Latest stored TechPort missions and projects from your MySQL import, shown newest first.
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.
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.
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.
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.
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.
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.
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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.
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.
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.
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.
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.
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.
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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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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).
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.
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.
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.
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.
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:
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.
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.
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.
Compact and electrically driven Terahertz-frequency quantum-cascade lasers (THz-QCLs) (~2x2 mm,
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.
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.
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:
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.
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.
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.
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.
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.
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.
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.
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.
CHAPEA is a Mars forward analog with the objectives to:
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:
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.
Development of an ion-electron charged particle sensor.
Reduced mass volume and power compared to traditional plasma spectrometers.
This IRAD aims to support high TRL rover lidar system mission infusion while investigating further SWaP reductions through an astronaut wearable lidar design.
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.
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.
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.
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.
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.
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.
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.
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.
This technology development will produce significant size, weight and power, and cost (SWaP-C) savings to future Earth Science remote sensing radar developments.
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.
This project will develop a non-mechanical beam-steering lidar system capable of high-resolution swath-mapping.
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.
Demonstration of a moderate resolution far-infrared on-chip spectrometer.
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.
Ultimately create a small, balloon-borne sonde that measures NO2.
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.
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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.
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.
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.).
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.
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.
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.
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.
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.
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.
No details available.
No details available.
PURPOSE: The HPSC processor development is nearing completion, and there is considerable interest across NASA is infusing it into future missions. NASA has also led a collaborative effort with industry and other agencies to develop an interoperable, modular, and standard SpaceVPX avionics architecture within the Sensor Open Systems Architecture (SOSA) organizations. To reduce risk for the infusion of a new processor into these missions there is a pressing need to prototype and demonstrate applications on flight-like avionics systems. This flight-like system, referred to as the HPSC Test Kit, is comprised of a chassis, and HPSC single board computer, a power supply, and other peripheral cards conforming to the SOSA standard. This proposed 1-year seedling consists of two related thrusts. First, an RFI will be developed to solicit from industry (a) potential HPSC Test Kit solutions and (b) bounds for cost and schedule. This information will inform the development of an RFP for the HPSC Test Kits. Subject Matter Experts (SMEs) form JPL and NASA will evaluate RFI responses and provide recommendations to JPL. Based on these inputs, JPL will then prepare the HPSC Test Kit RFP. Work will also continue by subject matters at NASA Centers and JPL on the development of card profiles within the SOSA Space Subcommittee (S3C). These profiles can then be referenced within an HPSC Test Kit RFP. Note that the S3C effort is currently funded through mid-FY25 by NESC, funds within this study will extend that effort through the end of FY25. Note that the S3C effort is currently funded through mid-FY25 by NESC, funds within this study will extend that effort through the end of FY25.
No details available.
No details available.
A Small Business Innovation Research (SBIR) Phase III was awarded to Yank Technologies in July of 2025 to develop a TRL-5, Bi-Directional, Dust-Tolerant, 6kW, Resonant Connector System designed to operate reliably in the extreme conditions of lunar and planetary environments. The proposed system replaces conventional interfaces that rely on exposed copper leads, which are prone to high impedance due to lunar regolith accumulation.
This system will be used to connect two lunar elements, such as power sources and loads, including Lunar Terrain Vehicles (LTV), rovers and In Situ Resource Utilization (ISRU) systems, providing up to 6kW of peak power exchange. These design requirements are based on the M2M-30002 Artemis Requirements Document and EHP-10069 Extravehicular Activity and Human Surface Mobility Power Specification.
The tasks to complete this project are:
Develop a vehicle interface that operates at 120 VDC and can be integrated on the vehicle. The exposed side of the interface that connects to the cable shall be dust tolerant.
Develop a dust-tolerant interface on the cable side.
Develop or procure a cable less than 100 meters, but should be greater than 40 meters, and can be carried by an astronaut.
Test and demonstrate operation of the dust-tolerant interface in a relevant environment, using lunar regolith simulant (i.e. GRC-1 or another equivalent). Testing plans include temperature cycling, thermal vacuum (TVAC) testing, Electromagnetic Compatibility and Electromagnetic Interference (EMC/EMI), shock and vibration, and abrasion testing.
Characterize operation using 120 VDCs and 120 VDC at 3kW and 5kW.
Deliver prototype to GRC.
The project is planned to complete by January of 2027.
This task advances the technology readiness level (TRL) of solid oxide fuel cell (SOFC) power system technology for Mars applications, specifically for cis-Mars transits, Mars landers and Mars surface power. Mars missions have emphasized the mass and energy savings resulting with maintaining cryogenic methane (CH4) propellant compared to cryogenic hydrogen (H2) propellant. Converting chemicals into electrical power, fuel cell power systems has proven successful in many applications. The most mature technology for space applications is the low temperature proton exchange membrane (LT-PEM) fuel cell electrolyte chemistry. However, this technology is not directly compatible with hydrocarbon fuels (e.g. CH4), such as those needed for Mars, and requires additional systems to process hydrocarbons and purify the resulting hydrogen before it can produce electrical power. This project will address key technology gaps of electrochemically reacting CH4 and LOX to generate electricity for space applications, specifically for Mars power and surface power needs. The proposed solution is an advanced SOFC system for power generation directly from CH4/LOX propellants. This can allow the use of CH4 or other hydrocarbons and can be thermally balanced at steady state for minimal external thermal management. This system has the potential to meet NASA's key performance metrics, including specific power, long service life, and multi-cycle capability. This activity also leverages lessons learned through past Small Business Innovation and Research (SBIR) grants to advance a required technology for Mars power applications. This task consists of an environmental test campaign of a Mars-focused SOFC power system test article, which includes the Device Under Test (DUT) and the Ground Support Equipment (GSE). The turn-key, autonomous test article will be functionally verified by the vendor prior to delivery to JSC. Multiple test articles may undergo testing. This testing incorporates operational performance testing and environmental testing representing an anticipated Mars mission consisting of a performance testing in a laboratory environment, vibration, shock, and thermal vacuum testing. Thermal vacuum testing consists of a pressure and temperature profile according to a potential Mars mission scenario that involves a start in orbit through landing and ground operation.
Assess the status of the technologies and identification of the toughest technology challenges. Specifically conduct a TRL assessment of the key power transmission technologies and major systems and subsystems. Evaluate the costs associated with the power broadcasting approach in comparison to other surface-based power solutions such as cabling. Document a set of Design Reference Missions (DRMs) for both a demonstration and operational system. This task includes bringing together mission concepts from Moon to Mars architecture teams, STMD, SMD, and technical SMEs at the centers. DRMs will includes cases for Orbit to Surface and Surface to Surface operations. Develop a system-level model that can be used to conduct trade studies. There would be two models created, one for a nearer term demonstration system and one for a larger scale operational system. This will utilize the concept of the ROSETTA model, to develop meta-models of these concepts that could be useful in future technologies studies. A demonstration of the meta-models in a technology process using the technologies identified in the earlier technology assessment will be performed. Additionally, the systems engineering model shall be updated to create a free and open source version using Python or similar with the intention of adding new capability and ease of portability. This work is building upon the original ROSETTA model that was packaged as a macro-enabled Excel file with user settable parameters. The goal of this package is to disseminate to the community at large after approvals. The GRC Compass team will perform a system design calling upon the technology assessments, and advancement degree of difficult assessment, as well as the systems engineering modeling to develop a technology demonstration reference design mission guided by MSFC and JPL.
