radiates from the unsteady plume of an actively gimballed and throttled rocket motor onto the legs of a lander is important to understand and predict in order to inform robust designs for future lander vehicles as well as to understand the risks of rocket plume heating in order to optimize performance and mission success.This is made more difficult on Earth because crosswinds, which are absent on the Moon and nearly absent on Mars, deliver additional and asymmetrical heat transfer from the rocket plume to the lander’s legs. 

Technology Maturation
Measurements taken on a vertical takeoff and vertical landing vehicle aim to help researchers understand heat transfer from high thrust to idle and from centerline thrust to hard-over gimballed operations. The existing payload will be modified to measure additional channels of temperature and to increase the capability to several dozen sensors. Researchers plan to compare measurements from numerous flights and conditions with predictions from modeling in order to inform modeling improvements.

Summary of Flight Test
2023-09-12 This tech maturation program set out to advance instrumentation for plume-impingement heating measurements, which was achieved. Minimum mass is important throughout spaceflight systems and these data and this testing method will aid in minimum-mass spacecraft lander leg design. Because o f changes in the commercial space industry, a shift in testing methods had to be developed and the result is a more affordable and more productive testing method for future work.
2024-10-14 This test concludes the entire campaign, which demonstrated plume-impingement studies designed for lander-type vehicles can shift to more economical and convenient ground-based operations. Because of changes in the commercial space industry, a shift in testing methods had to be developed and the result is a more affordable and more productive testing method for future work.

Benefits

Lunar and planetary landers—especially the newest generation of commercial lunar landers—often have legs placed close to their rocket plume. The heat that radiates from the unsteady plume of an actively gimballed and throttled rocket motor onto the legs of the lander is important to understand and predict in order to inform robust designs for future lander vehicles and understand the risks of rocket plume heating. Researchers at Purdue University are seeking to monitor this phenomenon with the Lander-Style Vehicle Plume-Structure Heat Transfer Monitoring: Knowledge Payload. Measurements taken on a vertical takeoff and vertical landing (VTVL) vehicle from Masten Space Systems are expected to enable knowledge acquisition, helping researchers understand the heat transfer during different conditions—from high thrust to idle and from centerline thrust to hard-over gimballed operations. This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Organizations building crewed or robotic landers for NASA
•Lander vehicle design for Earth-based entry, descent, and landing research

Overview

With the Capturing Human Adaptations in Novel Gravitational Environments in Space (CHANGES) demonstration, researchers will test a suite of sensors and a display technology designed as a non-pharmaceutical countermeasure for space adaptation sickness (SAS). Tasks displayed on a knee-mounted monitor will drive the head and gaze through a series of motions to invoke neuro-vestibular discomfort. Using an elastic headset, the technology provides a visual alert when head motion exceeds preset limits in order to prevent potentially debilitating SAS. Parabolic flight tests will facilitate assessment of the system’s effectiveness in microgravity.

Problem Statement 
Space flight gravitational transitions can occur in minutes, but the human vestibular system can require up to several days to adapt to a new gravitational environment. This delay in vestibular adaptation often results in space adaptation sickness, a potentially debilitating form of motion sickness.Space adaptation sickness could be prevented with a technology that trained the astronaut to minimize head motions.

Technology Maturation 
The CHANGES project aims to mature a non-pharmaceutical remedy for space adaptation sickness consisting of(1) a head-mounted inertial measurement unit to sense head motion, (2) a peripheral-vision display to generate visual alerts when motion limits are being exceeded, and (3) a wearable motion capture system. The headset and test apparatus have already matured to TRL 4 in a laboratory environment. Functionality in various gravitation environments will advance the system to TRL 7.

Summary of Flight Test
2021-12-07, 2022-06-27, 2023-05-08, 2023-10-16, 2024-08-20 Motion sickness in unusual gravitational environments is a common experience that is frequently exacerbated by head motions. In spaceflight, however, symptoms of motion sickness can undermine astronaut performance, posing a threat to mission safety and efficiency. This flight experiment tested a wearable, non-pharmaceutical countermeasure to motion sickness induced by head movements. The objective of the experiment was to induce head movement in a highly unfamiliar gravitational environment - the weightless period of a parabolic flight - and verify that the countermeasure device alerted to motions that might make the user feel sick. This flight campaign confirmed that our device functions as expected in reduced gravity, and has illuminated several next steps for improving and validating future prototypes.

Benefits

The CHANGES system is being tested to demonstrate the capability to prevent astronauts from experiencing space adaptation sickness. This could greatly increase the level of comfort and performance capabilities of space and air travel crews. This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Astronauts and military air crew
•Parabolic flight research
•Patients prone to motion sickness

Overview

Benefits

Overview

The Electrodynamic Regolith Conveyor is designed to move lunar regolith particles with the use of dynamic electric fields rather than conventional rotating or vibrating actuation. The technology concept involves generating electric fields by placing alternating high voltage on electrodes of the conveyor surface. A suborbital flight test aims to enable researchers to assess and advance this dust-tolerant technology for future in situ resource utilization (ISRU) operations on the Moon.

Summary of Flight Test
2025-02-04 The Electrodynamic Regolith Conveyor (ERC) simulated lunar gravity flight experiment, led by Dr.
Aaron Olson of NASA Kennedy Space Center’s Electrostatics & Surface Physics Laboratory, was successful. The experiment demonstrated the conveying of lunar regolith simulant with only the use of electrodynamic forces (no moving parts or mechanical actuation) in vacuum and simulated lunar gravity environment. This technology could be further developed for a variety of conveying, sampling, and dust mitigation applications on the lunar surface.

Benefits

Overview

Regolith Beneficiation for Lunar ISRU (LuSTR) is an integrated system for particle size classification and enrichment of anorthite from lunar regolith simulants (both mare and highland). This hardware includes two subsystems — a magnetic separation subsystem for enrichment of anorthite minerals and an electrostatic sieving system for separation according to particle size. The core technology, lunar regolith beneficiation with magnetic and electrostatic mechanisms, has the potential to impact lunar in-situ metal and oxygen extraction, additive manufacturing, and sintering processes by providing a refined product with low size, weight, power, and cost (SWaP-C) requirements. The innovation of this technology lies in the use of electrodynamical means (i.e., magnetic separation and electrostatic sieving), rather than mechanical (i.e., vibrational) to beneficiate lunar regolith for wider use of lunar in-situ resource utilization (ISRU). 

Problem Statement 

The NASA Technology Strategy Framework lists ISRU as a necessary capability: To develop scalable ISRU production/utilization capabilities, including sustainable commodities on the lunar and Mars surface. To meet this need, ISRU lunar regolith beneficiation (separation and enrichment) is needed to feed the downstream processing steps for producing construction materials based on calcium and aluminum. This technology uses electrodynamical rather than mechanical means to beneficiate lunar regolith for wider ISRU in lunar and Mars habitats. The technology also has the potential to impact lunar in-situ metal and oxygen extraction, additive manufacturing, and sintering processes by providing a refined product with low SWaP-C requirements and thus enable/advance a wide range of downstream ISRU processes. 

Technology Maturation 

Preliminary ground testing under 1g shows promising key performance metrics in terms of size separation and purity (up to 95% by weight of target-sized anorthite), as well as high sensitivity to some configuration settings (e.g., frequency of electrostatic waves for sieving). Testing in lunar gravity (1/6g) is essential to evaluate the key performance of the entire system. Specific measurements from flight testing would include size distribution and composition of collected particles at key stations along the pathway of beneficiation: during initial feed, after magnetic separation, after electrostatic sieving, and during final collection. Flight testing results will also be used to compare with performance metrics under 1 g. These comparisons will help validate and verify modeling and simulation efforts and inform optimization for further design, build, and test efforts. 

Summary of Flight Test
2025-04-29 Missouri S&T researchers tested regolith beneficiation technology in lunar gravity during parabolic flights to advance lunar in-situ resource utilization (ISRU). The integrated hardware achieved size separation of a variety of lunar regolith simulants, paving the way for several downstream ISRU processes such as metal/oxygen extraction through electrolysis.

Benefits

- Robust: Has low SWaP-C and uses minimal mechanical moving parts, resulting in less chance of failure 

- Wide-ranging: Uses combined electrostatic and magnetic means for beneficiation, resulting in wider uses for lunar regolith 

Future Customers 
- Beneficiation of lunar regolith for downstream ISRU processes 
- Lunar in-situ metal and oxygen extraction 
- Additive manufacturing 
- Sintering processes

Overview

Benefits

Overview

Benefits

Overview

The Kentucky Re-entry Universal Payload System (KRUPS) is a small re-entry capsule designed as a technology test bed, with the potential for use in rapid orbit-to-surface delivery for sample return on crewed or robotic missions. Two stratospheric balloon flights will test the material and instrumentation of the capsule’s thermal protection system. The overall objectives of this experiment are to validate the capsule’s powering and release sequence, communication capabilities, and parachute deployment. Successful completion of these objectives could enable future testing on an International Space Station return flight.

Technology Maturation 
The balloon drop tests will validate the on-board electronics and the communication system. They will also validate two new sub-systems: an industrial, scientific and medical (ISM) band radio and a parachute.

Benefits

• Cost-efficient: Offers a lower-cost option for technology testing, small payload delivery, and sample return
• Flexible: Integrates with various flight-qualifying instruments and thermal protection systems
• Resilient: Designed to withstand the harsh environment of re-entry 

Future Customers
• Small payload delivery for NASA and commercial space organizations
• Astronaut sample return during crewed missions
• International Space Station return capsule

Overview

Benefits

Overview

Benefits

Overview

The student-developed Software-Defined Payload Interface (SDPI) leverages prior flight engineering experience from the University of California, Los Angeles’ Electron Losses and Fields Investigation (ELFIN) satellite mission to provide a universal interface solution. The SDPI is powered by a flight-proven system-on-chip field-programmable gate array (FPGA), which offers high flexibility and customization. The technology provides a modular data and power interface for straightforward integration into a wide range of flight vehicles. Most common protocols are supported directly in hardware and customized via software, while more niche protocols can be implemented in FPGA fabric. Derived from technologies previously flown on CubeSats, the SDPI is small, low cost, power efficient, and nonintrusive. A graphical user interface assists in troubleshooting common interface issues. 

Problem Statement 
One of the many complex aspects of spaceflight is the design of interfaces for payloads that fly aboard host vehicles. Space missions often utilize a wide variety of data and power standards, making it rare for a spacecraft bus and an experiment to communicate without significant engineering effort and advanced planning. This process of ensuring a payload can interface appropriately with the flight vehicle is often complex and time consuming, as it typically requires a custom design. These custom interface solutions can introduce data quality issues, incur substantial engineering costs, and are typically not reusable for future missions. It is often important to get payloads to flight test as quickly as possible, but the lack of standardization and interoperability makes this challenging. 

Technology Maturation 
Flight tests aim to validate the SDPI technology and its ability to quickly transition payloads from the bench to integration to support flight tests on multiple vehicles. Additionally, the research team plans to use the SDPI as the interface for other UCLA-built instruments (e.g., highly sensitive magnetic field instruments and particle detectors for monitoring and studying space weather). Further evolutions of SDPI will likely involve multi-payload support (e.g., using a single SDPI to connect multiple payloads to a flight vehicle) and real-time data compression, since data bandwidth is often a limiting factor, especially for small satellites like CubeSats.

Benefits

- Adaptable: Customizable data and power interfaces for integration into diverse vehicles - Flexible: Common and niche (via FPGA fabric) hardware protocols and over-the-air updates - Efficient: Small, low-cost, power-efficient, and nonintrusive 

Future Customers 
- Potential use by NASA for quickly transitioning payloads from the bench to integration with multiple vehicles for flight tests 
- Commercial flight provider payload integration

Overview

Benefits

Overview

Solstar is flying satellite communications transceivers on-board suborbital reusable launch vehicles to test and demonstrate that commercial communications satellite networks can be used to provide internet and voice communications for people and payloads in space. These test flights will enable us to mature and develop our technologies specifically for the space environment. We will test text messaging, location reporting, voice communications, and WiFi payloads. The FOP tests provides an excellent test bed for maturing our technologies in a space environment.

Problem Statement: NASA and commercial developers of orbital and suborbital spacecraft, as well as crew on the ISS, have a constant need to lower the cost and ease of two-way air-to-ground data transmission. Current government-owned networks are expensive and sometimes over-extended. Solstar's new modern communications technologies, based on internet protocol, can provide a lower cost and efficient mode of communication to augment government-owned infrastructure and meet the need for lower cost, efficient communications.

Technology Maturation: The purpose of these flights is to demonstrate and mature voice and data communications services and equipment to be tested in the space environment, above 100km, and at rocket velocities. The FOP spaceflights will provide an ideal test platform to mature our technologies leading to commercial internet services in space. These test flights and subsequent evaluation of the data will enhance the TRL level of internet protocol applications in space.

Summary of Flight Testing
7/18/2018: Solstar successfully demonstrated a second test of its privately funded Wi-Fi service in space, posting the second commercial Tweet from space @SolstarOFFICIAL. The Tweet posted, “What a view of Planet Earth. Brought to you live from Space – this tweet from Solstar’s Space Communicator onboard #NewShepard! Connecting People and Things in Space to Earth #WiFiInSpace”

Solstar’s SC-1x Space Communicator and service was tested onboard Blue Origin’s New Shepard Crew Capsule on a flight funded by NASA’s Flight Opportunities Program (FOP). The spacecraft was launched from Blue Origin’s West Texas Launch Site near Van Horn, Texas, USA.

M. Brian Barnett, Solstar Founder and CEO remarked, “For the second time in 50 days our Space Communicator successfully tested our commercial WiFi service in space. This time our service was tested at a higher altitude at 74.6 miles (120 km). We achieved our other objective of acquiring and maintaining a data link during the vigorous flight conditions of the high-altitude escape test.” 

Commercial space shuttle astronaut and Solstar advisor, Charlie Walker, added, “Communication up to space and back is a vital connection for any activity in space, but the government has had a lock on that until now,” said Walker, now a part-time adviser to Solstar. “This technology is creating industrial infrastructure from the communications standpoint for users on the ground and in space.” 

Dr. Mark Matossian, Solstar’s COO remarked, “If, say, a company puts up a small research satellite, it can only talk with it once it passes over the ground station, which limits the ability to download data. Solstar’s technology will allow access to the satellite at all times, which could be a powerful option for space businesses and researchers that they haven’t had until now.” 

The test flight was an important milestone towards fulfilling Solstar’s goal of securely and conveniently connecting people and things in space to Earth via any internet connected device. “We want to extend our sincere gratitude to Blue Origin’s highly professional team for making our second WiFi in Space test possible today”, Barnett said.
 

Benefits

This technology is intended to provide researchers with a commercial two-way communication service with their payloads in flight, both in suborbital flight and in low earth orbit. 

Future Customers 
- NASA, FAA, DoD, International Space Agencies.
- Commercial spacecraft and spaceliners such as Virgin Galactic, Up Aerospace, World Space, private astronauts/passengers.
- Space researchers and scientists, sRLV payload specialists, science payload developers and operators on the ground communicating with their payloads in space.

Overview

Benefits

Overview

The Microgravity Investigation for Thin-Film Hydroponics project addresses the need for reliable crop production systems for human space exploration. The technology consists of a plant cultivation system that uses thin-film hydroponic techniques via passive capillary processes to support the growth of nutrient-dense aquatic plants and rooted land plants. Suborbital flight testing through NASA’s Flight Opportunities program builds on the team’s previous research on space crops through NASA’s Small Business Technology Transfer (STTR) program. Researchers will evaluate the system’s feasibility for operation in microgravity, including its water and nutrient delivery as well as growth-bed stability.

Problem Statement 

NASAs technology roadmap notes that self-sufficiency of life support systems is crucial for long-duration exploration missions. Regenerative life support will undoubtedly require food production, to recover nutrients and close the carbon loop in a spacecraft human habitat. Hydrophytes (or aquatic plants) have enormous potential for edible biomass production but have been little studied as potential food crops for space applications. During the STTR phase I investigation, water lentils were found to be 100 % edible (with no inedible biomass), nutritious, and exceptionally fast growing. For this reason, water lentils are gaining recognition as a promising new food ingredient for the rapidly growing plant protein market in the United States.