Maintaining reliable electrical connectivity in dusty environments presents a significant challenge for lunar surface operations. Terrestrial connectors have long been designed to tolerate high levels of contamination, often utilizing high normal forces and wiping actions to remove debris during mating cycles. These design principles are now being adapted for space-rated connectors, where the abrasive and adhesive nature of lunar regolith introduces unique risks to connector performance, durability, and mission success. Preliminary testing conducted at the Simulant Development Lab has yielded promising results using commercially available connectors. Though originally intended for terrestrial applications, these connectors demonstrated encouraging tolerance to simulated lunar dust conditions. Building on these findings, the current effort focuses on identifying and procuring bidirectional power connectors that meet the expected electrical and mechanical requirements for lunar missions. Candidate connectors will undergo rigorous testing with lunar regolith simulants to evaluate their dust tolerance, electrical integrity, and mechanical reliability. A key component of this testing campaign is the development of the vacuum-rated Uniform Dust Deposition System (UDDS). This system features a mechanical and electrical fixture that uniformly applies lunar regolith simulants to connector interfaces. It then performs automated mate/demate cycling while collecting performance data to assess degradation due to dust exposure. The latest iteration of the UDDS includes upgrades that enable testing within a thermal-vacuum chamber, providing a more representative lunar environment. This technology development effort supports the advancement of robust connector solutions for lunar surface systems and contributes to broader dust mitigation strategies essential for sustained human and robotic exploration beyond Earth.
Astrobotic’s LunaGrid system is a groundbreaking solution designed to address the critical need for accessible, scalable, and reliable power on the Moon. With 26 Lunar missions planned over the next six years, many aiming to establish a sustained presence on the Moon, LunaGrid is poised to play a pivotal role in enabling long-term Lunar operations. The system combines two key technologies: LunaRay, a state-of-the-art mission planning software suite, and Vertical Solar Array Technology (VSAT), a 10 kW deployable solar array system.LunaRay, which includes DEMkit, provides high-accuracy Lunar terrain and lighting models, essential for planning the placement and operation of LunaGrid elements in the challenging illumination environment of the Lunar poles. This software suite enables precise site selection, illumination studies, and mission planning, ensuring optimal power generation and distribution.The VSAT system, developed under NASA’s Game Changing Development contract, is a deployable solar array supported by Astrobotic’s Mobility Platform (AMP) rover. The VSAT generates power through static and mobile platforms, with advanced features like electrodynamic dust shields, spacerless multi-layer insulation, and a redesigned deployment mechanism for improved performance in Lunar gravity. The power generated is distributed via Lunar cables and mobile CubeRovers equipped with wired and wireless chargers, acting as mobile power plugs for surface assets.LunaGrid’s modular architecture allows for incremental expansion, evolving from standalone VSAT nodes to a regional power grid and eventually a widespread network. This scalable system will support diverse Lunar missions, including human habitats, ISRU platforms, and exploration of shadowed regions, while reducing costs, risks, and launch mass for customers. LunaGrid is a mission-enabling technology that aligns with NASA’s goals for sustained Lunar exploration and commercial activity.
Reliable power transmission between multiple Lunar or Martian surface elements is essential to Artemis and commercial missions. Missions on the Moon and Mars rely on continuous power for habitats, scientific instruments, rovers, and communication systems. Unlike Earth, where a power grid is well-established, these locations require independent and interconnected energy sources. Surface elements spread across different locations need to exchange power dynamically. Whether it’s sharing excess energy between habitat modules or ensuring rovers stay charged during long-distance travel, a resilient power network optimizes energy usage.Tethered Ultralight Intelligent Power Systems (TULIPS) is a reliable, ultralight DC power grid, qualified for 10 years of operation on the martian surface. The project will design, demonstrate, and qualify the lightest and most efficient power conversion and transmission solution, leveraging JPL’s state of the art TYMPO system. While the full TULIPS system proposes a 0.5 kW, 10 kW, and 50 kW system, this work would focus on the 10 kW system to enable near-term Mars and Moon applications. It will rapidly build a 10 kW transmission system operable on either planetary body.Project Objectives include: Define and document tether power and communications system requirements, including 10 kW power conversion systems, a 1 km tether, 10 kW tether, and spooling system.Develop, build, and perform laboratory testing on a complete breadboard TULIPS system, including assessment of viability of meeting system requirements.Develop, build, and perform laboratory testing on a complete prototype TULIPS system, including verification and validation of hardware performance against system requirements.Perform an end-to-end field test of a deployed 1 km, 10 kW prototype TULIPS system, demonstrating capability of power and communications over long distance in a field setting.Perform environmental qualification for full Lunar TULIPS system.
As NASA plans for the expanded presence of systems on the Moon and Mars, it is important to understand the novel challenges presented by operating on planetary bodies. One of the greatest challenges of operating on the surfaces of the Moon and Mars is the ability to maintain operable temperatures for all of the infrastructure located on the surface. The challenges are particularly difficult due to the extreme ranges of environmental conditions on the surface and wide range of operating conditions for the planned surface systems. The vast parametric space of environmental conditions and use cases makes it difficult to determine the critical technologies worth investment in to enable mission success on the Lunar and Martian surface. To support the continuous and growing presence of surface assets on the Lunar and Martian surfaces, the study aims to investigate a wide range of heat rejection technologies. These heat rejection technologies will be assessed against the vast range of surface assets, each with unique requirements, assumptions, and applications. This ensures that the technologies being assessed are relevant to the future goals of the Moon 2 Mars architecture. This study aims to focus specifically on heat rejection capabilities across the different missions (Lunar and Mars) as well as the different surface elements. The assessment will develop both the ground rules, assumption, and constraints that bound each of these mission and surface elements and compare them against a database of the possible heat rejection approaches including the use of architectural approaches (e.g., regeneration) and specific hardware (e.g., radiators, fluids) needed to meet requirements. The specific project approach includes developing a database of the different heat rejection technologies and surface elements and their associated parameters (e.g., performance, operational temperature, magnitude of heat rejection needed, etc.); develops both qualitative and quantitative figures of merit based on subject matter expert input to asess the different technologies against; and performs parametric based analysis to investigate at a high-level the performance of different heat rejection technologies relative to all of the surface elements' operational space.
NASA’s near-term vision for a sustained lunar presence revolves around the creation of a base at the South Pole of the Moon. A critical technology for developing this lunar base is power generation. Without power generation, future NASA visits to the lunar surface will be very short in duration and likely lack true scientific value. However, generating power is only the first step, delivering power where it is needed is a challenge of equal or greater importance. The task of the Robotically Assembled Light Bender (RALB) Announcement of Collaborative Opportunity (ACO) project was to demonstrate the ability to deploy an asset on the surface of the moon capable of redirecting sunlight to individual power consumers without direct sunlight, e.g. activities within a permanently shadowed region (PSR). Maxar partnered with Langley Research Center (LaRC) for the ACO and took the first step towards realizing the Light Bender vision for power distribution on the lunar surface through the redirection of sun light. The Maxar/LaRC partnership combined skills and experience related to In-Space Assembly (Maxar) and lunar structures and power systems (LaRC) to develop a method for assembling the tandem reflective mirrors (TRM) using Maxar’s robotic arm. During the ACO, the team refined previously designed mast and mirror subsystems to take maximum advantage of the MAXAR robotic arm creating an automatic robotic assembly (ARA) version of Light Bender. Past work at LaRC has demonstrated the ability to create an autonomously deployable mast that is mass and volume efficient. Over the last few years a mast design, with complete set of drawings, was created and a subset of components were fabricated for in house experiments.
NASA is working to expand human presence on the Moon first and then on Mars. Many infrastructures will require structures that need to stabilize and anchor to the surface to improve structural capability and reliability. However, much of this infrastructure will need to be deployed autonomously ahead of human presence on the surface and without human interaction. This research project is exploring the development of lateral stabilization methods to improve the structural margin of vertical masts. This includes actively controlled outriggers or guy wires to be deployed from equipment such as from the base of a vertical solar array (VSAT). The outriggers are implemented as three foldable mechanical arms that are initially secured against the deployment mechanism of the vertical mast to be autonomously erected. The outriggers are spaced 120 deg from each other and extend to a horizontal configuration via linear actuators. The guy wires connect the mast deployer to the mast tip and are paid off by the active controller to guarantee the mast is erected straight and under adequate loading. Once the mast is fully deployed the outriggers will continue to support the mast, increasing its structural stability, and pointing accuracy and stability. The project will fabricate a set of outrigger prototypes and perform functional testing with them to assess their usefulness and performance using an existing representative boom deployment mechanism.The project will also perform an independent study of future ground anchoring systems applicable to VSATs by establishing requirements, technology needs, and provide recommendations for future developments.