Technology Maturation 

The phase I STTR µg-LilyPond effort included an investigation into water and nutrient transport by passive capillary pressure and water lentil harvesting by rotary sieve for the micro-gravity space environment. The proposed water and nutrient delivery system provides reliable, self-regulating passive transport via capillary pressure and is the first space technology to allow a liquid-air interface for aquatic plants.

Summary of September 18, 2025 Flight Test
Space Lab Technologies took the first step toward growing food on the Moon by launching aquatic plants to space on Blue Origin’s New Shepard NS-35 mission. The uG-LilyPond payload is a specialized floating plant pond that combines both growth and harvesting systems. The growth chamber is an advanced, self-contained unit that grows plants under automated control without the presence of gravity. The mission demonstrated innovative technology for both watering and harvesting aquatic plants under reduced gravity in space. The payload contained Wolffia arrhiza (rootless duckweed), a nutrient rich superfood that is also commonly used in wastewater treatment. This research is crucial for developing future space life support systems and creating a sustainable food source for astronauts on long-duration missions.

Benefits

Space Lab’s space hydroponics system is more sustainable and cost effective compared with other currently available models. Its reusability and autonomous operation make it an advanced and resourceful solution for in-space crop production. The technology aims to benefit NASA missions and the commercial space industry.

Future Customers
• Food system and life support on crewed NASA missions
• Research platform for the International Space Station and Gateway

Overview

Building on 20 years of plant research in both suborbital and orbital environments, researchers are working to refine a biological imaging system for exploration science. The goal: to enable autonomous, high-resolution image data collection for a variety of biological payloads during transitions in gravity levels. The current hardware, while flight proven, lacks autofocus and modern resolution. Improvements will address these shortcomings and also examine new biological sensors for the imager.

Problem Statement 

This flight-proven imaging concept and hardware system fills the need for state-of-the-art images that characterize biological responses to changes in gravity levels during spaceflight. The suborbital flights are designed to provide context to similar deep space imaging systems. This experiment will conduct camera comparisons and a flight test of camera power and control based on triggering from capsule flight data. It is expected to enable finalizing of flight design, operations, and documentation.

Technology Maturation 

The camera and support hardware for the imaging system is designed to autonomously provide high-resolution fluorescent images of any biological specimen on a Petri plate during all phases of suborbital flight. This would facilitate the collection of morphometric, gene expression, and biochemical responses through fluorescent biosensors. The test flights will enable high-fidelity testing of the camera’s systems to inform development for cislunar applications.

Summary of 9/18/2025 Flight Test 
The University of Florida Space Plants Laboratory of Dr. Robert J. Ferl and Dr. Anna-Lisa Paul completed their final suborbital flight study of Biological Imaging in Support of Suborbital Science (FLEX) with the completion of the Blue Origin P-15 flight. The flight allowed for the advancement of technology as well as vital specimen collection for validation studies of plant responses to suborbital spaceflight.

Benefits

This technology is designed to be sufficiently robust and detailed to collect morphometric, gene expression, and biochemical responses through images of any biological specimen at all phases of suborbital flight. This would benefit future NASA missions, the commercial space industry, and other government agencies.

Future Customers
• Government, academic, and commercial biological research
• Biological studies to understand orbital and beyond low-Earth orbit environments

Overview

Efficient mechanical processing (milling) of lunar regolith for life support, propulsion, construction, 3D printing, and more, is a sustainable key enabler of research, exploration, and eventual permanent presence on the Moon. However, the variable particle size of lunar regolith can limit its applicability in certain domains. The Comminution of Regolith Using Milling for Beneficiation of Lunar Extract (CRUMBLE) experiment proposes a solution by investigating the ball and rock milling of regolith simulants under lunar conditions, offering insights into the effects of gravity, vacuum, and milling media. No prior state-of-the-art exists for lunar environment milling. Adapting milling processes for lunar material and the lunar environment is a large step toward efficient multi-ton lunar industry development. CRUMBLE is directly relevant to current technology shortfalls, including in-situ resource utilization (ISRU), advanced manufacturing, and excavation, construction, and outfitting (ECO). 

Problem Statement 

Milling is a long-established technique for Earth-based material processing and a well-studied phenomenon, but it is not well characterized in a lunar environment. Vacuum and reduced gravity may have complex and non-linear relationships with the performance of the milling process; hence, experimental determination is necessary. CRUMBLE aims to provide experimental data points on milling efficiency in the lunar environment and explore the trade-offs in size, weight, and power associated with use of lunar rocks as milling media. 

Technology Maturation 

CRUMBLE is a flight prototype-scale lunar regolith crusher that can maintain a vacuum and has two chambers for variable testing during a series of lunar gravity parabolas. It will fly on two back-to-back lunar gravity parabolic flights. Post-flight analysis will empirically assess milling performance in lunar conditions, comparing steel balls and lunar analog rocks as media. Specifically, data analysis will include laser diffraction with dynamic image analysis for particle size and shape parameters and scanning electron microscope imaging to elucidate the particle size and shape transformations that occur under each test condition. The flight tests aim to advance CRUMBLE’s technology readiness level (TRL) to TRL 6 by testing a mill in a lunar environment to validate analytical models. 

Summary of May 15, 2025 Flight Test 
lnterlune's experiment measured the performance over time of three identical mechanical processing devices for crushing/processing raw lunar regolith simulant into feedstock for in-situ resource utilization (ISRU). The testing included multiple chambers with lunar regolith simulant under vacuum, tested in a lunar gravity environment to assess trade-offs in size, weight, and power required for different performance levels. This is a first of a kind experiment, the results of which can be used for many types of ISRU as well as extraction of helium-3 from lunar regolith. 

Summary of October 28, 2024 Flight Test
Interlune’s experiment measured the performance of a milling system for crushing/processing raw lunar regolith simulant into feedstock for in-situ resource utilization (ISRU). The testing included multiple chambers with lunar regolith simulant under vacuum, tested in a lunar gravity environment to assess trade-offs in size, weight, and power required for different performance levels. This is a first of a kind experiment, the results of which can be used for many types of ISRU as well as extraction of helium-3 from lunar regolith.

Benefits

- Increase ISRU potential: Advance milling technology to process raw lunar materials into useful resources 
- Advance knowledge: Understand effects of vacuum, gravity, and milling media on efficiency 

Future Customers 
- Lunar ISRU applications 
- Advanced manufacturing capabilities – providing ISRU-derived feedstocks

Overview

Increased duration of human presence in space may increase the necessity for space-based surgery. However, no method currently exists to facilitate wound treatment in space while also managing bleeding and preventing fluids and tissue from contaminating the spacecraft. Researchers at the University of Louisville are pursuing Preparations for a Suborbital Evaluation of a Human-Tended Surgical Fluid Management Systemto address this challenge. An in-flight investigator will perform surgical tasks broken down into 10-second segments during periods of microgravity to establish surgical protocols for suborbital flight.

Problem Statement
Complex wound care and surgery during spaceflight is problematic because no method exists to facilitate wound treatment while also managing bleeding and preventing fluids and tissue from contaminating the spacecraft. This wound containment and control system would expand the range of trauma and emergency situations that could be addressed in space, improving crew health and safety, promoting mission success, and perhaps even saving crew member lives.
Previous parabolic flights have advanced this surgical containment and management system to the point where it is ready for evaluation by a spaceflight participant on a suborbital space flight. However, the manual operation of the system and the positioning, securing, and movement of the spaceflight participant inside a suborbital spacecraft require further study. Input from the suborbital flight providers and flight scripting of participant position and surgical tasks will be key activities in preparation for a suborbital flight.

Benefits

Increased duration of human presence in space may increase the necessity for space-based surgery. However, no method currently exists to facilitate wound treatment in space while also managing bleeding and preventing fluids and tissue from contaminating the spacecraft. Researchers at the University of Louisville are pursuing Preparations for a Suborbital Evaluation of a Human-Tended Surgical Fluid Management System to address this challenge. An in-flight investigator will perform surgical tasks broken down into 10-second segments during periods of microgravity to establish surgical protocols for suborbital flight. This would benefit NASA missions, the commercial space industry, other government agencies, and the nation.

Future Customers
•Treatment of medical emergencies in space
•Terrestrial surgical procedures

Overview

Benefits

Overview

Vertically Aligned Carbon Nanotubes (VACNTs) possess numerous remarkable electrical, thermal and optical properties, including that they are the blackest known substance to humankind. This property, as well as their very light thermal mass, makes them ideal absorbers for radiation measurement instruments. Herein we describe a demonstration of VACNT-based radiometer technology to be carried on a commercial suborbital reusable launch vehicle (sRLV). The results of this proposed work and demonstration would raise the technology readiness level (TRL) of this technology from 3 to 7 enabling their proposed use in future NASA and operational Earth science missions.

Problem Statement
VACNT based bolometer radiometers provide just the type of instrument improvements needed to make Earth and Sun observing radiometers sufficiently accurate and low cost to measure’s Earth’s absolute energy balance/imbalance for the first time. This is precisely the measurement that is needed to resolve the climate change debate and enable vastly superior predictions of future change.

Technology Maturation
Integration of the VACNT with a radiometer sensor head and environmental testing will bring them to TRL 5 for this application, and the flight on a sRLV will bring the technology to TRL 6. Successful measurement of the solar incident radiation will bring the VACNT-based radiometer sensor head to TRL 7.

Benefits

Overview

Electrically Driven Liquid Thin Film Boiling phenomena employs two components of the electrohydrodynamic (EHD) force generated by the application of a direct current electric field to a dielectric fluid. This technique enhances two phase heat transfer by providing a constant liquid working fluid source (thus alleviating dry out) through EHD conduction pumping and enhancing vapor departure via the dielectrophoretic force. This suborbital flight test will acquire experimental heat transfer data and confirm the engineering design of critical subsystems of a to-be-launched International Space Station EHD experiment.

Problem Statement 

The most advanced thermal solutions in practice are remote cooling schemes which employ liquid pumps or vapor compressors to pump the working fluid throughout the closed thermal management loop. The application of electric fields to two phase flow permits control of the liquid and vapor phases in a range of gravity fields. Electrically driven liquid film boiling phenomena will lead to a gravity independent, embedded hardware approach which will result in higher temperature heat acquisition, lower mass, size and pumping power consumption than the techniques currently used.

Technology Maturation 

The prototype hardware successfully completed a parabolic aircrat flight campaign (T0208) so is currently at TRL-5. The suborbital flight will provide minutes of micro-gravity environment firmly establishing thermal, electrical and hydrodynamic steady state raising the overall TRL to TRL-6: System Adequacy Validated in Simulated Environment. 

Summary of September 18, 2025 Flight Test 
A novel two-phase heat transport device driven by dielectrophoretic mechanism was flown aboard Blue Origin Shepard rocket. The main objectives of this experiment were as follows, 
1. Provide fundamental understanding of dielectrophoretically enhanced iquid film flow boiling in zero-gravity and multi-gravity settings. 
2. Provide phenomenological foundation for the development of electric field based two-phase thermal management systems leveraging EHD engineering advantages to develop systems of arbitrary mass flow requirements and geometries.

Benefits

Overview

No details available.

Benefits

Overview

The biggest barrier to widespread use of flow boiling in microchannel coolers is the complex nature of convective boiling and two-phase flow, particularly for microgravity applications for which only limited experimental data is available. To date, two-phase microgap coolers cannot be safely employed for spacecraft thermal management due to the lack of acceptable models and correlations for microgravity operation. The goal of the present effort is to characterize the fundamental fluid physics governing two-phase flows in heated miniature and microscale channels, with special emphasis on methods for minimizing the effect of gravity in such flows.

Problem Statement
The increasing functionality and miniaturization of modern and emerging electronic devices has exposed the limitations of the current remote cooling paradigm, which relies on conduction and spreading across multiple interfaces to dissipate waste heat. Such approaches are unable to support continued improvements in device performance. Embedded cooling overcomes this limitation by facilitating direct contact between the heat-generating device and coolant flow. Systems that enable the forced coolant flow to undergo phase change within the embedded channels provide additional benefits, such as higher heat transfer coefficients, lower pumping power, and better temperature uniformity.

Technology Maturation
Experimental validation of gravity-independent behavior would enable spaceflight systems to exploit this powerful thermal management technique and reduce development time and costs through reliance on extensive ground-based testing. Microgap coolers have demonstrated orientation-independent performance. However, varying the evaporator orientation with respect to the gravity vector is not the same as eliminating it, which is why microgravity validation is required.

Summary of 2/4/2025 Flight Test 
The Flow Boiling in Microgap Coolers (FBMC) payload is a compact and rugged test facility capable of providing experimental two-phase flow data for embedded microgap coolers over a range of acceleration levels, flow rates, and heat fluxes. During the P14 flight aboard the Blue Origin New Shepard space vehicle, a 0.4 mm tall microgap cooler was tested and near-saturated flow boiling was achieved over the thermal test chip from before liftoff until after touchdown. Preliminary analysis of the flight data and video of the two-phase flow suggests that the system performance was consistent throughout the lunar gravity coast, high-g re-entry, descent, and landing phases of flight. Additional analysis, including complete processing of all temperature, pressure, flow, and acceleration data, is underway and the results will be used to update the predictive tools developed throughout the technology demonstration effort.

Benefits

Microgap cooler enable the removal of high heat flux over a small area, and will benefit future NASA missions by reducing the size and mass of radiators.

 

Overview

Benefits

Overview

Future robotic and manned missions to the solar system bodies (Moon, Mars, Asteroids, etc.) demand accurate knowledge of ground relative velocity and altitude in order to ensure soft landing at the designated landing site. Some missions may even require landing within a few meters of pre-deployed assets or landing in a small area surrounded by rocks, craters, or steep slopes. To meet these requirements, a Doppler lidar sensor has been developed by NASA-LaRC under the Autonomous Landing and Hazard Avoidance Technology (ALHAT) project. A prototype version of the Doppler lidar has recently been completed and ready for demonstration flight tests. We propose a closed-loop flight demonstration of this Doppler lidar on the Masten suborbital reusable launch vehicle (sRLV).

COBALT Flight Demonstrations Fuse Technologies to Gain Precision Landing Results.
NDL is selected for a flight demonstration on the moon through Commercial Lunar Payload Services.

Problem Statement 
The Doppler lidar will begin its operation during the powered descent phase from an altitude of a few kilometers above the ground. The GN&C system processes the lidar data to improve the vehicle position data from the Inertial Measurement Unit (IMU) that after long travel time from Earth are grossly inaccurate by hundreds of meters. The improved position knowledge along with the lidar precision vector velocity data enables the GN&C system to continuously update the vehicle trajectory toward the landing site. In addition to the precision trajectory determination, the lidar data will play important role in performing the soft landing maneuver.

 

Benefits

This Doppler lidar technology will improve the vehicle position data from the Inertial Measurement Unit (IMU) for more accurate and controlled landings, which will benefit the commercial space industry and future NASA missions.

Future Customers 
This flight demonstration will reduce the risk of using the advanced Doppler lidar technology for future landing missions that may be launched as early as 2017 and certainly for recently-announced Mars rover launch in 2020. The flight demonstration will familiarize the potential users with the Doppler lidar measurements and gain the confidence of mission designers.

Overview

New tools are needed to increase the pace of physical and biological science research while functioning within constraints of the International Space Station and placing minimal demands on astronauts’ time. The Microgravity Lab Assistant (MLA): A Compact Robot for Sample Preparation Onboard the ISS is a compact robot with basic manipulation and machine vision capabilities. The goal of MLA development is to increase the pace of physical and biological science research by supporting sample preparation on the International Space Station and future in-space facilities. The robot is capable of autonomous operation in an unstructured environment using its onboard machine vision, or it can be operated remotely with intuitive control facilitated by its innovative arm geometry. 

Problem Statement 

Aboard the International Space Station, operating volume is severely constrained, and astronaut time is invaluable, limiting the rate at which experiments can be performed. Furthermore, many tasks that are performed frequently in biological and physical laboratory practice can be performed by manipulators smaller than human hands. The situation calls for a compact means of automating biological and physical science experiments. The MLA robot aims to fulfill this need through its capability to perform sample preparation tasks such as liquid handling, powder transfer, and operating lab equipment. Its compactness allows operation within restricted spaces like gloveboxes, where larger robots can’t function. Its size and relatively low cost make it possible for the robot to operate in a homogeneous team with copies of itself or in heterogeneous teams assisting larger robots. Its vacuum compatibility provides extensibility to extravehicular environments.