1.0 Purpose1.1 The first objective is to provide improvements to the 17 m long composite curing oven at NASA Langley Research Center (LaRC) previously purchased as part of the completed STMD/GCD Deployable Composite Booms (DCB) project. This oven is a unique asset to NASA and a capability that all industry can use to fabricate long slender composite structures. 1.2 A second objective is the design and fabrication of a set of unique molds capable of processing thermoplastic or thermoset composite booms of a larger cross-section than explored before, which are applicable to vertical solar array technologies (VSAT).1.3 A third objective is to design and fabricate tooling to create higher order structural boom trusses capable of longer lengths and loads applicable to larger VSATs than explored so far.2.0 Task Description2.1 Upgrades to the control electronics of the composite curing oven and component replacements necessary to increase the temperature rating for the oven to target the higher processing temperatures required by thermoplastic composites (up to 750°F) will be provided.2.2 A subscale mold (4-7 m in length) of a large cross-section boom will be designed and fabricated along with the ground support equipment (GSE) necessary to lift, rotate, and handle it. Representative thermoset and thermoplastic deployable composite booms will be manufactured to assess performance and capability of the oven and new tooling provided.2.3 A subscale tool (2-4 m in length) used to create truss boom prototypes from individual boom segments will be developed to explore manufacturing feasibility of this higher performance mast design concept.
The Vertical Solar Array Technology (VSAT) project was responsible for partnering with industry to develop solar array technology suitable for use at the Lunar South Pole region where elevation of the array component is of paramount importance to system performance. Three companies—Astrobotic (AB), Honeybee Robotics (HBR), and Lockheed Martin (LM)—demonstrated autonomous deployments and retractions of high-fidelity prototypes in both ambient and high vacuum/temperature extremes in JSC’s Chamber A. Additional environmental tests for Sun-tracking gimbals, dust mitigation, ultra-cold temperatures, bending stiffness and buckling, and tipping were also completed. All three designs included batteries only to survive, but not operate, during assumed worst-case darkness periods of 96 hours. As part of this project a government reference was designed and has been under fabrication at Langley Research Center (LaRC). The VSAT Government Reference Design (GRD) demonstrates the basic concepts involved in autonomous vertical deployment of solar arrays, lessons learned and problems from the first VSAT task, and ensures that the government team is adequately informed about the critical design features embodied in such an effort. The purpose of the GRD prototype is to demonstrate the basic concepts involved in autonomous vertical deployment of solar arrays and to ensure that the government team is adequately informed about the critical design features embodied in such an effort. There are two components for this VSAT GRD activity: 1.) Complete fabrication and assembly of solar array housings and 2.) mate the array housings to the existing VSAT mast and demonstrate deployment of both the mast and the array.
ARPG is a task to develop a project plan outlining the design, manufacture, assembly, and testing of the Heat Source Agnostic Stirling Generator (SG) Testbed and associated multi-convertor controller. Several options for radioisotope power sources may be available to future space missions, therefore a Stirling generator design that can accommodate multiple heat sources is attractive. Two heat source options are the European Large Heat Source (ELHS), fueled by americium-241, and the General Purpose Heat Source (GPHS) fueled by plutonium-238, among other possible heat sources. The Heat Source Agnostic SG Testbed design will include a trade study to select a Stirling convertor, optimization of the convertor operating point to achieve maximum output power, thermal and structural modeling to analyze multiple environments, and consider radioisotope fueling requirements to achieve a realistic generator assembly process. It will include development of a multi-convertor controller. Some primary functions of the controller are AC-DC power conversion and regulation of the power provided to the spacecraft. Notable features of the design will be a centrally located heat source that is radiantly coupled to the hot ends of the Stirling convertors, dual-opposed pairs of Stirling convertors, and passive cooling via a radiator housing. Assembly and integration will occur in the Stirling Research Laboratory at NASA's Glenn Research Center and leverage the experience gained from assembling and testing previous Stirling Generator Testbeds. The notional testing campaign will include a baseline operation test, a performance map, thermal loss testing to characterize the insulation package, redundancy testing to simulate a failed convertor pair, thermal vacuum testing, Radioisotope Power Systems System Integration Laboratory (RSIL) testing, and random vibration testing.
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No details available.
The purpose of ISM-ASTRO is to complete advanced studies and establish increased industry engagement while providing guidance for future in space manufacturing (ISM) investments. This task will focus on metals in space manufacturing, but also consider other ISM areas including verification technologies, recycling, electronics in space manufacturing, and modeling. Overall scope will be tied to the potential for commercial development of ISM capabilities to address NASA and entrepreneurial objectives (for example, logistics reduction and the ability to decrease the number of spares needed to be carried on a mission.) Leveraging of in space manufacturing processes for support of all aspects of sustained space presence are of interest, including, but not limited to, outfitting, repair, maintenance, assembly, construction, and production. Planned tasks include:Issue a Request for Information (RFI) to industry to define the current state of ISM and related processes, identify mission infusion points for ISM technologies that align with existing commercial business plans and goals, including any gaps or barriers to infusion, and determine the most effective near-term actions which can be taken to advance the maturity of these methods in alignment with both NASA's mission and commercial goals.Update In Space Manufacturing strategic roadmaps for the Advanced Materials, Structures, and Manufacturing focus area. Re-evaluate metal manufacturing processes to provide additional information on the potential feasibility for In Space Manufacturing. Utilize build parts to provide a mechanism for relative comparisons. Initiate a new trade study considering the certification/verification process tailored for In Space Manufacturing.Engage with industry/academia through Cooperative Agreement Notice (CAN) collaborative tasks. Engage with Commercial LEO Destination providers to understand microgravity infusion drivers.
This task restores NASA's capability to test Solid Oxide Fuel Cell (SOFC) stack "components" for Mars missions by modifying the methane (CH4) / air SOFC test facility at NASA Glenn Research Center to test developmental CH4 / O2 SOFCs. This is a separate capability from the Energy Systems Test Area (ESTA) at JSC which is focused on systems testing. Given the energy requirements for maintaining cryogenic hydrogen, Mars mission planners have emphasized using CH4 and LOX as the propellant for Mars Entry, Descent, and Landing (EDL). Using the same propellants for generating electrical power necessitates using the high temperature SOFC technology that internally reforms the CH4 into CO and H2 fuel enabling the fuel cell electrochemical reaction. Mars atmosphere does not contain a sufficient oxygen partial pressure to support the electrochemical power generation reaction, so Mars missions require using pure oxygen from propellants. No commercial SOFC currently exists which meets Mars mission requirements as commercial and industrial SOFCs use ambient air to provide the oxidizer for the power generation reaction inside a SOFC stack. Thus, a development activity is required to ensure that NASA has the SOFC technology needed to produce electrical power on the Mars surface in a mass-efficient manner.This task contains three sub-tasks: (1) facility test equipment, (2) test stand modification, and (3) test capability verification. The existing test facility requires new test equipment to safely manage and provide pure oxygen gases to the SOFC test stand. A fuel cell test capability assessment identified modifying the existing FuelCon (HORIBA) test stand to safely condition and deliver pure oxygen to the solid oxide fuel cell test article as the lowest programmatic risk for restoring NASA with this test capability. The final sub-task is to conduct a verification test to demonstrate that the test capability meets NASA's requirements for advancing SOFC technology for Mars missions.