Technology Maturation 

Parabolic flight tests are expected to help researchers demonstrate liquid acquisition and dispensing, quantify liquid measurement accuracy, and determine maximum pipette withdrawal speed without stray droplet production. The results of the flight tests will be used to optimize control of the MLA, while also having applicability to general efforts to automate fluid handling. Following the flight tests, the MLA is expected to support experiments by performing repetitive preparation in multi-well plates in cell and tissue research, sample acquisition and plant maintenance in botany, and operations with surface elements in physical sciences experiments on the Moon and Mars. The flight tests aim to advance this innovation’s technology readiness level (TRL) to TRL 6. 

Summary of Flight Tests 
May 8, 2025: Sierra Lobo’s Microgravity Lab Assistant demonstrated that it can automate pipette tip changes using its robot arm and specialized end effector. The microgravity experiments identified the conditions that produce reliable and sterile ejections of a pipette tip into a receptacle. Videos demoing these capabilities are being prepared for publication.

Oct-Nov 2024: Sierra Lobo’s Microgravity Lab Assistant demonstrated that it can accurately perform fluid transfer in a zero-gravity environment using its robot arm and specialized end effector. The zero-g experiments identified the conditions that eliminate stray droplet production during fluid transfer. Data on the droplet production dynamics that we observed is being prepared for publication.
 

Benefits

- Research enabling: Automates sample preparation in microgravity Space and time saving: 
- Uses CubeSat heritage hardware to create a compact robot that can perform sample preparation tasks 

Future Customers
- Biological and physical space science researchers 
- Government and commercial in-space servicing, assembly, and manufacturing (ISAM)

Overview

We propose to fly PAMSS on a balloon to demonstrate autonomous operation and trace gas sensing over a large range of pressures, temperatures, and concentrations. Success will advance PAMSS to TRL6. The resulting technology will be available for proposal for planetary mission instrumentation to detect trace species in the atmospheres of Mars, Venus, Titan, or giant planets. 

Papers:
Planetary Atmospheres Minor Species Sensor (PAMSS) (2014) 
Planetary atmospheres minor species sensor balloon flight test to near space (2015)

Problem Statement 

Trace gases can have a large impact on chemical reactions that control larger abundances of important atmospheric gases, such as pollutants and greenhouse gases. Trace gases can indicate for geologic and biologic activities. Knowledge of the presence, concentration, and spatial distribution is important on other planets as well as on Earth. A problem is that current methods of high sensitivity trace gases must interrogate over a range of altitudes and areas to obtain sufficient signal, and they are unable to quantify local concentrations and rapid spatial variations. An opportunity is PAMSS, the first mid-infrared intracavity laser absorption spectrometer. PAMSS achieves tens of kilometer effective optical path lengths in a small, light package with low power requirements. 

Summary of 3/8/2015 Flight Test
A World View balloon reached an altitude of 105,000 feet and loitered above 98,425 feet for nearly an hour and 45 minutes to test University of Central Florida’s (UCF), Orlando, Planetary Atmospheres Minor Species Sensor (PAMSS) experiment. UCF’s PAMSS is the first mid-infrared, intra-cavity laser absorption spectrometer that will be detecting trace gases and sensing over a large range of pressures, temperatures and concentrations while operating autonomously. This technology could be used for future planetary missions as well as the study of the Earth’s atmosphere.

Benefits

The Infrared Intracavity Laser Absorption Spectroscopy (ICLAS) technology will be used to detect trace vapors and gases on planets, which can benefit future NASA missions and other government agencies such as the military. In the event the technology is used for medical diagnostic purposes, it will benefit the entire nation.

Future Customers 
The resulting technology will be available for proposal for planetary mission instrumentation to detect trace species in the atmospheres of Mars, Venus, Titan, or giant planets. In addition the technology can be used for Earth atmosphere sensing as well as for detecting trace gases that may pose a health hazard to workers or a scientific contamination hazard to spacecraft instrumentation. The technology has many other applications, incl. sensing for explosives and medical breath analysis.

Overview

Benefits

Overview

The ARMAS Dual Monitor addresses the need to identify possible radiation sources that may lead to higher rates of melanoma and basal cell carcinoma in air crew members. The experiment builds on findings from six predecessor ARMAS experiments since 2011. Designed to fly on a balloon for 14 to 30 days, the system consists of four radiation detectors for total ionizing dose, gamma rays, linear energy transfer spectroscopy, and tissue equivalent proportional counter quality factor measurements. In addition, researchers hope to test two instruments on an aircraft for validation: total ionizing dose and thermal neutron monitors. 

This work is a continuation of previous flight testing under T0176 and T0221. 

Problem Statement 

This technology is designed to identify sources of radiation that contribute to air crew members’ higher melanoma and basal cell carcinoma rates. Researchers intend to validate this atmospheric radiation monitoring operational system for air traffic and suborbital flight safety.

Technology Maturation 

A successful demonstration of this technology will advance it from TRL 7 to 8. This will be accomplished by the identification of a radiation source that leads to crew shallow-tissue cancers.

Summary of Flight Test
2023-08-16 Space Environment Technologies (SET) successfully launched its ARMAS Dual Monitor payload with total ionizing dose and gamma-ray monitoring instruments on the World View Enterprises GRYPHON29 mission. The launch occurred around 6:30 am local time in Page, Arizona on Wednesday August 16, 2023 and the flight reached an altitude of approximately 21 km.
• Data streamed continuously from the ARMAS payload. SET engineering staff were evaluating the temperatures of the ARMAS system during the flight to understand its data quality when the flight was terminated after approximately 11 hours. Unfavorable winds leading flight safety issues forcing the early flight termination.
• WVE recovered the ARMAS payload intact and without apparent damage on Friday August 18, 2023 from a remote location in the Nevada desert.
• SET looks forward to a re-flight of the ARMAS instrumentation to accomplish its two objectives: i) 24/7 monitoring of the radiation environment in real-time for demonstration a path towards aviation radiation hazard mitigation and ii) understanding the sources of the complex radiation environment at aviation altitudes.
2024-08-31 Space Environment Technologies (SET) successfully launched its ARMAS Dual Monitor payload with total ionizing dose and gamma-ray monitoring instruments on the World View Enterprises ARMAS 2 mission. The launch occurred around 7:52 am local time (14:52 UT) in Page, Arizona on Saturday August 31, 2024, and the flight reached an altitude of approximately 20 km.
• Quality data has streamed continuously from the ARMAS payload’s FM5 instrument since launch via Iridium satellite link and the system passed its first historic milestone: more than 6 24 hours continuous monitoring of the radiation environment relative to human tissue factors above commercial air space. This has not been previously accomplished.
• WVE will recover the ARMAS payload after flight termination that could extend as much as 30 days total and will return the payload to SET.
• With this flight SET is demonstrating real-time, 24/7 COTS-based technology for regional ionizing-radiation monitoring at high altitudes (~20 km) using a long-duration balloon for a minimum of two weeks and up to four weeks. SET is also enabling a better understanding of the dynamic and variable radiation environment affecting aircraft crew and passengers due to all sources by measuring both total ionizing dose and gamma-rays.

Benefits

Featuring instruments precalibrated at the Los Alamos National Laboratory, the Automated Radiation Measurements for Aerospace Safety (ARMAS) dual monitor is designed to help identify potentially dangerous radiation sources. It is comprehensive in that it aims to gather data over a long duration. This would benefit future NASA missions, other government agencies, and the nation. 

Future Customers
• NASA suborbital, International Space Station, and Gateway missions, with real-time data assimilated in the NAIRAS global physics model (Nowcast of Atmospheric Ionizing Radiation for Aviation Safety)
• Department of Commerce, Federal Aviation Administration, and commercial air and space radiation management

Overview

ChipSats, or chip-scale satellites, are an emerging technology designed to package a fully functioning, autonomous spacecraft into an extremely small form factor. Powered via solar cells and containing a magnetometer, gyroscope, antenna, and microcontroller with a UHF transceiver, these 2-gram ChipSats are designed for use in Earth, lunar, and cislunar space applications. If successful, such satellites would enable previously unattainable, and possibly even disruptive, capabilities.

Problem Statement
The low cost, small size, and full autonomy of chip-scale satellites make their anticipated impact far reaching. This demonstration will test ChipSat deployment, recovery, and re-entry survivability.

Technology Maturation
This technology will combine the JANUS integration and monitoring system with a deployer for 100 2-gram ChipSats. Upon validation of the ChipSat operation and re-entry survivability, the TRL will advance from 6 to 7.

Benefits

With a lower launch expense than heavier spacecraft, ChipSats expand the possibility for commercial activity in Earth’s orbit. They also provide utility without interfering with other satellites. This would benefit future NASA missions and the commercial space industry.

Future Customers
• Earth science in difficult-to-explore upper atmosphere regions
• Study of other planets’ and moons’ atmospheres and surfaces
• Commercial suborbital and orbital missions
• Lunar and cislunar missions

Overview

The Green Propellent Zero-G Control Methods project is designed to respond to the goal of NASA and the broader space exploration industry to use more renewable, lower-toxicity propellants to replace standard, high-emission propellants. A human-tended flight test experiment will enable evaluation of renewable energy sources for use as propellants. The test aims to enable research into the non-linear wetting behavior of green propellants on tank walls and vanes. This learning may ultimately help to inform elements of future spacecraft design. 

Problem Statement Non-linear wetting behavior of the liquids on propellant tank walls and vanes is poorly understood, and especially so when it comes to novel green propellants. In particular, modeling stick-slip non-linearity is currently very difficult. Testing in microgravity is expected to inform future spacecraft propellant design. 

Technology Maturation Flight tests, bolstered by extensive and high-quality video, are expected to provide robust detail for post-flight analysis. It is expected that this combination of flight test and video material will give researchers better models to predict the behavior of green propellants and provide necessary understanding for improved design. 

This work is a continuation of previous flight testing under T0128. 

Benefits

Overview

Benefits

Overview

The Suborbital Flight Demonstration of Ionizing Radiation Dosimeters for Use in the Upper Atmosphere will evaluate the ability of several dosimeters to operate continuously and successfully during the entirety of a suborbital rocket-powered flight. Researchers will study whether the vibration during the cruise phase of the flight degrades the dosimeters’ recorded signal quality and obtain ionizing radiation data for use in validating results from atmospheric radiation environment computer models.

Summary of September 18, 2025 Flight Test
The flight test of the Space Tissue Equivalent Dosimeter (SpaceTED) dosimeter aboard Blue Origin's New Shepard suborbital rocket demonstrated that this instrument is able to provide flight dosimetry for space tourism missions. While the New Shepard passed (twice) through the Regener-Pfotzer Maximum where the absorbed dose rate from cosmic radiation in the atmosphere is most intense, the very short duration of these flights translates to an extremely low radiation exposure to any passengers on the mission.

Benefits

Overview

The Plasma Jet Printing for In-Space Manufacturing experiment will test plasma jet printing in a reduced and microgravity environment. Plasma jet printing is a low-cost, versatile, and high-throughput method for printing conductive traces and metal electrodes on non-conventional substrates including flexible materials and nonconformal three-dimensional objects. This test is part of NASA SBIR-funded work to adopt and test the plasma jet printing method for use in space as part of NASA’s On-Demand Manufacturing of Electronics (ODME) project.

Summary of Flight Testing
June 28, 2022: Space Foundry has successfully demonstrated plasma jet printing of conducting copper patterns using a proprietary, environmental friendly, aqueous-based ink that can be used for long-term operation in low earth orbit and also on lunar surface. Copper and silver printing has been successfully demonstrated in both lunar and zero g using Space Foundry’s plasma jet printing.

November 17 and December 15, 2021: The Space Foundry team demonstrated plasma jet printing of silver interdigitated electrodes (IDE) and antenna in microgravity using the Zero G parabolic flight. Controlling the fluid flow and printing using the electromagnetic field and plasma jet, both of which are gravity independent, enables opportunities for printed electronics manufacturing in space. Interdigitated electrodes are widely used in a wide variety of sensors including gas and bio sensors. Printing of antenna pattern will enable a wide variety of applications including communication, inventory control, energy harvesting etc., Plasma jet printing technology was originally developed at NASA Ames Research Center and commercialized by Space Foundry for both terrestrial and space applications. NASA awarded Space Foundry with an SBIR Phase 1 in summer 2018 and since then Space Foundry has received multiple contracts including NASA SBIR Phase II, IIE and III.

Benefits

Overview

Benefits

Overview

Benefits

Overview

Benefits

Overview

The Bronco Ember: Autonomous Nascent Wildfire Detection and Prevention System aims to provide autonomous point-of-interest (POI) detection and tracking of nascent wildfires by potentially improving upon the positional accuracy of current geolocation technologies. This project will combine the use of a short-wave infrared (SWIR) camera with artificial intelligence and machine learning to provide potentially faster and more accurate aerial detection of fires, natural disasters, or other planetary science observations (e.g., methane plumes on Enceladus or ejecta from lunar impacts). 

Problem Statement 
Current geolocation lacks the positional accuracy needed for aerial detection of nascent fires. This geolocation algorithm aims to provide higher precision location determination for nascent wildfire detection. This improved precision could prove beneficial to not only wildfire detection but Earth observation and planetary research missions as well. Improved geolocation positional accuracy could benefit current and future sensing technologies. 

Technology Maturation 
The gimbal mechanism is designed to provide full mobility and continuous tracking of a target within a 180° field of view. This project aims to advance this innovation’s technology readiness level (TRL) to TRL 6 by the time of launch.

Summary of Flight Test
2022-07-08 The Bronco Ember team has successfully conceptualized, designed, manufactured, and deployed a working autonomous nascent wildfire observation system on-board a Raven zero-pressure balloon within an accelerated 10-month period. The system test provided validity to the technology concept, further calibration of sensors and software is planned for continued development. We are very grateful to all the help provided to us by the NASA Flight Opportunities program, the NASA Small Spacecraft Technology program, our university Cal Poly Pomona, and our faculty advisor Professor Tarek Elsharhawy, who without his guidance and sponsorship we would not have achieved these magnificent feats.
2023-05-24 During this flight campaign, the Bronco Ember team was able to validate key performance metrics of the system.
The test flight proved the durability and sustainability of the system over longer duration deployments. The mission also provides valuable data for the tuning and improvement of the AI powered analytics onboard.

Benefits

This project aims to provide autonomous point-of-interest (POI) detection and tracking of nascent wildfires by improving upon the positional accuracy of current geolocation technologies. This project will combine the use of a short-wave infrared (SWIR) camera with artificial intelligence and machine learning to provide potentially faster and more accurate aerial detection of fires, natural disasters, or other planetary science observations (e.g., methane plumes on Enceladus or ejecta from lunar impacts).

This has the potential to benefit NASA missions, the commercial space industry, other government agencies (e.g., forest management and wildfire prevention), Earth science and planetary researchers, and the nation.

Future Customers
- Detection and tracking of wildfires and other terrestrial/planetary observations
- Improved geolocation systems
- Government forest management and wildfire prevention agencies
- Earth science and planetary researchers

Overview

The Proximity Operations Sensors Demonstration project will test a lower-cost alternative to existing sensor concepts for autonomous rendezvous and proximity operations (RPOs). The tests will use an ultra-wideband relative localization system and a vision-based navigation camera to determine the relative position and attitude of two spacecraft at reduced size, weight, power, and cost compared to existing sensors. This could provide a beneficial alternative for more routine operations.

Problem Statement
The national roadmap for returning humans to the Moon requires numerous rendezvous and docking activities for crewed and uncrewed spacecraft. Existing concepts for autonomous RPOs are reliant on large, expensive, heavy, and relatively power-hungry sensors. There is a need for alternative, lower-cost sensor options for RPOs to enhance the ability to carry out complex, multi-vehicle missions in low-Earth orbit and cislunar space.

Technology Maturation
The sensors being tested will collect relative position data between 1) the propulsion module and the crew capsule of Blue Origin’s New Shepard rocket-based system from separation to loss of signal, and 2) the propulsion module and the landing pad during landing. New Shephard’s navigation system will provide truth data for comparison. The flight test aims to advance the proposed low-cost vision-based and ultra-wideband sensors for RPOs from technology readiness level (TRL) 4 to TRL 6.