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No details available.
The Flight Test Instrumentation (FTI) portfolio develops and implements capabilities that enable the capture of critical flight data for the validation of models and simulation tools that improve performance, reduce risk, and enable new capabilities for planetary entry, descent, and landing (EDL) missions across the Solar System. Project activities span three technical capability areas:
Novel Instrumentation – Maturation of improved instrumentation technologies for capture of thermal protection system performance, descent system performance, and entry & descent system environmental data. Improvements of interest include enhanced instrument sensitivity & accuracy; capture of datasets more encompassing of system performance; and/or reduction of instrument cost, footprint, and system integration complexity.
Flight Testbeds – Development and demonstration of low-cost, sub-scale flight testbeds for capture of thermal protection system performance, descent system performance, and entry & descent system environmental data. Platforms of interest include those that provide unique data free of ground-based test artifacts and/or enable capture of complex data that are otherwise unobtainable.
Remote Observation – Development of ground and in-flight technologies for remotely capturing spacecraft entry environmental data and characterizing vehicle behaviors during entry and descent. Technologies of interest would allow detailed data capture to validate and mature aerothermodynamics models of spacecraft during entry, aerodynamics models of spacecraft and deceleration systems such as parachutes, and evaluate anomalies through high-resolution imaging.
Maturation and demonstration of technology outcomes will be conducted through rigorous testing – both ground (where applicable) and through internal and external flight opportunities. Technologies have and will continue to be infused into the Agency's strategic exploration and scientific missions and transferred through partnerships to commercial partners.
This task develops and delivers the HPSC System Test Kit, a modular development platform aligned with the SOSA Space Segment (S3C) standard. The Test Kit provides NASA, other government users, and the broader aerospace industry with a consistent and practical environment for evaluating the HPSC processor, integrating early software, and studying system behavior expected in future avionics. It assembles a SOSA compliant chassis, HPSC based Single Board Computers from qualified vendors, supporting cards such as storage and power modules, an I/O interface card, and a management subsystem. Together, these elements create a representative lab system that developers can use well before flight ready hardware becomes available. The technology fills a clear gap within the current HPSC timeline. While the processor and associated software continue through qualification, missions and commercial developers still need a way to examine multicore performance, mixed criticality configurations, time sensitive networking, and integration workflows. The Test Kit provides that bridge by offering a stable platform for running operating systems such as Linux and commercial real time systems, along with flight software frameworks like cFS and F Prime. It supports early bring up, functional testing, and evaluation of application behavior on the HPSC architecture. This reduces downstream risk for NASA programs and gives industry partners a meaningful way to align their own products and designs with HPSC capabilities. The Test Kit also supports national goals around modular open systems and standards based avionics. By aligning with SOSA S3C, the system promotes cross vendor interoperability and helps cultivate a sustainable industry ecosystem built around open architectures. It enables collaboration across NASA, commercial developers, academic groups, and standards bodies by providing a shared reference system for testing, research, and technology maturation. The result is a reusable and mission relevant platform that strengthens the path from HPSC development to real operational use across both government and industry.
The SIPS project incorporates advanced instrumentation (sensors) into solar arrays to monitor the local space plasma environment and inform array operation regarding relevant information about the operating evironment to maximize power output without compromising safety across a variety of spacecraft charging conditions.SIPS improves solar array operations in various charging environments (whether Lunar, GEO, HEO, or Deep Space) through ML modeling and advancing sensor development which expands upon instrumentation developed in a separate Project.The SIPS project aims to improve the existing state of solar array operations through the development of advanced instrumentation that allow environment-informed array operation by demonstrating the ability of autonomous lifetime management using an embedded prognostic capability.The SIPS sensors will be used to monitor arc rates of the array and other relevant information about the operating environment using data from significant test campaigns in the Plasma Interaction Facility, an ML model will be developed to be housed in lightweight microprocessors. This model will be used to tailor array operating levels to the current environment instead of designing the array for worst-case scenario. Not only will this maximize power output without compromising safety across a variety of spacecraft charging conditions, but it will also streamline solar array design by allowing arrays to be standardized. As opposed to being designed for space operations in a specific mission environment, arrays with active sensing and environment-informed operations can be standardized.When operating in the presence of charged particles, solar arrays can experience electrostatic discharge events known as arcs. These arcing events can be highly damaging to solar cells and array components and will result in severe power loss over time if not addressed. In the Space Technology Mission Directorate (STMD) the ECI project Mitigating Arc Inception via Transformational Array Instrumentation (MAI TAI), developed active arc mitigation circuitry that can detect and quench secondary arcs before they damage the array. The SIPS project advances the arc mitigation circuitry to create an "active" solar array that interacts with it's specific environment to provide protection from deleterious effects of it's operating environment. Currently, no advanced solar array instrumentation like SIPS is in use. Typically, "passive" solar arrays are developed as one-off designs for each mission profile, and the Non-recurrent engineering (NRE) costs account for 30%-50% of the final solar array cost to the Project.
As we move to longer duration exploration missions and a sustained presence on the moon and/or mars, the incorporation of both In-Space Manufacturing (ISM) and in-space recycling in mission architectures will greatly enhance mission flexibility and reduce the need for resupply missions. In addition to providing the necessary resources to support and complement mission needs, the ability to recycle materials in space will reduce overall mission costs leading to an increased economic sustainability of exploration missions. To realize this benefit, both ISM and recycling must be developed in parallel as the two capabilities naturally complement each other. The utilization of recycled feedstocks for ISM greatly reduces the mass of feedstock that must be launched. In turn, the availability of ISM technologies increases the viability of recycling by providing a method to turn recycled feedstock into new necessary parts or structures manufactured in space and on non-terrestrial surfaces. The goal of this project is to consolidate prior learnings and multi-center knowledge to establish a data-informed foundation for the efficient material selection and end-of-material-life recycling efforts. This will be achieved through a trade study to determine which high value/impact materials that are already planned to be available as waste could be incorporated into the recycling and manufacturing processes to create new relevant parts or outfitting/construction feedstock. Polymers will be selected based on the likelihood of their availability as a waste material from ISS consumables data and the material properties needed for the recycling and in space manufacturing technologies included in the scope of this study. Specifically, appropriate polymers for both grinding/casting and filament production/FDM printing methods will be selected to ensure the versatility to manufacture different components. A regolith additive will be included as a combination to expand the amount of material that could be produced and target radiation shielding as a potential application.
Automated Additive Manufacturing Inspection, Detection and Repair for Space Structures (AAMIDRSS) will develop an automated defect inspection, detection, and repair (IDR) demonstration for wire-based additive manufacturing (AM) to enable in-space manufacturing (ISM) and a sustained human presence beyond low earth orbit (LEO) by improving confidence in the production and repair of critical components and structures. The system will have sensors mounted on the AM tool capable of detecting common AM defects in newly made or repaired parts. Software will autonomously process the defect data acquired from the parts and determine the defect types and criticality to the parts' structural integrity. The system will determine the best corrective action (if any) and issue repair commands to the AM system to perform a repair action. A final scan will be performed to verify that the repair was successful.Currently, most terrestrial additively manufactured parts for use in-space require strict process control in addition to the printing of large numbers of test samples for characterization and mechanical testing to ensure quality (see NASA-STD-6030). Process monitoring systems exist for some AM processes to flag potential defects but require human-in-the-loop for IDR. Similarly, in-space IDR of damaged parts are performed by astronauts using up precious time or requiring risky extravehicular activity. Automating IDR would improve the quality of AM parts made without direct human supervision and increase the reliability of AM part for both ISM and on-Earth manufacturing. Additionally, the technology decreases the need for human intervention, paving the way for autonomous manufacturing and repair of space structures in remote locations. The technology offers a multitude of potential savings in protecting valuable astronaut's time, decreasing mission risks by maintaining assets, decreasing the need for costly launches of replacement and spare parts, enabling reliable AM (both in-space and terrestrially), and broadening of mission design space with the ability for parts to be manufactured and repaired. Furthermore, the data collected forms a digital record that can be leveraged towards a digital twin.
This Project develops a Surface Power Model to include MATLAB modeling that will help inform design of electrical power systems to enable sustained Lunar and planetary surface power infrastructure. Previous work completed so far includes analytical studies recommending a 3 kV AC electrical power grid for the Artemis power system, and the development of an initial proof of concept breadboard of the universal modular interface converter (UMIC) which is a bidirectional, grid forming inverter intended to connect Artemis assets to this grid. NASA GRC is leading this effort with JSC support responding to modeling and analysis needs for novel Lunar surface power management and distribution (PMAD) systems. Specifically, NASA JSC has expressed a need to model and analyze the PMAD systems of candidate In-Situ Resource Utilization (ISRU) systems.JSC provides the ISRU modeling tools and baseline simulation for testing and evaluation. JSC also provides the training to GRC personnel to understand the modeling environment. The first steps for the Project will be working with JSC on these two items. Then GRC will review the JSC modeling tools (TRICK, etc.) and determine the bet integration of GRC modeling capabilities. For example, can the GRC modeling tools directly integrate into the JSC modeling tools as a complied real time software? GRC will then develop various ISRU power system architecture to meet the power demands for the ISRU studies. GRC will also integrate power system models with JSC ISRU models. Once these tasks are completed, GRC will document the results in a demonstration of MATLAB HIL model simulationand in a Final Presentation ot the GCD Program Office.
The purpose of SPEARS is to research and develop technology on solid‑state batteries (SSBs) as a resilient energy storage platform to survive and operate under extreme environments in space. Expanding energy storage operation temperatures from −40 °C to 150 °C is sought to enable a breadth of missions that could include traversing permanently shadowed lunar craters, cryogenic deep‑space transits, the large temperature swings on the Moon and Mars, or high temperature inner‑planet atmospheric probes. The effort leverages solid-state battery technology developed primarily under the SABERS (Solid State Architecture Battery for Enhanced Rechargeability and Safety) project in NASA's Aeronautics Research Mission Directorate (ARMD). SABERS demonstrated the feasibility of high specific energy chemistry under all-solid-state conditions in prototype cells and pack architectures with rechargeability and wide temperature adaptability. The SPEARS project will . SPEARS build upon this prior work to focus on low‑temperature survival and operation and larger scale manufacturability for commercialization aligns with STMD goals by de‑risking transformational energy storage technologies that reduce mass, simplify thermal control, and open new mission classes.This Project will address (1) mission requirements, (2) fundamental material discovery, (3) manufacturability, and (4) commercialization plans. Collectively, the Project addresses the materials science challenges specific to Solid State Batteries (SSBs) that are identified in recent NASA studies, including low‑temperature ionic conductivity, critical interfacial kinetics, rechargeable chemistry, and scalable manufacturing, but with further design parameters targeting specific space missions. The result will culminate in space worthy solid-state battery designs and module prototypes with identified industry partners. An initial study and pre-formulation effort will be performed to further develop a detailed approach to addressing overall objectives. This study will also identify low temperature equipment availability for fabrication, testing, and scale up feasibility.Materials discovery thrust will synthesize, characterize transport mechanisms, and evaluate performance of novel materials identified as promising low-temperature candidates from the initial study in relevant environments. Cell performance will target an operation temperature range of -40 to 150°C.The manufacturability thrust will identify and develop approaches for laboratory-to-pilot-scale transition for larger formats designed around industry standards and interoperability.
Air Force Research Lab (AFRL) has developed an SBIR/STTR Phase-2 follow-on mechanism dubbed Strategic Funding Increase (STRATFI) to accelerate Phase-2 to Phase-3 SBIR transitions. Multiple AFRL STRATFI investments are pursuing further development toward flight of hypersonic re-entry testbeds that provide mutual benefit to the NASA. The newest STRATFI effort initiated with AFRL and transferred to the Defense Innovation Unit (DIU) is with Inversion Space. This award with Inversion provides advancement of a Mid Lift/Drag (Mid L/D) aeroshell and parafoil system that can benefit several NASA+AFRL shared objectives with a hypersonic testbed, including providing validation data for existing computational models, new deceleration systems models, guided parafoil performance data, and assessment of hypersonic re-entry algorithms. The testbed will also provide NASA with atmospheric entry environments, which are more representative of flight than sounding rocket entries or arcjets, for testing and demonstrating new entry and descent system sensors and evaluating thermal protection system materials.This award with AFRL also continues the NASA/DoD/DoW partnershp in hypersonics research. This award also supports addressing Entry Descent and Landing (EDL) shortfalls 1567: Entry Capabilities for Small-Scale and Commercial Missions as well as shortfall 1572: Performance Optomized Low-Cost Aeroshells for Entry Descent and Landing. Investments in STRATFI help NASA work with commercial partners to develop technologies that have high potential for offsetting mission risk, reducing cost, and advancing existing or creating new capabilities - technology investments that enable NASA’s science and human exploration missions and foster growth and job creation in domestic industries - through partnerships with universities, small businesses, and other Government agencies.
This project is focused on technology development of a polymer-based tribological coating that has previously shown potential for dust tolerance in sliding contacts, as in a cam follower for example. The previous work, which was performed under SBIR phase I and II, will be extended to investigate the coating in rolling contacts suitable for rolling element bearings such as typically used in rotating space mechanisms. The coating system will be investigated in basic tribological rolling contact tests (ex. ball on flat plate) designed to evaluate the effectiveness of the tribological properties of the coating, like friction and wear, under rolling contact. Additionally, full bearing tests with varying environmental conditions including vacuum and dust exposure at the component level will be conducted to evaluate the coating in a relevant bearing geometry. Lastly, a full scale system test is planned wherein a surrogate mechanism (harmonic drive) will be designed, manufactured, and tested to assess the coating system performance on bearings in a full scale mechanism commonly used in space flight hardware. If successful, the work plan will advance the TRL of the coating technology to 5 or 6, making it a potential technology for infusion consideration into NASA lunar surface missions like Artemis III and beyond. The coating system also has additional potential applications in both terrestrial and other space environments. The earlier SBIR work included testing of the coating after aging exposure to Venus conditions, which combined with successful demonstration of tolerance to dust and severe environmental factors in this effort would make the technology attractive to many future NASA destinations, including Mars and Venus. In addition, the contractor established a partnership under SBIR Phase IIe for this coating with a US valve manufacturer, demonstrating a potential commercialization path in addition to the potential space applications.
This SBIR program will mature plasma spray coating technologies developed in SBIR Phase II Program NNSCC21C0514 that were found to be optically stable in the presence of dusty and severe space environments while operating on the lunar surface or lunar orbit. The program will establish processing procedures for coating application of the seven identified material formulations onto three commonly used structural substrates (aluminum, graphite epoxy composite, and carbon-carbon composite), and should evaluate and verify the performance of these applied systems in relevant and bounding conditions for dust mitigation and reflectance stability in UV and radiation environments. These substrates are targeted to support projects in extreme, dusty environments including future lunar surface and orbiting programs radiator designs. Additionally, this effort should define infrastructure requirements to manufacture sufficient quantities of materials to support upcoming NASA missions and establish processing envelops for high reliability performance for applications using the plasma spray technology. The effort will also develop touchup and repair techniques employing new low pH binder systems for plasma and traditionally sprayed systems. Lastly, the program will process engineering development hardware on a variety of typical substrates and validate performance of these scaled up formulations on project hardware. Processing protocols and standard operating procedures will be developed for each of the formulations on the different hardware substrates and configurations, thereby providing a straightforward processing pathway for the different mission goals. The results of this program should sufficiently elevate the maturity of the coating technology and identified material systems to a level for insertion into a Lunar flight project demonstration test and/or flight mission.