Benefits

This project will test a lower-cost alternative to existing sensor concepts for autonomous rendezvous and proximity operations (RPOs). The tests will use an ultra-wideband relative localization system and a vision-based navigation camera to determine the relative position and attitude of two spacecraft at reduced size, weight, power, and cost compared to existing sensors. This could provide a beneficial alternative for more routine operations. The national roadmap for returning humans to the Moon requires numerous rendezvous and docking activities for crewed and uncrewed spacecraft. This has the potential to benefit NASA missions, the commercial space industry, and other government agencies.

Future Customers
RPOs for future crewed and uncrewed lunar missions
Routine RPOs requiring lower costs, size, weight, or power consumption

Overview

Project Duneflow aims to enable direct characterization and comparison of regolith simulants under lunar gravity. Researchers plan to quantify gravity-dependent geotechnical properties (e.g., angle of internal friction) of existing and recently developed lunar regolith simulants. Successful testing in lunar gravity during suborbital flight is expected to lead to advancements in manufacturing of geotechnical simulants (i.e., those that better replicate flow behavior). This in turn may enable better testing of excavation and regolith conveyance systems leading to greater effectiveness of the tested technologies.

Summary for 2/4/2025 Flight Test
ICON on behalf of the NASA Space Technology Mission Directorate (STMD) Game Changing Development (GCD) Moon to Mars Planetary Autonomous Construction Technology (MMPACT) project has successfully conducted an experiment into lunar gravity terramechanics. Lunar regolith, lunar regolith simulants, and reference material were subjected to simulated lunar gravity aboard Blue Origin NS-29. The video data recorded will advance the understanding of how these materials respond to conventional approaches to conveyance, tune the gravity component in our present models of powder flow, and shed light on the mechanical viability of our Earthly simulants.

Benefits

Overview

Benefits

Overview

Over the past decade, research has been conducted on the technology of Electromagnetic Formation Flight (EMFF), which uses the local generation of electromagnetic fields by the vehicles of a spacecraft cluster to control their relative degrees of freedom without consuming propellant. RINGS, which stands for Resonant Inductive Near-field Generation System, provides a hardware implementation of EMFF that will operate as a payload on SPHERES, the formation flight test facility onboard the International Space Station (ISS). To maximize productivity during the planned ISS test sessions, we will use a parabolic flight campaign to conduct preliminary formation flight testing and begin the control algorithm refinement process.

Problem Statement
Spacecraft formation flight is a potentially enabling technology for any mission where the desired operational size of the structure exceeds the existing launch shroud capacity. This will very likely be the case for future on-orbit telescopes. Examples include the synthesis of very large apertures by a sparse array of smaller apertures, or the assembly of a large segmented aperture from a highly compact stowed configuration, such as might be done for a larger version of the James Webb Space Telescope.

Technology Maturation
The parabolic flight tests of RINGS will act as a bridge between extensive 2D ground testing and long duration 3D testing onboard the ISS, whereby an array of control approaches can be evaluated in a realistic dynamics environment. Any major control implementation issues can be addressed in the intervening periods between flights over the four-day campaign, and the solutions could prevent the loss of valuable testing time on-orbit.

Benefits

NASA, DoD, NRO, ESA – Benefits any entity utilizing formation flight for on-orbit assembly or aperture synthesis

Future Customers
Propellantless formation flight could benefit or enable any mission where a large degree of reconfiguration is necessary, either during the construction phase of a system that is too large or complex to be deployed from a stowed configuration, or during the operations phase when filling in the u-v plane of sparse aperture. Future space telescopes such as Terrestrial Planet Finder, Stellar Imager and Constellation-X, could have their operational lifetimes greatly extended from this technology.

Overview

Benefits

Overview

The Root-Like Burrowing Device in Lunar Conditions flight tests will assess and compare the reaction and anchoring forces of a rigid intruder and a pneumatic tip-extending device in a low-gravity environment. These tests seek to determine whether the tip-extending device could self-anchor and improve burrowing in microgravity, where reaction forces are difficult to produce. Self-anchoring would enable the device to deliver subsurface sensors to deeper depths. Flight tests also will evaluate the validity of using bed aeration to simulate reduced gravity on cohesive and non-cohesive lunar regolith simulants.

Summary of Flight Test
2025-02-04 Asteroid Soil Strength Evaluation Test (ASSET) – The ASSET experiment is designed to help develop an understanding of soil properties and particle interaction within a low- and micro-gravity environments. The device will first compress a simulant to a known density using a compaction stage and then penetrate the simulant while collecting force vs displacement data with a probing stage. The data that was collected will be used to validate and refine granular material behavior simulations, and inform future generations of designs.
Honeybee Bubble Excitation Experiment (HBEE) – HBEE will help characterize gas bubble formation and propagation in viscous liquids in lunar gravity. These insights will help better predict how oxygen bubbles will act in regolith /rock that is melted during the in-situ resource utilization (ISRU) process called molten regolith electrolysis (MRE). The data that was collected will be used to inform designs of future ISRU systems.
PUFFER-Oriented Compact Cleaning and Excavation Tool (POCCET) – POCCET is designed to explore granular material interactions with a pneumatic system in lunar gravity conditions. The system will demonstrate non-contact pneumatic trenching by blowing air at a known outlet pressure onto a surface of loose kinetic sand and recording the response. The data collected will expand our understanding of possible pneumatic applications as more mass- and power-efficient alternatives to traditional mechanisms.
Root-Inspired Lunar Anchoring – This payload will demonstrate a low-reaction-force and low-material-displacement approach to anchoring structures to lunar surface regolith.
The experiment will extend, and then retract, a root-inspired inflatable anchoring mechanism in a resettable simulant container under lunar gravity conditions. This lunar anchoring approach has the potential to become a cornerstone architecture of human lunar permanence objectives.

Benefits

Overview

Benefits

Overview

Future space exploration missions require advanced thermal control systems to dissipate heat from spacecraft, rovers, or habitats to external environments. These systems must be lightweight, reliable, and able to effectively control cabin and equipment temperatures under widely varying heat loads and ambient temperatures. Current state-of-the-art thermal control systems face the challenge of freezing in the harsh space environment when heat loads are low, and the ambient temperature is extremely cold. The Microgravity Demonstration of Freeze-Tolerant Radiator for Spacecraft Thermal Control is a new radiator technology capable of three-phase operation. The radiator is placed within a vacuum-insulated tube, and a small flow of liquid nitrogen metered to the chamber provides a thermal shroud (panel) for radiative heat sink – a common thermal management system to transport heat energy. The vaporized liquid nitrogen is vented overboard. This technology has the potential for a wide variety of applications given that spacecraft, habitats, payloads, and rovers must adequately remove heat from the operating environment to the external environment. 

Problem Statement 

Thermal control systems will be required for future space missions. Typically, spacecraft radiators are engineered to reject the maximum anticipated heat load for the maximum temperature design environment. When the heat loads are minimal and the ambient temperature is cold, the radiator working fluid can fall below the freezing point. Thermal control systems must be designed to avoid ice formations when the head load is minimal. Deployable radiators are especially vulnerable given their large surface area and low thermal mass. This technology is designed to overcome mass and system complexity in current solutions, as well as the need for freeze-tolerant solutions. 

Technology Maturation 

Parabolic flight tests are expected to demonstrate the radiator’s thermal performance and freeze-tolerance at several heat loads at variable-gravity conditions and measure the motor power during deployment under microgravity. Researchers intend to use data collected during these flight tests for further model validation. The flight tests aim to advance this innovation’s technology readiness level (TRL) to TRL 6. This work is closely tied to and builds upon previous flight testing under T0337. (This work focuses on testing a freeze-tolerant radiator. T0337 tested all other primary components but does not include a radiator.) 

Summary of May 5, 2025 Flight Test
Creare has successfully tested its two-phase thermal flow loop which includes an innovative freeze-tolerant radiator, a microgravity two phase separator, and a microgravity accumulator. The team is steadily increasing the viability and reliability of two-phase heat rejection for a broad range of space applications. The heat rejection system achieves high specific power, high reliability, and good isothermality in the harshest conditions. The team is excited to deploy this technology on new space missions and infrastructure. Funding for the development and testing of this technology was provided by the NASA SBIR program and NASA Flight Opportunities.

Benefits

- Enabling: Provides an innovative solution for a freeze-tolerant condensing radiator capable of three-phase flow in the harsh space environment 
- High efficiency: Reduced pumping power and high heat transfer coefficient; high turndown capacity 

Future Customers 
- Environmental control for surface habitats (advanced habitation systems) and spaceborne platforms 
- Potential fit for the Human Landing System (HLS) for NASA’s Artemis program 
- Extreme environment (lunar, solar system) exploration 
- Commercial low Earth orbit (LEO) satellites for telecommunications

Overview

Benefits

Overview

Benefits

Overview

Benefits

Overview

The In Situ Resource Utilization (ISRU) Pilot Excavator Bucket Drum Flow experiment is designed to assess the performance of a regolith collection method that relies on bucket drum excavation technology. This technology allows regolith to be collected as the drums rotate, and then dispensed as they rotate in the opposite direction. These opposing rotations happen simultaneously to counteract excavation forces. The technology could be used on the Moon and other planets to enable low-mass robotic excavators to dig in low gravity environments.

Summary of Flight Test
2025-02-04 On 2/4/25 the IPEx team successfully completed their Bucket Drum Subsystem Flight Test. This test was an experiment on board Blue Origin's New Shepard 29 mission which created 2 minutes of artificial lunar gravity for automated payloads. The bucket drum experiment housed 6 scaled down versions of our excavation tools under vacuum and filled with various types of regolith simulant. The test provided valuable data to understand the flow of regolith in lunar conditions. This data will be used to reduce/eliminate the risk of regolith clogging or jamming inside the bucket drums. The experiment performed flawlessly during flight and all desired data was captured. The team will post process the data and release publications on the results.

Benefits

Overview

The Multiphase Microfluidics for Chemical Analysis Systems demonstration aims to help researchers assess multiphase reservoirs for sample mixing and bubble migration. The experiment apparatus utilizes reservoir shapes and a high voltage electric field to help drive the gas phase to a desired location and prevent bubbles from blocking outlet/inlet channels. A mixing filter in one reservoir and a high-voltage electrode in the other could potentially help researchers understand the occurrence of unexpected phase behavior.

Problem Statement

Microfluidic systems are an established approach to moving small volumes of fluid for precision chemical analysis via primarily capillary driven flow and are hence insensitive to gravity. However, in some cases, both the gas and liquid phase need to be present at the same time in a reservoir. These multiphase reservoirs are sensitive to gravity, and technologies need to be designed and proven for these multiphase applications. This technology seeks to address that challenge by designing the shape and surface wetting properties of the interior volume of the reservoirs to promote bubble migration to desired regions.

Technology Maturation

This work aims to advance the state of the art by demonstrating that end-to-end fluidic systems, including multiphase reservoirs, are suitable for chemical analysis missions at any gravity level. In combination with other planned environmental testing, this will raise the system technology readiness level (TRL) to 6.

Summary of February 4, 2025 Flight Test
FORGE met many of its goals during the P14 flight. FORGE was able to execute its fluidic protocol and capture an image of the system in its initial state. Critically, FORGE was able to empty all the reservoirs and return them to an air-filled state. This last step is important to prepare instruments for potential cold storage at freezing temperatures when not in use during a robotic space mission. It is also important as a method for resetting the system when operating in the case that a bubble shows up in the wrong place and is not otherwise easily dislodged.

Benefits

The Multiphase Microfluidics for Chemical Analysis Systems demonstration aims to help researchers assess multiphase reservoirs for sample mixing and bubble migration. The experiment apparatus utilizes reservoir shapes and a high-voltage electric field to help drive the gas phase to a desired location and prevent bubbles from blocking outlet/inlet channels. Testing the apparatus in relevant gravity conditions will help researchers test for the occurrence of unexpected phase behavior. This has the potential to benefit NASA missions and the commercial space industry.

Future Customers
· NASA
· Commercial resource prospectors

Overview

Benefits

Overview

Benefits

Overview

The Material Flammability in Lunar Gravity experiment will assess the flammability of solid materials in lunar and Martian gravity. Researchers expect to burn multiple samples in a variety of atmospheres to record flame images, radiant emissions, temperatures, and product gas concentrations. These moderate-duration flammability tests aim to provide guidance for rating the many materials anticipated to be used on the Moon and Mars. As humans prepare for deep space exploration, it is crucial to understand material flammability and its impact on spacecraft and habitats.

Summary of Flight Test
2025-02-04 The LUCI project achieved the first-ever, extended duration combustion tests (greater than 25 seconds) in simulated Lunar gravity. The results are applicable to NASA’s exploration efforts in that they guide the selection of fire-safe materials and environments and ensure safety of future spacecraft and Lunar habitats. The data also provides fundamental understanding of fires burning at reduced gravity for comparison to sophisticated numerical models. Finally, the experiment is a steppingstone to the ultimate goal of performing burn tests on the Lunar surface in the Flammability of Materials on the Moon (FM2 ) experiment which will fly on a SpaceX Human Lander System unmanned test flight.

Benefits

Overview

Benefits

Overview

Benefits

Overview

Project Objective

To address continuous and discrete variables in the concept of operations (CONOPS) and logistics problem spaces present in the model, optimization, and synthesis of space exploration campaign (SEC) architectures.

Project Description

Space exploration campaigns (SECs) are a multi-element system-of-systems (SoS). The individual elements within the campaign need to be orchestrated to meet all needs, goals, and objectives in a technically feasible and programmatically viable manner. Given the intractable number of possible alternatives, exploring a meaningful subset of the tradespace for downselection to a handful of recommended alternatives remains a difficult challenge for the Agency. To advance the Agency’s SEC architecting efficiency and enable data-driven decision making, a digitally integrated testbed that leverages mature digital technologies is necessary to synthesize technically feasible SECs. The purpose of a Digitally Integrated Exploration Campaign Architecture Synthesis Testbed (DIECAST) is to rigorously evaluate SEC alternatives for Pre-Phase A activities.

The synthesis of technically feasible SECs uses an optimization process to first establish feasibility by satisfying requirements and constraints and then use the remaining degrees of freedom to improve the solutions’ desirability with respect to needs, goals, and objectives. These solutions are then assessed for programmatic viability. Generating solutions constitutes a large-scale optimization of an SoS problem, where the degrees of freedom increase exponentially with SECs that require more elements. This class of problem is very challenging, as it involves both continuous variables traditionally addressed by gradient-based optimizers as well as discrete variables in a CONOPS and logistics problem space that is known to be NP-hard. As such, modeling and optimizing this class of problem necessitates introducing mathematical methods that are not typically employed within the conceptual design of SEC architectures. These methods are then combined with the digital testbed for synthesizing SECs to improve architecture desirability. The goal of this project is to demonstrate this combined evaluation method on the nuclear thermal propulsion (NTP) architecture from the set of Mars Transit Vehicle (MTV) alternatives.

Project Results and Conclusions

Mixed Integer Programming (MIP) and Mixed Integer Nonlinear Programming (MINLP) techniques are typically used in bespoke formulations for SEC-related problems, such as space logistics. The inclusion of discrete variables and MIP/MINLP in-the-loop of sizing and synthesizing an architecture concept, especially in a generalized manner, has not been done before. Depending on the scope and level of analysis of an SEC and its elements, multiple subproblems with different sets of discrete variables can be identified. This project focused on the drop tank CONOPS of the NTP architecture, showing proof-of-concept in combining the discrete distribution, usage, and disposal of the propellant drop tanks with the nonlinear sizing and performance of the NTP element throughout its mission. 

A global optimization approach was developed to model and solve this problem, which cannot solely rely on current state-of-the-art solver libraries and methods. The physics-based nonlinear problem space is highly nonlinear and not provably convex, which eliminates many of the current methods. The use case for the integer portion of the problem space does not have a common analogy in other fields that use MIP/MINLP, and there is a need to have the CONOPS modeling formulated in such a way that it can integrate with the current digital testbed for architecture sizing and synthesis. This approach splits the overarching NTP architecture synthesis problem into multiple subproblems that focus on the nonlinear sizing, the mission profile, and the drop tank operations as either continuous, MIP, or MINLP problems; a larger master problem acts to converge all three subproblems using the Augmented Lagrangian Coordination (ALC) method. Additional MIP-related techniques, such as Column Generation, were used to improve convergence for the relevant subproblems.