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The purpose of this task is to establish a Hydrogen (H₂) / Oxygen (O₂) Dirty Thermal Vacuum (DTVAC) test chamber capability that can safely handle potentially significant H₂/O₂ leakage. Currently, there is no Lunar or Mars TVAC chamber with this capability. The proposed capability will enable the controlled introduction of nitrogen (N₂) into the TVAC chamber volume to dilute and reduce H₂/O₂ concentrations below the flammability thresholds of H₂. The capability to precisely control and manipulate hydrogen and oxygen in a vacuum opens new frontiers for fundamental and applied research. This approach allows for safe operations while maintaining relevant Lunar and Mars vacuum environments at the following conditions:
Lunar vacuum: 1.0 × 10⁻⁴ to 1.0 × 10⁻⁵ torr
Mars vacuum: ~6 torr
This upgrade will close a critical gap in the ground testing infrastructure available to the Space Technology Mission Directorate (STMD) for hydrogen/oxygen-based power systems. Without this capability, it is not possible for ground testing to increase the Technical Readiness Level (TRL) of a system to 6 (requires a demonstration in a relevant environment).
A survey of available chambers at the Johnson Space Center’s (JSC) Energy Systems Test Area (ESTA) was completed to determine which chambers have a majority of the desired test environment available. Existing lunar and/or Mars chambers will be upgraded to handle H2/02 leakage as follows.
Lunar Chamber: Add a second turbo pump to the Lunar TVAC chamber to tolerate higher H2/02 leakage without impacting vacuum levels.
Mars Chamber: Upgrade the vacuum pump system, the Martian gas mixture capability, and the gas mixture analysis system.
No details available.
No details available.
The Accurate Lunar Surveyor and Terrain-mapping Autonomous Rover (ALSTAR) project is developing a brassboard Light Detection and
Ranging (LiDAR) sensor that will be used for characterization and demonstrations for autonomous Lunar rovers. This brassboard unit will
be designed with Lunar environment considerations, including utilizing a Lunar dust mitigation mechanism and possessing a broad operational temperature range. The ALSTAR LiDAR's performance will be evaluated under realistic terrain operational conditions at the JSC Rockyard, using existing rover platforms. ALSTAR is a 3-D Imaging LiDAR sensor with integrated real-time image processing algorithms used to enable autonomous surface mobility operation and to produce high resolution terrain maps. The system leverages the Terrain Sensing LiDAR (TSL) that has been developed at NASA Langley Research Center (LaRC) and has successfully demonstrated precision navigation and hazard detection during rocket-powered vertical test bed, drone and helicopter flight tests. The ALSTAR LiDAR will operate as a “standalone sensor” to survey local terrain and detect obstacles (rocks, holes, and human artifacts) for optimum route planning, and to provide relative position, heading, and velocity data to enable autonomous navigation. The hi-resolution elevation maps produced by the ALSTAR LiDAR will also support resource exploration and investigation of scientifically interesting locations. For example, ALSTAR will be capable of generating 3-D maps of caves that may contain water ice or can be used as shelters. Additionally, ALSTAR can identify docking port markers and provide proximity, bearing, and velocity data for habitat mating. The basic functionality of the ALSTAR LiDAR sensor has already been demonstrated using a breadboard at the LaRC LiDAR test range.
Establishing trust in autonomy technology is always a challenging task. The CARMEL project, led by Ames, is a multi-center/industry collaboration with GSFC, LaRC, JSC, Blue Origin, and Red Canyon Software Systems, which aims to create a certification process using an assurance-centric approach, where a structured argument is the organizing focus for justification of a system's properties. This approach promises to be more flexible and adaptable for NASA and commercial providers to get technologies certified for space missions. The assurance case approach allows the provider to give confidence to stakeholders that the autonomous system meets its objectives and operates safely and reliably, thereby building trust by showing stakeholders that the risks are acceptable. The assurance case approach has been adopted in an increasingly wide range of safety-critical industries, such as transportation (including road, rail, and air), oil & gas, military defense, medical, and food & drugs, in order to demonstrate that a product is acceptably safe and effective for its intended use, helping regulators understand complex systems, map out risks and mitigations logically, and build confidence for stakeholders. In the US, assurance cases have been applied by the FAA for performance-based approval of UAS operations, the Nuclear Regulatory Commission (NRC) for nuclear waste disposal, and the FDA for infusion pumps. In recent years, NASA has begun to commercialize at the program level by making use of commercial transportation services and commercially developed launch vehicles, operated by commercial providers rather than by NASA. This changes NASA's acquisition strategy by making essential use of contractors in a different manner. The NPR 7120.5 program and project management requirements are no longer practically applicable given that NASA does not oversee the design, development, testing and evaluation (DDT&E). The need to accommodate new commercial acquisition models motivates the need to evolve NASA’s safety and mission success (S&MS) framework to use the assurance case regime, that is objectives-driven (bringing focus on clear objectives through a structured framework), risk-informed (using risk analysis for decisions), and case-assured (requiring a documented, evidence-based argument that objectives are met). The CARMEL project will conduct a case study on a reference mission, inspired by the report of the Autonomous Navigation Demonstration Relevance Assessment Team (ANDRAT) commissioned by the SMD, flying a single spacecraft in cislunar space exercising Level 3 autonomy (without Earth dependence during nominal autonomous navigation, but contacting ground operations during off-nominal navigation). Using this reference mission, we will develop an assurance case to build trust in autonomous navigation systems. This assurance case will serve as an exemplar assurance case for autonomy missions. Through this case study, we will develop a certification process, along with metrics, measures, and V&V strategies for certifying autonomy technology using an assurance case approach, as well as assurance technology, a software toolset to help projects throughout the process. Finally, we will infuse our assurance case methodology and technology in the commercial US space industry through publication and outreach, as well as by soliciting feedback throughout the project development.
None listed.
DIsk-Shaped Configurable and Modular vAcuum uNit (DISCMAN) is one In Space Manufacturing (ISM) project advancing in-space welding technology development. The DISCMAN payload is a compact, modular vacuum chamber designed to support in-space laser beam welding (LBW) technology maturation through ground, parabolic, and potentially in-space flight testing. This demonstration will simultaneously investigate the influence of reduced gravity and pressure on this process. In-space welding (ISW) is vital to joining & repairing structures in Earth orbit, on the surfaces of the Moon & Mars, and during transit. The DISCMAN vacuum chamber contains a sample cartridge with a rotating platen that holds metallic coupons, sheets, and other materials. A laser welder fires through a window on the laser enclosure into the sample cartridge to perform welds while the samples remain under high vacuum. Thermocouples are placed within the cartridge in contact with the workpieces while welding & thermal cameras monitor the process through the chamber window. The sample cartridges are swappable and removable, allowing for numerous sample configurations and the return of samples to Earth for detailed materials diagnostics testing. Weld samples could include shear, butt-lap, or bead-on-plate line or spot joints in a variety of relevant metal alloys. An orbital demonstration with DISCMAN will provide information that increases confidence in the use of LBW technology on future on-orbit or non-terrestrial missions. Process data captured during the demonstration will also validate datasets for computational models, inform the development of future LBW controls and equipment suitable for flight, and reduce risks associated with goals to advance ISW as a NASA mission capability.
High-speed Intelligent Robust Autonomous Terrain Exploration (HI-RATE) will demonstrate robust, high-rate, autonomous surface mobility for future planetary surface missions. The project will develop software for autonomous navigation onboard planetary rovers, leveraging advances in perception sensors and high-performance space computing to provide high-speed autonomy to drive farther faster and with less need for human operator intervention. Utilizing existing robotic mobility platforms, the team will integrate these various subsystems into a system for a long-range demonstration in representative proving grounds.
Taking advantage of new flight-worthy sensors like rover-capable LIDAR sensors combined with a new generation of high-performance space computing, HI-RATE will go beyond the kinds of navigation algorithms used by current planetary rovers like Perseverance or VIPER to adapt cutting edge self-driving car technologies to the unique challenges of planetary surface mobility of the Moon and Mars.
Several infusion paths are explored as part of the HI-RATE effort through engagement with existing study contracts and creating new Workshop opportunities. Infusion paths include: the Exploration Systems Development Mission Directorate (ESDMD) Strategy and Architecture Office (SAO) to collaborate with the NextSTEP-2 Appendix R surface logistics studies, the Extravehicular Activity and Human Surface Mobility Program (EHP) on benefits to the Lunar Terrain Vehicle, Pressurized Rover, and the SMD Endurance pre-Phase A team to work specific infusion details. HI-RATE also seeks to identify additional infusion paths through planetary community groups such as LEAG and MEPAG. Discussions with Commercial Lunar Payload Services (CLPS) are another avenue for commercial engagement. It is expected that a number of new opportunities for infusion will be exposed through industry engagement.
The SIIMPLE project is developing technologies and designs for modular batteries for the Moon and Mars. Batteries provide power to many space applications, such as Extravehicular Activity suits, rovers, and habitats where other sources of power may not be readily available. A modular battery would be swappable across these platforms, such as a rover on a multi-day mission with a depleted battery swapping for a replacement battery at a solar array station and leaving the “empty” battery behind to be recharged for the return trip or another customer/mission. Typically, each mission develops its own battery based on a set of requirements and interfaces are not standardized, so the batteries are not swappable across vehicles or missions. A modular battery would allow for swap ability across missions, enable second-life use cases when batteries are still usable, improve reliability and reduce development resources. A trade study will identify the best use cases and requirements to finalize a modular battery design that extends across both Lunar and Martian missions.The overall goal of the SIIMPLE project is to provide a preliminary design for a modular battery that has plug-and-play extensibility across multiple mission platforms and use cases. SIIMPLE will perform a trade study to determine the most widely applicable parameters across relevant Lunar and Mars missions to finalize modular battery requirements. Technology investigations and demonstrations will be performed to evaluate next-generation cell technologies, thermal management techniques, safety components, and packaging concepts. Deliverables include a power trade study technical memorandum and a technology demonstration summary. The proposed technology demonstrations and modular battery design will make progress towards closing modular battery needs/gaps for the Lunar surface and future Mars missions and allow informed investments for future prototype demonstrations.
This initiative centers on the development and deployment of a High-Performance Space Computing (HPSC) system based on the Microchip PIC64 integrated within a modern time sensitive Ethernet network framework. While the PIC63 HPSC offers a substantial advancement in computational capabilities for space missions, enabling applications and scientific objectives previously unattainable with existing solutions, it is essential to recognize that HPSC is one element within a larger architectural context. This project aims to deliver foundational reference architectures that missions can utilize, addressing a broad array of architectural requirements and mission objectives. By providing these pre-designed architectures, missions can concentrate on their specific goals rather than the underlying system design.The project will create multiple HPSC system architectures tailored to the needs of emerging space and industrial applications. These architectures will address specific architectural drivers, including distributed and centralized systems, high fault tolerance, sensor aggregation, real-time processing, and legacy interface requirements. This approach will provide NASA with direct experience and critical knowledge of how to effectively apply the HPSC Time-Sensitive Networking (TSN) Ethernet infrastructure and its ecosystem to complex challenges, without reliance on any single industry partner's architecture. This effort will also serve as a catalyst for NASA to cultivate relationships with industry and academia, fostering an independent ecosystem for future developments that benefit NASA. The TSN Ethernet architectures developed in this project will be shared with industry, and collaborations will be pursued to drive use case solutions that align with NASA’s strategic plans.This initiative includes developing prototypes, demonstrating functionality, and benchmarking the architectures both in absolute terms and against existing products. This will provide NASA and industry with static and dynamic metrics derived from active HPSC-based systems. Prototyping will leverage industry solutions at the subsystem level while maintaining NASA’s ownership of the overall architectures. Special emphasis will be placed on applications requiring high fault tolerance, exploring architectures for Size, Weight, and Power (SWAP)-optimized fault tolerance solutions. Cybersecurity will be addressed within the proposed architectures, recognizing its growing importance for space-based assets. The architectural choices will examine the overlap between fault tolerance, security, and testability to identify areas of commonality and efficiency in the architectural decisions.
Currently, surface rover navigation relies on a combination of stereo imaging, inertial measurement units (IMUs), and sun-dependent visual odometry. While these methods have proven effective in past missions, their performance is constrained by lighting conditions and can degrade in low-illumination environments. In contrast, 3D LIDAR enables lighting-independent depth sensing and provides higher spatial precision, allowing for more reliable, autonomous, and higher-speed navigation across varied terrain. Despite the widespread availability of terrestrial LIDAR systems and prior investments by STMD, no past NASA surface rover mission has selected LIDAR as a primary navigation sensor. In cases where LIDAR is being considered, particularly in commercial lunar missions, current implementations often rely on unproven terrestrial systems with limited environmental qualifications. This results in considerable residual risk on the transition to flight readiness. LIDAR Line-up Assessment for Upcoming Navigation Challenges to Help Ease Risk (LIDAR LAUNCHER), is an initiative to survey, test, and road-map 3D LIDAR solutions for surface mobility missions. The objective is to bring together a broad set of stakeholders from sensor builders to mission developers to identify technical needs, assess performance gaps through quantitative testing, and establish a clear path for LIDAR technology maturation and infusion into future commercial and NASA missions. The expected impact of this effort is multifaceted. It will provide STMD with valuable insights to inform future investments in LIDAR technology maturation. By enabling direct collaboration between LIDAR developers and mission teams through shared facetime and test data, the project supports the identification of high-potential, near-term navigation applications while helping to mitigate adoption risks. Furthermore, this project aims to foster a nascent planetary ‘autonomous driving’ community between NASA and industry, acting as a force multiplier for future navigation development through the public release of best practices, performance metrics, interfaces, test data, and software.
Stereo imaging of Plume Surface Interactions (PSI) during and through CLPS lunar descent and landing. High frame-rate imaging is to begin at an altitude above where PSI onset is expected in order to capture the morphology of the disturbed terrain. This imaging continues through lander descent in order to capture PSI onset, measure morphology changes, and determine the extent of surface obscuration. High frame-rate imagines continues through landing and dust settling in order to capture the morphology of the disturbed terrain after PSI. Additional imaging during the surface mission will also be collected in order to improve post-landing morphology through changes in the ambient lighting, including shaddowing effects. Photogrammetry is used to measure the surface morphology and thus estimate the extent of PSI erosion and site alteration. The collected data in-situ flight data can then be used to validate and anchor PSI computational and engineering models currently being developed in support of various system (including lander, surface and orbital) and system architecture designs. The SCALPSS 2.0 payload hopes to improve upon the successfull SCALPSS 1.1 payload which was formally selected for development as part of the CLPS 19D mission awarded to Firefly Aerospace which launched in January 2025 and landed on 2 March 2025, and the SCALPSS 1.x payload which will be delivered to Blue Origin for integration to the first Mk1 test flight planned for mid-2025 as part of the CLPS CT-3 mission. The SCALPSS 2.0 payload will utilize new electronics to improve data management and higher resolution cameras for improved science data.