The stated project milestones were presentation charts on the approach, documented work, and code implementation of the developed algorithms and models for the demonstration problem. Conference and journal articles have been submitted and accepted for this work. The resulting algorithms have been used extensively in the past year to exercise the NTP architecture concept in the digital testbed for multiple purposes, including cryogenic fluid management (CFM) technology assessments and creation of data products for the Mars Architecture Team. 

Benefits

This effort advances the Agency’s ability to rigorously evaluate SEC alternatives for Pre-Phase A activities. SECs are highly complex SoS problems, in which the downselection of feasible alternatives for programmatic assessment is difficult mainly due to the factionalized paradigm of modeling alternatives across the Agency. DIECAST is meant to address this issue, and a key enabler of modeling SECs is capturing the discrete problem spaces that are typically excluded from the conceptual design of SEC architectures. MIP/MINLP methods were demonstrated by modeling the NTP architecture among the set of MTV alternatives, showcasing the effects of including discrete variables in the sizing and synthesis process. The effort resulted in a new formulation to model the architecture and its CONOPS, as well as a novel approach and algorithms to solve the formulated mathematical optimization problem. Continuations in this research area will extend this approach and its techniques to cover other discrete portions of the SEC problem space.

Overview

Project Objective  

Sorbent-Based Atmospheric Revitalization (SBAR) is a compact, NASA-patented, adsorption-based carbon dioxide (CO2) scrubber and humidity removal system for human space transportation and habitation systems.  

Project Description 

The Marshall-developed SBAR system is a low-resource technology for CO2 and humidity removal that has been shown to be a viable and competitive technology when compared to other state-of-the-art technologies. The SBAR system utilizes zeolites, which are nontoxic, nonflammable, and commercially available adsorbent materials packed in layers in a two-bed assembly. Zeolites have been proven effective and safe in spacecraft including Skylab and the International Space Station.  

SBAR's novel approach allows operation without thermal regeneration for short mission durations and unlimited operation with periodic thermal regeneration.  The system utilizes zeolites type 13X and 5A packed in layers in a two-bed assembly. Flow passes through the first 13X layer to remove water vapor. A portion of the dehydrated flow bypasses downstream bed layers and is returned to the cabin. The remainder of the flow passes through an additional layer of 13X to remove residual moisture and through 5A to remove CO2. The second bed of the system is simultaneously placed under vacuum to allow the CO2 and H2O to be removed. Each bed has three locations for vacuum access. The valves are sequenced during the desorb cycle so that the vacuum source is opened to the flow inlet end of the bed (13X side) first. The center port is then opened to the vacuum source, and then finally the 5A end of the bed is placed under vacuum. This sequence ensures the material with the greatest water loading is evacuated first and that the flow direction minimizes water propagation into the 5A material.

The 2025 effort included technological advancement of the SBAR system for regenerative and non-regenerative applications by incorporating internal heater fins to increase desorption efficiency and reduce power consumption compared to previous heater location external to the beds. Additionally, the adsorbent beds were packed utilizing a “snowstorm” technique to reduce zeolite attrition and dusting.

Project Results and Conclusions 

At the conclusion of 2025, an updated SBAR development unit and test stand, including facility connections, software, and data acquisition needs, was completed.  The goals to incorporate internal heaters along with improved adsorbent packing were met. The team also achieved significant progress towards testing, including modeling of SBAR systems for specific NASA missions with the intent to move into testing in 2026. Other accomplishments include a published NASA Technical Memorandum and a New Technology Report for integrated plenum valves. SBAR has received significant interest from NASA programs for use in human space transportation and lunar and cislunar habitation systems.

Benefits

Further development of the SBAR system aligns with Marshall's pursuit of highly reliable, robust environmental control and life support (ECLSS) systems for habitation development and exploration missions. Having a wide range of applications within the space sector, as well as within the government and private industry, positions SBAR as an ideal technology for MSFC investment and potential future partnerships. 

Overview

This project aims to develop a suite of specialized AI-assisted capabilities to aid mission proposal development and planning at NASA Goddard Space Flight Center. By combining human expertise with advanced AI capabilities, this project aims to significantly enhance the efficiency, quality, and competitiveness of NASA Goddard mission proposals, ultimately advancing the agency's space exploration and scientific discovery goals.

Benefits

1. Enhanced proposal development and competitiveness: AI tools will accelerate mission implementation planning by enabling teams to create high-quality drafts earlier. The result is higher-fidelity mission implementation plans, identification and addressing of potential weaknesses, and overall stronger proposals. This streamlined process improves NASA Goddard's mission proposal competitiveness while optimizing the use of time and resources throughout the development cycle.

2. Streamlined mission planning and documentation: The project aims to reduce effort in transitioning to digital threads and MBSE models, enabling faster design iterations and improvements. Additionally, AI tools will efficiently generate initial drafts of supporting documents based on mission context, such as cost Basis of Estimates, design review slides, requirements, risk statements, heritage summaries and more. This comprehensive approach to mission planning and documentation enhances overall efficiency and quality.

3. Improved onboarding and communication: The project will reduce the time needed to onboard new proposal support staff and decrease communication overhead for key personnel, including Principal Investigators, Project Managers, Systems Engineers, and Subject Matter Experts. This improvement facilitates smoother team integration and more effective collaboration.

4. Integration with NASA's digital transformation: The project directly contributes to NASA's ongoing Digital Transformation and Digital Engineering efforts by implementing AI-powered tools in the proposal development process. This integration provides a clear path for future missions to adopt these new capabilities, ensuring Goddard remains at the forefront of technological advancements in mission planning and execution.

5. Broader applicability and industry impact: While focused on NASA missions, the tools and methodologies developed have potential applications in the commercial space industry and other government agencies. For example, the AI-assisted document generation and proposal review processes could be adapted for use in commercial satellite development or in planning Earth observation missions for other agencies.

6. Advancing national space leadership: By enhancing NASA's ability to develop and propose innovative space missions more efficiently, this project strengthens the nation's position in space exploration and scientific discovery. The improved proposal process and resource optimization contribute to higher-fidelity mission concepts and more robust implementation plans. This increased proposal quality and thoroughness translates into selected missions that have a better chance of meeting schedule, budget, and performance targets during implementation. Consequently, this leads to more successful space missions, accelerated scientific advancements, and reinforces NASA's role as a global leader in space exploration.

Overview

Benefits

No details available.

Overview

The 2011 Strong Tether Centennial Challenge was held at the Space Elevator Conference in Redmond, WA on August 12, 2011. The Space Elevator Conference, sponsored by Microsoft, The Leeward Space Foundation and The International Space Elevator Consortium has hosted the Tether competition for 5 years and for this, the fifth year, there has yet to be a winner. Although no competitor has been able to claim the Centennial Challenge prize, the strength exhibited in competing tethers has continued to increase over the years as new and innovative methods are discovered for fabricating tethers with carbon nano-tube technology.

Dr. Bryan Laubscher of Odysseus Technologies and Flint Hamblin, an independent inventor, competed this year trying to achieve a tether strength of at least 5 MYuris. The goal of the Strong Tether Challenge is to develop a strong but lightweight tether. The unit of MYuri (N/kg/m) takes into account strength and weight of the sample being a measure of force carried per gram per length of tether sample.. A strong but heavy tether may have a lower Yuri value than a weaker but lighter sample. For a Space Elevator tether that may be 100,000 kilometers in length, both strength and weight are obviously important. While Bryan and Flint both entered tether samples that broke below the 5 MYuri threshold for a prize, they have continued to contribute to material science advancements in the use of carbon nano-tubes as a strengthening material.

Odysseus Technologies is a business venture started by Dr. Laubscher to advance the use of carbon nano-tubes in engineering materials design and use.

The Strong Tether Challenge is driving material science technologies to create long, very strong cables (known as tethers) with the exceptionally high strength-to-weight ratio. Such tethers will enable advances in aerospace capabilities including reduction in rocket mass, habitable space structures, tether-based propulsion systems, solar sails, and even space elevators. Dramatically stronger and lighter materials are also revolutionizing the engineering of down-to-earth structures such as aircraft bodies, sporting good equipment, and even structures of bridges and buildings.

This challenge offers a prize purse of $2 million. Competitions have been held in 2006, 2007, 2009, 2010 and 2011. As yet no team has claimed the prize.

Benefits

The Strong Tether Challenge is driving material science technologies to create long, very strong cables (known as tethers) with the exceptionally high strength-to-weight ratio. Such tethers will enable advances in aerospace capabilities including reduction in rocket mass, habitable space structures, tether-based propulsion systems, solar sails, and even space elevators. Dramatically stronger and lighter materials are also revolutionizing the engineering of down-to-earth structures such as aircraft bodies, sporting good equipment, and even structures of bridges and buildings.

Overview

Conduct ground testing and flight demonstration of cryogenic LH2 transfer (the most challenging of the cryogenic propellants) and long duration storage in space. IFD incorporates up to 17 critical technologies identified by NASA into a single system that demonstrates the transfer, storage, and pressure control of LH2.

Benefits

The ability to store and transfer liquid hydrogen (LH2) is critical to NASA’s Artemis architecture, a future Lunar “water-based economy,” and the ability to send humans to Mars. This demonstration will advance several critical CFM technologies with an in-space demonstration in a micro-gravity (μ-g) environment.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

Benefits

No details available.

Overview

In 2024, the Cryogenic Fluid Management Portfolio Project Office (CFMPP) at NASA’s Marshall Space Flight Center tasked a group of engineers to write a high-level guidelines document for In-Space Cryogenic Propellant Transfer (ISCPT). The group produced CFM-DOC-008 Guidelines for In-Space Cryogenic Propellant Transfer (ISCPT), which was baselined in January 2025. The document is not prescriptive in nature but is intended to assist NASA and Commercial Projects in developing architectures and ConOps for systems under development. The document “sets the stage” by making some initial assumptions – among them that two spacecraft (termed the “propellant supplier spacecraft” and the “propellant receiving spacecraft”) are docked together, and the act of docking the two spacecraft accomplishes the mating of cryogenic fluid coupling devices (termed “cryocouplers”). Then the document discusses procedures for settled propellant transfer, unsettled propellant transfer, cryocoupler construction, and safety.

Benefits

The ISCPT is a groundbreaking document; no other document like it exists. Even in its simplest form (settled transfer), the transfer of cryogenic propellants in microgravity is very complex. The benefit of the ISCPT document is that it gives engineers a place to start when planning propellant transfer(s) for systems under development.

Overview

Benefits

Overview

Benefits

Overview

This activity's objective is to develop a combined protection systems that combines thermal protection (i.e. MLI) and hypervelocity impact protection. Testing will include hypervelocity impact testing at both the coupon and tank applied level as well as thermal calorimeter testing, liquid hydrogen tank applied testing, and tank applied vibration testing.

Benefits

Combining these protection systems on cryogenic tanks will decrease their thickness and allow for a significant volumetric increase for tanks as well as a reduction in mass.

Overview

Project Objective

The objective is to design, build, test, and optimize a thermal switch for passive thermal management of avionics.

Project Description

The long-term goal of this project is to create a technology that will allow the operation of electronics in extreme thermal environments while minimizing power consumption. In order to do this, a thermal switch will be developed and optimized through thermal vacuum testing. By isolating variables and variation of the design, we can achieve a high turndown ratio. The turndown ratio is the ratio of conductivity of the switch in its open and closed state.

Once this design is optimized and understood, a test article will be sent to operate outside the international space station as a proof of concept.

With a proof-of-concept and operational parameters, an energy savings for a given mission can be calculated. That energy savings can then be converted to a mass savings for a given battery system.

Project Results and Conclusions

The project was a great success. All objectives for the period of performance were met or exceeded.

Two different designs were tested, a design that used a wax motor and a design that used coefficients of expansion. In addition, multiple heat pipe designs and thermal interface materials were tested. By combining the best design characteristics, a turndown ratio about 70:1 was achieved.

After the design was optimized, a test electronics box and enclosure were designed, built, and tested to represent the box that would be sent to the international space station. The testing of the full electronics enclosure with the switch on the printed circuit board showed that the turndown ratio drops significantly due to the circuit board mounting and electrical wiring. In the full enclosure, the ratio dropped to 10:1.

Going forward, a new enclosure will be designed to maximize insulation and increase the turndown ratio.

Benefits

This investment is for the further development of an innovative passive thermal switch mechanism which helps to regulate the temperature of printed circuit boards (PCBs) in extreme thermal environments via variable heat rejection capabilities. There are multiple STMD capability gaps addressed by this project. In the category of Advanced Avionics Systems, this project addresses STMD gap ID AV 447. This technology will help to create electronics that can operate over a wide temperature range. The technology will reduce the amount of energy needed to keep the electronics warm during lunar night. In the category of Advanced Thermal, this project addresses STMD gap ID THERMAL 483, 604, 1132. The ability to have variable heat rejection on small independent payloads with high efficiency heat pipes will allow for better power management. The technology can make each avionics box easier to manage thermally as it can isolate or conduct as needed.

Overview

Project Objective

This custom designed bubble point test stand supports two major objectives: 1) Gives NASA Marshall Space Flight Center (MSFC) the ability to perform its own bubble point testing which is the current state-of-the-art for filter testing, and 2) Lays the foundation with which NASA’s newly developed filtration and contamination test methods can be compared.

Project Description

For more than 50 years, NASA had not maintained a significant in-house Filtration and Contamination (F/C) testing capability, relying instead on aerospace filter manufacturers to perform critical evaluations such as bubble point testing. Bubble point testing is one of the key tests currently used to characterize filter performance and although experts at MSFC routinely participated in vendor-conducted tests to support propulsion filter design and system-level filtration efforts, the resulting data were proprietary and could not be broadly shared or archived for agency use. Establishing an in-house filtration bubble point test stand at MSFC closed this long-standing capability gap, enabling NASA to independently characterize element pore size and correlate filtration ratings with actual filter performance.  Additionally, this capability will enable MSFC to support filter-related anomaly investigations and provide transparent, shareable data to NASA programs and industry partners. 

This custom bubble point test stand was designed specifically to meet MSFC’s unique test objectives. As a primary function, this test stand enables fundamental, standardized filtration testing at NASA. In addition, this stand was designed with an elevated clear tank to provide an unobstructed view for demonstration and teaching applications as well as photography.  MSFC is developing advanced methods to characterize filter performance and this bubble point test data will serve as a critical benchmark for correlation.

Project Results and Conclusions

The primary deliverable of this effort was a fully operational filtration bubble point test stand at MSFC, acquired and implemented through structured procurement and installation/checkout phases. Given the limited availability of bubble point systems—most of which were high-cost, automated platforms designed for large production facilities—the selected, Hydra Tech stand provided a cost-effective, customized solution tailored to NASA’s research and development needs. The system featured hands-on manual controls for enhanced flexibility and a unique, clear test tank that provided 360° degree visibility, enabling detailed observation, photography, and improved technical assessment of articles throughout the testing process. The custom stand also allowed testing of disk-shaped screens, commonly used in propulsion system valves, in addition to cylindrical filter elements. 

This bubble point test stand is the keystone in the larger filtration and contamination test facility at NASA MSFC. Its capabilities reaffirm MSFC’s commitment as the agency’s center of excellence in filtration requirements development and fluid system contamination prevention, strengthening NASA’s ability to advance reliable filtration technologies for current and future space exploration missions.

Benefits

NASA’s Marshall Space Flight Center (MSFC) is committed to advancing the state-of-the-art in filtration and contamination prevention for propulsion systems as well as improving the development of filtration system requirements. The recently installed bubble point test stand represents a significant addition to MSFC’s capabilities, providing a standardized test method that establishes a baseline for filter performance evaluation. This capability not only enables consistent assessment of current filtration elements but also serves as a foundation for evaluating and correlating future technologies, including real-time particle detection and advanced filtration techniques, thereby supporting MSFC’s ongoing efforts to enhance reliability and performance in critical fluid systems.

Overview

Project Objective  

A compact, reconfigurable vacuum chamber can accommodate diverse experiments for ground testing, parabolic, and suborbital flight environments, enabling access to microgravity testing.

Project Description 

Environmental testing is a critical component of risk reduction for space missions. Ground-based thermal vacuum testing is utilized by several MSFC projects, making access to this testing extremely important. Additionally, simulated microgravity is a major component of the space environment, and it is difficult to access. Flight experiments are high in both time and monetary costs. Streamlined access to suborbital and parabolic flight experiments and ground testing capabilities are important for NASA and Marshall to continue high-caliber science and technology development.

Previous work has been done to conduct flight experiments for the development of in-space laser beam welding. A simple vacuum chamber, conceived for a previous center investment proposal, now has potential to become a modular, compact thermal vacuum chamber, with a design that allows variable chamber volumes and instrumentation ports. This proposal will enable this development to take place. The size of the chamber allows it to fit on ES31’s 3-axis rate table, and it is versatile enough to use for both ground and suborbital/parabolic flight experiments. Thermal capabilities will support ground testing, but development of this chamber is a step towards enabling thermal capabilities of the chamber during flight experiments.

Project Results and Conclusions 

A prototype chamber was constructed to support laser beam welding experiments, demonstrating vacuum level, sample positioning, and welding capabilities. This effort became the jumping off point for DISCMAN (DIsk-shaped Configurable and Modular vAcuum uNit) - an STMD project targeting deployment in the Voyager Airlock on the International Space Station. There is still forward work to expand DISCMAN's design to other types of testing and the addition of heating/cooling capabilities.

Benefits

This project has directly benefited NASA's Space Technology Mission Directorate, as a flight payload based off of this prototype has been funded for development. This flight payload will advance the understanding of space environments (vacuum and microgravity) on the laser welding process and how it will impact In-Space Servicing, Assembly, and Manufacturing via laser processes.

Overview

Benefits

This project is to develop ways to engage the public in the development of simulated tasks for Mars surface Extravehicular Activities (EVAs) for use in simulated missions. This would include the development of relevant scenario and task definitions, the associated 3D models/model detail needed, and any associated simulations to drive responses and interactions of those models. 

The ultimate goal of this project is to provide the framework for public engagement that results in the generation of hundreds of hours of interesting and relevant simulation capability that research subjects and astronauts can engage with during simulations within a virtual reality (VR) environment.

Project Team received scenarios and assets to be implemented into the XOSS environment and help train astronauts for future missions to Mars. Team also identified a community of XR developers to tap for future work.

Overview

Early detection of a developing fire is critical for ensuring that a fire does not result in crew death or injury. A comprehensive lunar fire detection strategy involves selection of the most effective detection technology (e.g., ionization, photometric, or a combination of multiple sensors), detector placement (e.g., behind returns or on ceilings), and appropriate alarm thresholds to optimize early fire detection. In addition, false alarms due to lofted cabin dust challenge reliable fire detection on the ISS and will likely pose a greater problem with the addition of Lunar dust as a source of nuisance cabin aerosol. Ongoing experimental work will characterize smoke signatures (gas and particle compositions and concentrations) generated during potential early fire scenarios, evaluate optimal times to alarm, and identify potential solutions to false nuisance alarms from cabin dust.

Lunar and Martian habitats will undoubtedly have forced convection for ventilation and dust control. Based on ISS designs and requirements for dust control, it is logical that the diffusers for this flow will be near the ceiling. On the Moon or Mars, a fire will form a buoyant plume which will rise to the ceiling although slower than on Earth. A dust removal ventilation system would most likely be located near the floor to remove the dust as it settles. The interaction between these two systems could significantly delay fire detection. Of course, fire detectors near the floor would be prone to nuisance alarms from dust but with ventilation, smoke particulate may not reach the ceiling. The purpose of this work is to model this phenomenon to determine the optimal location for fire detectors in Lunar and Martian applications. This will inform both NASA and contractor personnel who are involved with designing and verifying Lunar and Martian landers and habitats.

Benefits

Based on this work, future surface vehicles and habitats can design fire detection and dust mitigation strategies that work together to effectively perform their functions. Specifically, the location of fire/smoke detectors to provide effective fire detection can be identified.

Overview

NASA has developed a set of emergency response equipment to address spacecraft fire safety hazards. Because of the unique requirements of human spaceflight, much of this equipment has been developed in-house by NASA and maintained as Government Furnished Equipment (GFE). Human spaceflight missions beyond Low Earth Orbit (LEO) have spacecraft fire safety requirements that are more severe and more challenging. Without an opportunity to quickly return to earth, spacecraft fire safety systems must operate with a longer service life and protect the crew for a longer duration under more severe conditions.

This project includes two technology development projects with the objective to incrementally improve and upgrade systems already in service on ISS, as well as provide new technologies for deep space missions like Artemis and Mars.

One project improves capabilities of the Emergency Breathing Apparatus. The respirator cartridge qualified for use on ISS uses a catalyst to catalytically convert carbon monoxide to carbon dioxide. This catalyst system is prone to underperformance under cold conditions, overheating breathing air when carbon monoxide concentrations are high, catalyst dusting, and filter clogging when there are large amounts of liquid droplets from the discharge of a fire extinguisher or large amounts of smoke and soot. The mask-respirator development project addresses each of these four issues and aims to prototype and test a complete mask system with improved safety performance.

The corkscrew pre-filter project has a project goal of improving smoke-eater performance by integrating a corkscrew prefilter into a smoke eater system with a cylindrical bed shape and a radial inflow configuration. The goal of the corkscrew pre-filter project is to increase the capacity for water droplet and smoke particulate ingestion, reduced system pressure drop, and enabling performance tests that can be conducted in 1g conditions and accurately reflect performance in a microgravity environment.

Benefits

The project goal is to improve the safety performance of two pieces of fire safety equipment.

The project goals for the mask are: 1) improve catalyst performance at low temperature, 2) reduce breathing air temperature at high carbon monoxide concentrations, 3) improve the capacity for smoke, soot, and water droplets. FY25 goals for the mask project are to demonstrate key performance parameters in a prototype respirator cartridge.

The project goals for the smoke eater prefilter are: 1) have a capacity for water droplet capture greater than the entire water quantity in the portable fire extinguisher, 2) maintain a prefilter pressure drop of less than 0.2 IWC (inches of water column) for all loading conditions, 3) verify performance with testing in 1-g. FY25 goals are to demonstrate key performance parameters at the sub-assembly level.

In FY24, these technologies will continue to be developed so they can be designed, fabricated, and tested in FY25. If successful, a complete respirator cartridge will be prototyped and tested in FY26. The anticipated benefit of this work is to have an upgrade to the emergency breathing masks completed as the existing breathing masks are removed from service (5 year lifetime).

Overview

SONTRAC is designed to detect incident solar neutrons within an energy range that fill a current gap in the energization process of flare ion acceleration. SONTRAC tracks recoil protons (from neutron interactions) as they traverse the fiber bundle volume, which deposit ionization energy along their path.

Currently, the reconstruction involves determining the energy deposited and the direction (e.g., the momentum vectors) of the recoil protons. In many cases, there is significant ambiguity in how to best identify the tracks properly. Kinematics can be used to eliminate certain configurations, but the effort is fully manual and laborious. We will take advantage of PIML to dramatically simplify the reconstruction effort, resulting in a significant improvement in the number of neutron interaction events that can be reconstructed in an autonomous manner and thus improve the instrument efficiency. We will embed physics within the training of the model via sophisticated custom loss function terms to utilize established physical principles and derived formulas. Using PIML also allows for enhanced generalization to unseen scenarios due to the embedded knowledge of physical phenomenon.

By simulating SONTRAC we enable the production of adequate amounts of data for training, and combining this with ML, which gives us novel insights, we can embed the insights within classical physics-based equations, we can usher in a new state-of-the-art (SOA).

We will also explore using PIML to improve the efficiency of the Wang-Sheely-Arge (WSA) model of the near-solar environment. WSA, currently built with empirical evidence, is used to predict space weather and is vital for assessing the impact of solar winds on satellite operations, communication systems, and astronaut safety. It is used worldwide and is currently standard and SOA in its field, but enhancements have not been made in many years.

The end goal of this effort is two-fold. The first end goal is to significantly improve the use cases targeted in this work, which are the SONTRAC instrument, which would be improved via enhanced autonomous neutron interaction event reconstruction, and the current WSA model, by utilizing PIML to achieve better accuracy and/or efficiency. The second end goal is to advance the field of PIML in Heliophysics, which would enhance many current efforts, such as (but not limited to) the Magnetospheric Multiscale Mission (MMS), Cluster mission, by automatically detecting and labeling plasma waves, or current Heliophysics models like ENLIL, by enhancing its accuracy and efficiency.

Our approach has three primary tasks: (1) training dataset generation, (2) loss function development, and (3) model training. To use our proposed ML models, we collect Geant4 simulator data into an ML-ready format. Then, we will process the individual neutron paths into a voxel representation resembling the physical construction of SONTRAC. Since we will have the compressed 2D readout from the simulated SONTRAC instrument as inputs and the true 3D paths through the instrument as labels, we can train an ML model, such as a physics-informed neural network (PINN), to directly predict these particle paths and collisions through generation of the 3D voxel representations. We will then be able to construct a loss function that ensures predicted paths do not violate the hard physical constraints that limit these particle interactions. This loss function will have multiple parameters, and their relative weighting will be a subject of investigation. We will then attempt to generate experimental data to prove and benchmark our ML model for SONTRAC.

We will do a similar process with WSA. First we will generate simulation data based on WSA, as well as gather any in situ data that might be available. Then, we will embed the physical and empirical aspects of the current WSA model with PIML, achieving this goal using the aforementioned primary tasks, to create a new and improved WSA model.

This process will be directly applicable to instruments and models beyond SONTRAC and WSA, and will provide a blueprint for others to implement their own physics-based strategies. The developed loss functions will be iterated on as part of a standard hyperparameter search completed during the training of out-path generation models. This results in model that accurately interprets SONTRAC data with a strong physics rationale, and predicts solar wind speed with greater accuracy and/or efficiency.

Benefits

This mission will directly benefit the SONTRAC instrument, by enhancing its capabilities of tracking neutron incident tracks and energy deposits via protons.

This effort directly aligns and supports:

• The following Goddard 2040 Vision Key Elements:
  • 1. Models and Method
  • 2. Multiscale Measurement and Characterization Tools and Methods
  • 3. Optimization and Optimization Methodologies
  • 4. Decision Making and Uncertainty Quantification and Management
  • 6.Data, Informatics, and Visualization
• The following Goddard 2040 Strategic Vision Vectors:
  • 1. Advance Multidisciplinary Space Science
  • 4.Enhance Space Weather Knowledge and Applications
• Strategic Focus Area (SFA) of Heliophysics
• NASA Artemis mission priorities via supporting space weather and solar activity prediction, thereby improving Artemis human spaceflight success through increased safety from hazardous solar particle events (SPE).

Overview

Introduces first class Linux support for flight software in next-generation space processors and allows missions to tap into Linux's unrivaled performance, hardware support, and software ecosystem. This support is enabled through an embedded linux distribution using the Yocto Project named Space Grade Linux, Linux-specific core Flight System apps, and other general operating system components.

Benefits

• Offers a reusable software ecosystem reducing the need to "reinvent the wheel".
• Reduces required level of technical expertise to develop flight software.
• Facilitates integration of modern software frameworks, such as for AI/ML, into flight software running on modern space processors.
• Establishes a reference operating system on which flight software and next generation space processors can target.
• If desired, enables future collaboration among industry, academia, and large open source non-profit entities that can revolutionize the software and hardware ecosystem for space to pronounced effect Automotive Grade Linux project had on the Automotive industry.

Overview

Compact and electrically driven Terahertz-frequency quantum-cascade lasers (THz-QCLs) (~2x2 mm,

Benefits

This technology will have diverse applications in planetary science, heliophysics, and earth sciences that require high-resolution (>1ppm, R>106), compact, and compatible with cryogenic sensors operating from 1-5 THz.

Overview

The placement of the Remote Sensors and Far-Field Diagnostics in the Saffire-IV-VI experiments provided data on the conditions within the Cygnus Vehicle during the fire events. The ultimate goal of this data is to develop and verify a model of fire scenarios in spacecraft with inputs of ECLSS air flow, heat release rates, and release rates of combustion products (particulate and gaseous). Data from other tasks within the Spacecraft Fire Safety Demonstration activity will incorporating data for Li-ion battery fires, typically considered the "worst case" spacecraft fire, and the fate of acid gases during the fire and associated cleanup are required.

A greater understanding of the effects of a fire inside a crewed vehicle at potential exploration atmospheres is needed. These exploration atmospheres, such as those being proposed for upcoming Lunar missions, include higher oxygen concentrations and lower pressures, also known as Normoxic conditions. Full scale fire testing, such as those performed during previous space programs, is the most straightforward way to obtain this understanding. These tests are difficult to implement in 1-g and even more challenging to attempt in Lunar-g. The goal of this work is to develop a model to inform experiments aimed at determining flammability properties of common materials at exploration atmospheres, as well as determine the effect a fire has inside a spacecraft. This model can also be verified against existing experimental data and be easily simulated in Lunar-g to predict the effect of gravity on fire propagation.

Benefits

The anticipated benefit of this work to is provide realistic models of worst-case spacecraft fire scenarios to determine the impact of such a fire on the crew and vehicle and the effectiveness of post-fire cleanup strategies.

Overview

Based on tests performed in the Gas and Aerosol from Smoldering Polymers (GASP) lab, HCl and HF were included in the Anomaly Gas Analyzer (AGA) developed as the replacement for the Compound Specific Analyzer – Combustion Products (CSA-CP) on ISS. This instrument will also be used on Orion. However, the long-term fate of HCl and HF following a fire is not clear. While it is easily removed by a carbon filter, tests have shown that they readily adhere to surfaces. Therefore, rather than scrubbing these compounds from the air, they would have to be removed from surfaces in a spacecraft. This task is to conduct a test campaign to understand which materials are more susceptible to collecting HCl and HF, the deposition rate, and how the surfaces can be cleaned.

Key Performance Parameters:

• Characterize fate of acid gas in a fire, by studying HF and HCl absorption on spacecraft materials. Achieve understanding of partitioning of acid gases over surfaces, fire aerosols, and the gas phase to support post fire cleanup.
  

Benefits

The anticipated results of this work is two-fold. First, the uptake of HCl and HF on various materials will be quantified and a model for that uptake will be developed. This could then be incorporated into the fire scenario computational model being developed in a separate task. Second, the rate of uptake will be quantified which can be used to develop requirements for clean-up of surfaces following a fire.

Overview

We are working on developing integrated photonics technology to improve the functionality of space-based microwave radiometers. By encoding the radiometric microwave spectra onto an optical carrier, we can process broad parts of the microwave spectra in parallel using optical techniqiues. Employing integrated photonics allows us to ruggedize the system, shrink the size and potentially improve instrument efficiency.

Benefits

We can reduce size, weight and power of space-based instrumentation. This simultaneously improves measurement capabilities and makes a smaller more flexible package for satellite use. The integrated photonics tools and components we are developing will also have broader usage in other sensors.

Overview

This project supports the wider Intelligent Extensible Mission Architecture (IEMA) by providing the software and hardware platforms required to demonstrate artificial intelligence across heterogeneous, extensible constellations. There are three critical elements: a simulation platform in which to prove algorithms, an Unmanned Aerial System (UAS) platform to accomplish a snow hydrology science mission, and a credible path to spaceflight through a hybrid constellation demonstration. We will leverage the NASA Operational Simulator for Small Satellites (NOS3) and the On-board Artificial Intelligence Research (OnAIR) Platform to achieve these goals. Demonstrations will progress from entirely simulated, a field UAS campaign, to a hybrid constellation that incorporates distributed simulated assets and physical UASes.

Benefits

The development of autonomous, ad-hoc, heterogenous constellations has the potential to enable new Science missions, increase the useful life of assets, and improve the return on investment compared to traditional, monolithic, one-off missions. Autonomy is required for assets to react to transient events, overcome bandwidth limitations, and deal with novel situations. Extensibility and heterogeneity is necessary to increase the longevity of assets so that they continue to be of use beyond their initial goals and adapt to new conditions and resources.

Overview

ISS crew rely on exercise countermeasures to mitigate health effects associated with long-duration exposure to microgravity. However, current systems are mass-, power-, and volume-intensive and are sufficient for microgravity extravehicular activities (EVA) but not completely effective for crew egress or immediate surface EVA after a long period in deep space. Mass efficient and effective exercise is needed for preventing injury and providing muscle/cardio fitness in preparation for crew activities, including surface EVA. For long-duration missions, effective exploration-compatible exercise countermeasures and assessment tools are needed for crew to accurately maintain and monitor physical health and performance during exploration missions.

The Exercise Physiology Countermeasures lab at JSC has two tasks working towards gap closure: Exploration Exercise Treadmill Requirements (Zero T2) and Exploration Exercise Capability Development (EECD).

ZeroT2’s intent is to understand the impact a treadmill has on maintaining the human systems (sensorimotor, bone, aerobic fitness, or muscle) of astronauts in microgravity. The intent of this project is to know if a treadmill is required for Artemis missions.

Artemis missions and beyond have volumetric and mass constraints that limit exercise hardware to be lightweight and have a small footprint. This has resulted in the development of exercises devices that are more compact and provide both aerobic and resistive training on one platform. Currently, these devices provide a variety of full body resistance exercise options, aerobic rowing, and cycling, but no treadmill. Treadmill is the only exercise hardware that provides ambulation or reinforcing the motor pattern of walking.

Building on FY25 formulation work (selection criteria development and comprehensive market survey), the Exercise Physiology and Countermeasures team will conduct Human-in-the-Loop (HITL) testing of aerobic monitoring technologies in FY26 (EECD). These capabilities are essential for long-duration exploration missions, providing accurate, mission-relevant physiological data that informs both real-time crew health monitoring and long-term countermeasure planning. Additionally, the Danish Aerospace Company’s Aerobic Fitness Monitor (AFM) will be included in the HITL evaluation, giving early insight into its acceptability as a next-generation VO­2 monitor for use in parallel in-flight research by the ZeroT2 study. Current flight hardware is being decommissioned and its size, complexity, and the time requirements are too great for exploration missions, driving the need for selection of new technologies for future monitoring systems.

Benefits

The Zero T2 study will determine the effect of exploration exercise modalities with no treadmill use during spaceflight on bone health, muscle performance, aerobic fitness, and sensorimotor performance during and after ISS missions. Data from this study is needed to inform exploration vehicle design early to avoid cost and schedule impacts associated with vehicle system re-design.

By targeting aerobic monitoring technologies, the EECD effort enables the future integration of real-time and longitudinal assessments of crew aerobic fitness, supports effective countermeasure use, and contributes directly to CMS system requirements by distinguishing viable technology solutions for meeting Mars Concepts of Operations (ConOps). The resulting evidence base will inform integration decisions within the constraints of mission architecture, vehicle design, and mission operations.

Overview

This project would enable Engineers and Scientists to get early hands-on opportunities with the High Performance Space Computing (HPSC) Evaluation cards to build expertise and demonstrate concepts. Scientists and Engineers have collected several applications and use cases that are currently too demanding to execute on the current State of the Art offering of rad hard processors. This project would develop and evaluate those use cases on HPSC hardware, benchmark results and provide comparison to our existing known processor architectures. These results will be critically important to inform processor selection and science formulation boundaries for future mission concepts.

Benefits

HPSC will offer game changing processing capabilities, and open opportunities for entirely new science mission and operations concepts. GSFC has the experience, and ambition to lead the way in developing those new mission concepts. This IRAD effort enables engineers to operate the HPSC Eval cards, benchmark performance of applications, evaluate flight software, and compile the results to inform NASA strategy for future mission opportunities.

Overview

The “worst-case” fire identified by the Orion and HLS Programs is that of a Li-ion battery undergoing thermal runaway. In fact, a Li-ion battery fire was used to develop requirements for all the fire response equipment carried on-board and to evaluate the effect of an elevated %O2/reduced pressure on the propagation of such a fire. The purpose of this activity is to conduct ground-based tests of the thermal runaway of Li-ion batteries in single pouch cell and complete tablet and laptop computer configurations.

Key Performance Parameters:

• Characterize heat release rates, aerosol, and hazardous products for 4 possible battery scenarios (identify reasonable subset of scenarios)
• Determine heat released, gas species and aerosol produced during Li-ion battery thermal runaway, informing modeling and mission and hardware design.
  

Benefits

The unique feature of this testing is that the heat release rate, gaseous species released, particulate loading, etc. can be quantified with tablets under different conditions (state of charge, storage configuration, etc.). This data uniquely determines the outcomes of the event that would impact a closed spacecraft environment. CFD models of fire events that are being developed (the Saffire experiments in Cygnus are being modeled, for example) would use this ground-based data as input to model a battery thermal runaway event in a spacecraft. Therefore, gaseous species, particulate, temperature, pressure rise, etc. can be tracked in the spacecraft.

Overview

Missions for Moon to Mars are very different from missions to the ISS due to length of isolation and confinement, distance from Earth, and the resource restrictions that will be applied to the crew. Artemis Program vehicles have limited mass allocations for food and other consumables. Given the increased distance to Mars and timeline for return, programs need to understand the impacts of restrictions within realistic constraints on health and performance to inform risk/resource trades prior to a mission.

CHAPEA is a high-fidelity Mars Analog focusing on validating operational countermeasures and informing program risk/resource trades.

Benefits

CHAPEA is a Mars forward analog with the objectives to:

• Assess the integrated impacts of realistic Mars mission constraints including isolation and confinement, timelines, time delay and more extreme resource restrictions than ISS on human health and performance for exploration class missions.
• Inform NASA standards, associated vehicle mass and volume requirements, and resource-risk trades for long-duration exploration missions.

Overview

Build a prototype of our Tandem Ion Mass Spectrometer (TIMS), that can separate the mass and charge of atomic ions and can separate atomic and molecular ions of similar mass-per-charge ratio (M/Q). This prototype TIMS currently has the opportunity to fly on a sounding rocket in FY25 as a technology demonstration instrument. One of the main innovative aspects of TIMS is the capability of a really low noise floor, allowing for the detection of minor ion species in a variety of plasma environments, including planetary magnetospheres (Earth’s included), the lunar environment, the solar wind and even interstellar space, therefore targeting a number of future mission opportunities.

Benefits

The benefit of our Tandem IMS is that it can proposed for a range of missions on the near horizon such an Artemis Lander Mission to the lunar south pole and Artemis lunar orbiter mission. It can be used to measure the ion composition (mass and charge state separation capability) of the solar wind from Mercury to the outer Heliosphere. It can measure the interstellar pickup ions within the heliosphere on a mission to Uranus' magnetosphere, and an Interstellar Probe Mission to measure the plasma environment within the interstellar medium due to its multi-stop low noise design.

Overview

This works is to progress integrated on-chip far-infrared spectrometer technology towards the higher performance required for next generation far-infrared balloon or space astrophysics instruments.

Benefits

Demonstration of a moderate resolution far-infrared on-chip spectrometer.

Overview

We propose to investigate lunar-specific improvements to the design of an orbital swath-mapping lidar based on a new lidar system. The novel measurement approach was successfully demonstrated at 1550nm with a lab and rooftop demonstration in 2022. We are looking to design a lunar orbital version with higher-TRL components than available at 1035 nm. This project will evaluate a modification of the design that would enable the use of existing photon-counting detectors aligned with spaceflight implementation and future maturation efforts. We will also address specific needs related to the data processing for this novel type of lidar.

Benefits

This project will develop a non-mechanical beam-steering lidar system capable of high-resolution swath-mapping.

Overview

We propose to investigate the generation of versatile radar radio frequency (RF) waveforms using the beat frequencies of two locked lasers and then applying an external amplitude and frequency modulation to one laser.

Benefits

This technology development will produce significant size, weight and power, and cost (SWaP-C) savings to future Earth Science remote sensing radar developments.

Overview

X-ray computed tomography (XCT) provides 3D visualization of the interior structure of planetary materials, such as rocks and ices. The proposed work will advance capabilities of XCT instruments to be deployed on landers/rovers. By increasing chemical/structural sensitivity through the use of X-ray filtering and hyperspectral imaging, the proposed work would have applications across Moon, Mars, asteroid, and comet missions.

Benefits

Multiple mission types to multiple planetary surfaces would benefit from an enhanced ability to directly image the interior of rocks and ices. XCT would fill a significant gap in current capabilities. XCT can contribute significantly to answering multiple Planetary Science Decadal Survey priorities as well as Moon to Mars Objectives and Artemis goals. Evidence for accretion, volcanism, impact modification, and hydrothermal activity are all preserved in astromaterials and within the imaging capabilities of XCT. Using XCT in concert with other techniques – such as bulk chemical analyses – would enable much higher fidelity interpretation of chronology, primitive solar system gas/dust reservoirs, origin of water and other volatiles, organics, etc. As such, once the XCT technologies have been developed at GSFC, they can be readily deployed and be highly competitive in multiple mission instrument calls; anywhere there is a lander or rover, XCT will be a possible payload.

Overview

The Mars Campaign Office, Logistics Reduction project called the Trash Compaction and Processing System (TCPS) is a waste management technology. Currently, there are no trash management practices that are being implemented in the space environment other than manual compaction of waste into a plastic bag. The current practice does not recover critical resources such as water, does not prevent the growth of potentially harmful microbiological pathogens, and provides only limited volume reduction.

The objective of the TCPS task is to develop a reliable trash processing system to support long endurance human space missions (target TRL 8/9). The TCPS project plans for an International Space Station (ISS) technology demonstration.

The TCPS objectives are to: reduce volume of trash, safen processed trash to reduce biological activity risks, stabilize processed trash for efficient storage and disposal, and to recover water and manage gaseous effluents. Processed TCPS trash appear as tiles and can be used for radiation shielding augmentation. For a one-year, four-person crew mission, it is estimated that TCPS could recover ~8 cubic meters of habitable volume, produce over 900 kg of radiation shielding tiles, and recover 230 kg of water from ~1,300 kg of trash. Additionally, the tiles could be jettisoned during a transit mission to reduce propellant needs.

FY2012-FY2018

This period saw the development of the Heat Melt Compactor (HMC). The HMC is a full-scale TCPS precursor that was developed to refine previous versions’ trash processing capabilities, finalize operational parameters, and identify hardware issues. During the period between FY2012 and FY2016 various trash compactor prototypes were developed. This included an SBIR Phase 2 Plastic Melt Compactor System developed by Orbital Sciences Corporation (aka Sierra Nevada Corp), and the Generation 1 HMC developed at Ames. In FY2016, a Generation 2 (Gen2) HMC (now called TCPS) with an ISS “flight-like” design was designed and built at Ames. Limited Gen2 HMC ground testing began in 2017 but was not completed due to inability to reach the desired compaction pressure and vacuum. In FY2018, the hardware was repaired to partially restore its desired capability. Several SBIR awards related to the HMC have occurred in the following areas: microgravity-compatible condensing heat exchanger designs, trash bag liners to allow hygienic tiles after HMC processing, and general HMC system design.

FY2019 – FY2021

In FY2019, two contractors were selected for Phase A contracts under the NASA Next Space Technologies for Exploration Partnerships (NextSTEP) Appendix F: Logistics Reduction in Space by Trash Compaction and Processing System (TCPS), Broad Agency Announcement (BAA). The two contractors were the Sierra Nevada Corporation (SNC) and UTC Aerospace Systems (UTAS), also known as Collins Aerospace. Some background information is given here: https://www.nasa.gov/general/nasa-seeks-new-ways-to-handle-trash-for-deep-space-missions/

Phase A was implemented in FY19-20 and completed in FY20. Phase A developed and validated TCPS flight concepts to inform SNC and Collins in flight hardware development. Risk reduction activities at NASA’s Ames Research Center (ARC) HMC facility in support of the Phase A contractors’ work included: gas and water effluent analysis, system operations, product quality, and design analysis including 15 trash processing runs of various trash models. Collins completed their compactor development work in June 2020 and SNC completed their work of a compactor, water recovery, and effluent gas management in October 2020.

In FY2020 and FY2021, the NASA Ames Research Center (ARC) team continued risk reduction activities that included tests of the HMC Gen2 under different operational scenarios. The information gained was used to inform Phase A TCPS contractors as they developed their PDR-lite designs and prototypes. A HMC Generation 3 (Gen3) by SNC was delivered to ARC as part of a SBIR Phase II awarded to Materials Modification Incorporated (MMI). MMI also developed high-temperature, low outgassing, and semi-permeable bags for use with the HMC.

Phase A work was completed in FY2021, but the contract was extended into FY2022.

From here onward the HMC was renamed the TCPS.

FY2022

When processing trash, the TCPS Gen3 outlet gases were fed into the Source Contaminant Control System (SCCS). The SCCS is designed to remove toxic gases such as CO, CH4, and volatile organic compounds. This system consists of an activated charcoal adsorbent bed and a catalytic oxidizer. Precision Combustion Inc. (SBIR Phase II) sized the SCCS catalytic oxidizer for use with the HMC/TCPS.

Testing consisted of identifying species in TCPS outlet gases using a GasMet FTIR analyzer before and after the SCCS. The TCPS ran using unbagged trash. A particulate matter measurement system determined particulates given off during use of the TCPS system. Finally, TCPS processing ran at shorter run times to determine how well a tailored Trash-to-Gas feedstock could be created.

The ARC team worked with Glenn Research Center’s aerosol team to design a particulate matter system to measure and monitor particulates released during TCPS operations: trash loading, tile removal, and handling of the product tiles. The particulate matter system consisted of a SBIR Phase II analyzer which is like current ISS flight hardware. Additionally, semi-permeable trash containment bags from MMI and ISS-approved wet trash bags were tested for their ability to prevent the release of particulates during tile TCPS operations while reducing gas and water contaminants and still allowing water recovery.

FY2023

On Aug. 26, 2022, the NextSTEP Broad Agency Agreement (BAA) Phase B contract modification was awarded to Sierra Nevada Corporation (now Sierra Space) of Madison, Wisconsin. The period of performance is from Sept. 1, 2022, through Aug. 31, 2027, and includes four option periods, ending in an ISS flight demonstration with the possibility for continued use to support ISS operations. The System Readiness Review, Preliminary Design Review, Phase 0 Safety Review, and Phase 1 Safety Reviews have been completed.

Risk-reduction test activities at ARC included characterizing SCCS efficiency for toxin removal from TCPS outlet gases. Tests using Sea-2-Summit nylon bags to contain the trash have been completed. These are the same bags used aboard the ISS. Tests using vapor-permeable bags to see if a greater liquid amount can be removed from the trash were also completed in 2023. The different trash batches (models) are: nominal, high-liquid, high-cloth, and benign. The benign batch is thought to be safe for TCPS outlet gases to vent directly to the ISS cabin without need of SCCS gas processing.

FY2024

The Sierra Space BAA Phase B program completed its Phase II Safety Review and Critical Design Review.

Sierra Space is currently building an Engineering Development Unit (EDU) with completion expected in late 2024. The EDU will be transitioned into a Ground Unit (GU) and will be ready for testing in early 2025. NASA ARC will supply 21 trash batches (5 nominal, 5 high liquid, 5 high cloth, 5 benign, 1 foam) beginning in January 2025 for ground testing. The Flight Unit (FU) was awarded in FY24. The FU will benefit from the GU testing and will be flown to ISS for a technology demonstration in FY27. Ground testing will be compared to the On-Orbit testing to validate the technology.

Work is currently underway to develop a way to send trash batches to the ISS without needing cold storage or freezing of any trash items. The astronauts will only need to add water to a pre-made bag of items to be hydrated. This new technique will be used as part of the January 2025 ground testing.

This year, testing has been completed to determine the amount of water contained in the different types of trash batches. Now when tests are performed either at ARC or by Sierra Space using their Ground Unit, the mass difference before and after testing provide a more accurate assessment of how much water (and other volatiles) were removed. Previous work used an estimated amount of water in the trash batch.

TCPS testing has also been completed using Crew Health and Performance Exploration Analog (CHAPEA) trash. A report is forthcoming. CHAPEA is a series of analog missions that will simulate year-long stays on the surface of Mars.

To expand the list of acceptable items for TCPS compaction, non-typical trash items are being tested in the TCPS. When compacted, these items will not give off toxins after SCCS processing nor will they harm the TCPS system. Tested items include: a running shoe, electric shaver, calculator, flashlight, leather belt, leather gloves, oxygen sensor, open-end wrench, pH strips, and rubber bands. More tests are planned.

Testing is underway with silicone gloves to determine outgassing compounds when heated. Preliminary work has shown that certain gloves will give off CS2. Although concentrations are elevated, they are believed to be below Spacecraft Maximum Allowable Concentrations (SMAC) levels. CS2 can potentially poison the SCCS CatOx catalyst. The source of these contaminants is being investigated.

Upcoming testing includes using more non-typical trash items like inkjet cartridges, adhesives, markers, etc. Batteries, sharps, hazardous materials, and metabolic waste will not be included in these tests.

Another series of tests will determine the outgassing compounds from processed tiles. Current ISS safety requirements have the processed tiles to be bagged. This work will determine if this extra bagging step is necessary.

Trade names and trademarks and company names are used in this report for identification only. Their usage does not constitute an official endorsement, either expressed or implied, by the National Aeronautics and Space Administration

Benefits

TCPS will develop a highly reliable technology primarily for reducing trash volume. TCPS will also recover water from waste materials and produce microbiologically stable, low volume tiles for radiation protection, storage or disposal. For a one-year mission of four crew, it is estimated that TCPS could recover ~8 cubic meters of habitable volume, produce over 900 kg of radiation shielding tiles, and recover 230-720 kg of water.

The TCPS technology would benefit any long-duration operation with limited habitable volume. The goal is to reduce trash volume and microbiologically inactivate it. This will provide less odor generation and improve habitat hygiene. As an alternative to radiation shielding, increased habitable volume, and recovered water, TCPS processed trash could be processed further using trash-to-gas technology to produce methane, or the tiles could be a compact form for trash disposal/ejection from the vehicle.

Overview

This IRAD aims to support high TRL rover lidar system mission infusion while investigating further SWaP reductions through an astronaut wearable lidar design.

Benefits

As NASA pursues its mandate to explore the moon, Mars, and beyond in-situ navigational autonomy for planetary surface operations will be of paramount importance. Not only is this essential for safety and reliability of robotic and crewed missions, but it cuts costs and improves scientific return by decreasing ground control requirements and communication bandwidth.

Overview

We propose to develop an optical detection technique that can be used to measure NO2 with a balloon-borne sonde (in a follow-on IRAD). This IRAD, we intend to see if this measurement works in a lab environment.

Benefits

Ultimately create a small, balloon-borne sonde that measures NO2.

Overview

Electric spacecraft thrusters are closely coupled with the spacecraft electrical, software, and thermal systems, whereas traditional chemical systems have a simpler interface. Integrated testing of smallsats shows that the software is well-defined and cannot harm the hardware, and that noisy output cannot impede the control of the system of a whole.

Benefits

Integrating the flight hardware into an automated test system will allow for a true “test as you fly” approach that generates a meaningful amount of confidence that the control, telemetry, and behavior of the system are rigorous enough to be flown on smallsat missions.

Overview

Development of an ion-electron charged particle sensor.

Benefits

Reduced mass volume and power compared to traditional plasma spectrometers.

Overview

The Fast Neutron Spectrometer (FNS), formerly known as the Advanced Neutron Spectrometer, was developed, built, and operated by Marshall Space Flight Center (MSFC). From 2016 to 2018, it conducted a technology demonstration on the International Space Station (ISS) as an intravehicular neutron environment monitor, with sustained operations until 2023. After its return to MSFC, the FNS flight unit was evaluated and found to be in good operational condition. At the conclusion of the FNS project, the detector was then relocated to Johnson Space Center (JSC) to begin transition of future FNS operations under JSC personnel.

The FNS Reflight Assessment Campaign aims to 1) establish the necessary engineering and scientific expertise at JSC to operate the FNS, and 2) reassess the flight unit to ensure it meets all previous performance metrics and did not degrade during its ISS deployment. There are a number of measurable performance metrics that can be used to fully determine that the FNS did not incur degradation during flight. Degradation of the Photomultiplier Tube (PMT) and Scintillator interface, degradation of the PMT gain stages or high voltage supplies would result in loss of signal gain and resultant shift in signatures, and decreased signal-to-noise performance. These metrics can be measured on the ground at a high precision neutron metrology facility, and would manifest as a reduction in energy dependent neutron detection efficiency. A key component of the FNS reflight campaign will be a measurement of mono-energetic neutrons at Physikalisch-Technische Bundesanstalt (PTB) in Germany. Measurements conducted at that facility will provide data for one-to-one comparisons with the FNS’s performance pre-flight. Once it has been confirmed that the FNS is performing within the necessary performance target, the team will transition to preparing the unit for a reflight opportunity.

Benefits

Typical development of high performance neutron spectrometers require long development times (5+ years) and significant cost ($10+ million), as was the case for FNS and the related ISS-RAD instrument (also operated by JSC personnel). As the only fast neutron spectrometer currently available with TRL8 flight readiness with the potential for reflight, it is imperative that NASA maintains the ability to evaluate and operate the FNS for future missions to retain the significant investment in developing the technology. Maintaining fast neutron measurement capabilities is critical to understanding the harmful effects of chronic radiation exposure on astronauts, including the excess relative risk of cancer and death; neutron radiation contributes an estimated 15-30% of the total effective dose an astronaut is expected to receive over their career, depending on vehicle configuration and environment (LEO, lunar orbit, lunar surface, etc.).

Overview

Project Objective

The Portable In‑Field Acoustic Sensor Array project is focused on the development of the Real‑Time Display 2 (RTD2) Sentinel, a portable, standalone, time‑synchronized acoustic‑intensity measurement system designed to autonomously operate for long‑duration periods and capture data essential for reducing uncertainty in Space Launch System (SLS) liftoff acoustic environments.

Project Description

The Portable In-Field Acoustic Sensor Array project is focused on developing the RTD2 Sentinel, a portable, standalone, time‑synchronized, long‑duration acoustic‑intensity measurement system that enables NASA to collect high‑quality acoustic data in environments where traditional instrumentation cannot be deployed. Built entirely in house, the RTD2 Sentinel integrates Inter‑Range Instrumentation Group time code, Format B (IRIG‑B)-synchronized timing via Global Positioning System (GPS), low‑frequency acoustic‑intensity sensing and a robust active/passive thermal‑management system into a compact, battery‑powered package capable of operating autonomously for a week or more without external power or network connections. This capability allows teams to deploy multiple synchronized sensor arrays around a launch pad or test site and capture detailed acoustic information during critical events.

The project was initiated in response to findings from Artemis I, where post‑flight analysis revealed larger‑than‑expected uncertainties in models predicting duct overpressure (DOP) and low‑frequency liftoff acoustics. These low‑frequency pressure events are especially important because the Space Launch System (SLS) is highly sensitive to them, and accurate predictions are essential for ensuring the safety of the vehicle, crew, and ground systems. To address these gaps, the RTD2 Sentinel systems are being developed to support the deployment of a linear array of ten systems within the Launch Complex 39B (LC‑39B) pad perimeter, positioned outside the plume region but close enough to capture the low‑frequency acoustic source characteristics and signatures that play a role in structural loading and internal vehicle acoustics.

Each RTD2 Sentinel unit consists of a four‑sensor acoustic‑intensity subarray, a standalone data acquisition unit, a GPS‑synchronized IRIG‑B timecode generator, an active and passive thermal‑management system, and a long‑life battery system. These arrays measure not only the amplitude of acoustic pressure but also the direction of wave propagation, enabling the determination of the location, strength, and efficiency of acoustic sources during liftoff. This includes characterizing the complex interactions between engine plumes, the flame trench, and surrounding structures. In addition to acoustic‑intensity measurements, the system architecture is intentionally designed to be flexible and modular, allowing teams to integrate other types of sensors, up to four per system, for measurements such as pressures, strain gauges, accelerometers, or mixed configurations, expanding its usefulness beyond acoustics alone.

The goal of the project is to generate the high‑fidelity datasets needed to improve physics‑based acoustic models, refine prediction tools, and reduce uncertainty in liftoff environments for SLS and future launch systems. These data will directly support updates to liftoff acoustic models, provide validation for Exploration Ground System (EGS) acoustic requirements, and help characterize transient phenomena such as igniter shock and ignition overpressure events. 

Beyond SLS, the RTD2 Sentinel technology is designed for broad applicability across NASA programs. Its portability, autonomy, and modular sensor architecture make it suitable for engine and motor development testing; lunar and Martian habitat testing; far‑field community acoustics; and any scenario requiring synchronized, remote, long‑duration measurements. The project includes the procurement and integration of multiple system components, data acquisition hardware, GPS‑synchronized timing modules, pressure transducers, sensor stands, batteries, thermal‑management hardware, and protective enclosures.

Project Results and Conclusions

The RTD2 Sentinel systems were successfully fielded for the Artemis II campaign, marking the first operational deployment of the newly developed long‑duration, standalone acoustic‑intensity arrays within the LC‑39B Pad perimeter. All units were installed, and the team completed full pre‑launch functional checkouts and configuration verification. Following Artemis II liftoff, the project will analyze the collected low‑frequency acoustic and overpressure data to assess system performance; validate the measurement approach; and begin refining SLS ignition overpressure, duct overpressure, and liftoff acoustic models based on the new dataset.

Benefits

The RTD2 Sentinel systems are expected to significantly enhance NASA’s ability to characterize and model the complex acoustic environments associated with an SLS launch. By providing long‑duration, time‑synchronized measurements from multiple locations within the pad perimeter, the system will supply higher‑fidelity data for validating predictive models and improving vehicle acoustic design margins. These measurements also enable corroboration of existing datasets and support integration into numerical acoustic inverse modeling frameworks, improving the accuracy of reconstructed source fields and propagation behavior. The modular sensor architecture further allows mission‑specific configurations, enabling teams to capture pressure, vibration, strain, and other key parameters alongside acoustic intensity. Together, these capabilities will reduce uncertainty in liftoff acoustics, support safer and more efficient operations, and inform future upgrades.

Overview

Food and nutrition are critical to health and performance and therefore the success of human space exploration. However, the shelf-stable food system currently in use on the International Space Station (ISS) is not sustainable as missions become longer and further from Earth, even with modification for mass and water efficiencies. Bioregenerative foods as part of the astronaut diet are expected to provide whole food nutrition, improve menu variety, and positively impact behavioral health. Significant advances in both knowledge and technology are still needed to inform productivity, nutrition, acceptability, safety, reliability, and operations of bioregenerative food systems. Utah State University's Utah Re-Usable Root Module (URRM) is designed to enable continuous crop production in microgravity. URRM provides a uniform peat-based root zone through continuous monitoring and control of water and nutrients. The system has been used to grow multiple crop cycles in the same substrate using the signal from the embedded water content sensors to inform Ohalo III of root zone moisture status and the need to replenish water and nutrients at frequent intervals to maintain an optimal water/air nutrient balance in the root zone. The Phase B grant advanced the technology and design to demonstrate functionality on the ground with a follow-on contract planned to test the flight design in Ohalo III. Ohalo III is a prototype crop production system that will validate water/nutrient delivery and volume optimization, of candidate root module systems like URRM and advance knowledge on crop production operations which will inform design decisions for a future crop production system intended to be deployed on Deep Space Transit missions.

Benefits

Ohalo III will serve as a platform to develop advance water delivery and volume optimization concepts like Utah State University's (USU) Utah Re-Usable Root Module (URRM) that will enable future crop production operations on long duration exploration missions. USU's Phase B grant advanced the design of URRM and once the design is finalized, flight hardware delivered to ISS, and following the evaluation of URRM in Ohalo III, it may prove to be the basis of the first operational crop production system in space. The integrated system will provide valuable information on the productivity, reliability, and operations associated with growing crops as a component of the exploration food system. In this capacity, Ohalo III and will serve a prototype for the crop production system that is eventually deployed on the Mars Transit Vehicle and will also inform early lunar and Mars surface crop production systems.

Overview

Food and nutrition are critical to health and performance and therefore the success of human space exploration. However, the shelf-stable food system currently in use on the International Space Station (ISS) is not sustainable as missions become longer and further from Earth, even with modification for mass and water efficiencies. Bioregenerative foods as part of the astronaut diet are expected to provide whole food nutrition, improve menu variety, and positively impact behavioral health. Significant advances in both knowledge and technology are still needed to inform productivity, nutrition, acceptability, safety, reliability, and operations of bioregenerative food systems. Sierra Space's Hydroponic/Aeroponic Nutrient Delivery in Volumetrically Efficient Garden (HANDIVEG) is designed to enable continuous crop production in microgravity. HANDIVEG tests volume optimization concepts and uses soilless water and nutrient delivery technologies similar to eXposed Root On-Orbit Test System (XROOTS) https://techport.nasa.gov/projects/94182. HANDIVEG is designed to grow multiple crop cycles. The Phase B grant advances the technology and design to demonstrate functionality on the ground with a follow-on contract planned to test the flight design in Ohalo III. Ohalo III is a prototype crop production system that will validate water/nutrient delivery and volume optimization, of candidate root module systems like HANDIVEG and advance knowledge on crop production operations which will inform design decisions for a future crop production system intended to be deployed on Deep Space Transit missions.

Benefits

Ohalo III will serve as a platform to develop advance water delivery and volume optimization concepts like Sierra Space's HANDIVEG that will enable future crop production operations on long duration exploration missions. Sierra Space's Phase B grant advances the design of HANDIVEG and once the design is finalized, flight hardware delivered to ISS, and following the evaluation of HANDIVEG in Ohalo III, it may prove to be the basis of the first operational crop production system in space. The integrated system will provide valuable information on the productivity, reliability, and operations associated with growing crops as a component of the exploration food system. In this capacity, Ohalo III and will serve a prototype for the crop production system that is eventually deployed on the Mars Transit Vehicle and will also inform early lunar and Mars surface crop production systems.

Overview

Project Objective  

The primary goal of this project is to complete the experimental study for the determination of the corrosion process and rate of cables under different environmental and operational conditions.

Project Description 

This project aims to prevent the possible failures caused by the corrosion of silver-plated copper cables widely used in current NASA systems. The primary goals of this project are: to complete the experimental study for the determination of the corrosion process and rate of cables under different environmental and operational conditions; and to monitor the corrosion status in cables, further validating the nondestructive methods developed by this team in a previous project.

In this proposed project, four objectives are to:
1) Continue experiments to determine the corrosion rate up to a time period of two years and determine the chemical reaction(s) and products generated by the corrosion and study the chemical mechanism of these reactions. The results will establish a solid database to
estimate the corrosion status of a cable, which can help NASA to guide the future practices;
2) Search a commercially available solder so that bonding cables with the solder will minimize/eliminate the increase in the corrosion rate caused by the solder. The selected solder will be recommended to NASA for future fabrication of circuits, which would increase the reliability of the systems, in which silver-plated copper wires/cables are used;
3) Test the corrosion rate of cables under different electrical currents to determine whether there is a threshold of the current, meaning the corrosion acceleration due to the current is very weak when the current is lower than the threshold. If, yes, the threshold current will be experimentally determined for each cable. Based on the results, a recommendation about limit of electrical current to pass through a cable will be made; and
4) Further develop the nondestructive methodology for in-situ monitoring the status of corrosion in a cable. The S-signal of cables will be determined at frequencies from 100 kHz to 3 GHz for the cables treated at different conditions with different times. All four parameters of four signals (i.e., S11, S12, S21, and S22) will be used for the study. At the end, a simple parameter with a well-defined frequency range will be selected to represent the corrosion status of a cable. The patent application about the technology will be updated.

Project Results and Conclusions 

General results are listed below.

•All cables suffer significant red plague.
•For cables (Ag/Cu) bonded with solder (Pb/Sn), the corrosion starts at the junction and then spreads along the cable into areas under insulation and penetrates deeper into the copper core.
•It was experimentally observed that solders with less elements show a slower corrosion.

For cables without DC current:
•Under 90° F and 90% relative humidity, the corrosion progresses along the cable direction (longitudinal) to about 1 inch in the first year while the average corrosion depth across the radius direction (transversal) is about 5.43 microns in the first year for a strand of 230μm-radius.
•Under 70°F and 40% RH, after 1 year, no cables suffered red plague corrosion yet. Therefore, more time is needed.
•With corrosion induced manually in the cables, the longitudinal corrosion spreads is about
3 inches in the first year in cables without solder joints, and about 4 inches in the first year in cables bonded with solder joints.
•The atmospheric depth of corrosion for long-term periods was predicted using the power function and power linear model.