Successful exploration of the lunar surface, martian surface and beyond by humans and robotics will require significant power generation. One of the best options for high level power generation is a nuclear fission reactor which can produce large amounts of power during the day and night on the lunar surface; however, it will also produce significant amounts of waste heat that will need to be rejected. A liquid droplet radiator is one option for effectively radiating this waste heat to space. This type of radiator will minimize mass over conventional panel-based radiators and require minimal deployment enhancing the feasibility of using nuclear power on the lunar surface and other locations in the solar system. The liquid droplet radiator could also be used as the heat rejection capability for some In Situ Resource Utilization (ISRU) processes. This study will establish the feasibility of the liquid droplet radiator concept in conjunction with a nuclear fission power system on the lunar surface and look at its applicablility for missions beyond the moon such as Mars and the moons of Gas and Icy Giants. A system study that compares a nuclear fission reactor using a conventional radiator system to the liquid drop radiator will be done for a lunar habitat and ISRU power system mission in conjunction with the NASA Glenn Reseach Center (GRC) COMPASS team. The plan is to leverage lunar fission surface power studies to investigate the design, benefits, costs and feasibility to deploy a liquid droplet radiator as an upgrade to traditional radiators.
The regolith simulant project consists of simulant experts from many NASA Centers and the Johns Hopkins University Applied Physics Laboratory (JHU-APL), with particular experience and scientific backgrounds relevant to simulant design, production, and use. Together, the team serves as the Agency's Simulant Advisory Committee (SAC). The tasks for the project team include 1) providing simulant consultations and recommendations for Game Changing Development (GCD) Program-funded projects. In addition, numerous non-GCD projects have reached out to the committee for advice and are supported as resources permit; 2) provide simulants in small amounts (less than or equal to 10kg) to GCD projects, and work to get future larger simulant needs defined and funded; 3) publish a NASA Technical Memorandum update of the NASA Regolith Simulant User's Guide, soon to include martian simulants as well as lunar simulants; 4) participate on the NASA Simulant Advisory Committee bi-weekly meetings; 5) collaborate with JHU-APL's Lunar Surface Innovation Consortium (LSIC), including participation in LSIC's Lunar Simulants Working Group; and 6) familiarization and interaction with the HLS-UG-001 Human Lander Systems User's Guide, Human Lander Systems Lunar Thermal Analysis Guidebook (LTAG), NASA-STD-1008 Dust Mitigation Standard (the SAC is actively updating this document), SLS -SPEC-159 Cross Program Design Specification for Natural Environments (DSNE), Lunar Thermal Environments Task Team (LTETT), and NASA/TP-20220018746 Lunar Dust Mitigation: A Guide and Reference. Previous efforts of the team included 1) publishing an update to the Lunar Simulant User's Guide, 2) vetting previous public simulant database documents for compilation and eventual release likely on LSIC's website, 3) performing a survey of GCD-funded and LSIC-related projects that utilized simulants as to their needs, which included the types of simulants as well as their quantities; 4) working in collaboration with commercial simulant providers to achieve improvements in commercially available simulants to better meet NASA's needs, specifically in the creation of the highest fidelity lunar highlands simulant produced to date; 5) characterizing available simulants and comparing them in terms of how well they replicate specific aspects of regolith utilizing Figures of Merit methodology; and 6) distributing small amounts (less than or equal to 10kg) to simulant users and assisting in the identification of sources of larger quantities of regolith simulants.
This task involves conducting a multi-center study in FY25 to assess the performance and feasibility of autonomous systems in relation to Artemis architecture needs and M2M objectives. The study will elucidate the Strategy and Architecture Office (SAO) Lunar Architecture Team (LAT) evaluations for STMD Autonomous Systems & Robotics (AS&R). The team will integrate prior STMD-funded efforts and existing commercial/academic partners to establish a broad base of expertise for formulating future development efforts. Key outcomes will include identifying technologies requiring further development and formulating forward efforts to advance autonomous systems capabilities and other architecture-driven autonomous systems use cases leading to transition to industry for NASA and commercial mission applications. The study will consider the following STMD AS&R Shortfalls: 0680: Robust Robotic Intelligence for High Tempo Autonomous Operations in Dynamic Mission Conditions1304: Robust, high-progress-rate, and long-distance autonomous surface mobility1530: Aerial Robotic Mobility and Onboard Intelligence for Expanded Capabilities on Mars, Venus, and Titan1532: Autonomous Planning, Scheduling, and Decision-Support to Enable Sustained Earth-Independent Missions1533: Autonomous Robotic Sample Identification, Classification, Collection, Manipulation, Verification, and Transport1535: Autonomous Vehicle, System, Habitat, and Infrastructure Health Monitoring and Management1536: Free-Flying Mobility Aids for Crew EVA1537: Free-Flying Systems for Robotic Inspection, Data Collection, and Servicing of In Space Assets1538: General Purpose Robotic Manipulation to Perform Human Scale Logistics, Maintenance, Outfitting, and Utilization1539: Intelligent Robotic Systems for Crew Health and Performance During Long-Duration Missions1540: Intelligent Robots for the Servicing, Assembly, and Outfitting of In Space Assets and Industrial Scale Surface Infrastructure1541: Intuitive and Efficient Human-Robot Interaction for Safe Teaming and Remote Supervisory Control1542: Metrics and Processes for Establishing Trust and Certifying the Trustworthiness of Autonomous Systems1543: Multi-Agent Robotic Coordination and Interoperability for Cooperative Task Planning and Performance 1544: Resilient Agency: Adaptable Intelligence and Robust Online Learning for Long Duration and Dynamic Missions1546: Robotic Mobile-Manipulation for Autonomous Large-Scale Logistics, Payload Handling, and Surface Transport1548: Sensing for Autonomous Robotic Operations in Challenging Environmental Conditions1625: Intelligent Multi Agent Constellations for Cooperative Operations With consideration given to the following for AS&R coherence:1336: Robotic Mobility for Robust, Repeatable Access To and Through Extreme Terrain and Surface Topography1531: Autonomous Guidance and Navigation for Deep Space Missions1545: Robotic Actuation, Subsystem Components, and System Architectures for Long Duration and Extreme Environment Operation1547: Robotic Systems for Sub-Surface Access Through Ice and Ocean Mobility
For FY25 there are 3 discrete elements of work to be performed under the TPS Portfolio study. The primary element is to produce an investment strategy, roadmap, and customer engagement/transition plan for NASA investments into TPS material developments that best support Science, Human Exploration, and commercial entities for FY26-31. These products shall be delivered to the Deceleration Systems Capability and the Land Domain leadership. A draft strategy with technology objectives and a cost phasing plan shall be delivered in support of PPBE27.The secondary element is to produce a white paper study on “Alternative TPS Options for Orion”. This effort supports near-term Human Exploration objectives within NASA. This is a separate effort from the NESC work regarding investigation of the Avcoat Char Loss during Orion 1 re-entry. This effort seeks to identify potential TPS alternates to the Block Avcoat should NASA opt to switch the TPS for future missions, i.e. AR3 and beyond. This report shall be delivered to the Deceleration Systems Capability, Land Domain. The third element is to produce a test/development strategy for a Scalable/Tiled Conformal PICA TPS heatshield that can support Aerocapture, Moon to Mars and High-Speed Earth Return for aeroshells > 1.5m diameter. While Tiled Conformal-PICA has been flight demonstrated (VARDA) for heat fluxes < 200 W/cm2, aerocapture missions, Moon-to-Mars architecture, and high-speed sample return may require an aeroshell capable of ~1500 W/cm2 and 1.3 atm. Therefore, a C-PICA system with gaps/seams requires a solution proven to higher conditions. The Scalable/Tiled C-PICA development strategy shall be delivered to the Deceleration Systems Capability and the Land Domain leadership. A draft strategy with cost phasing plan shall be delivered in support of PPBE27.
Multiple AFRL STRATFI investments are pursuing further development toward flight of hypersonic re-entry testbeds that provide mutual benefit to the NASA LAND Domain. The newest STRATFI effort with Outpost Technologies Corp provides advancement of a deployable aeroshell and parafoil system that can benefit several NASA+AFRL shared objectives with a hypersonic testbed, including providing validation data for existing computational models, new deceleration systems models, guided parafoil performance data, and assessment of hypersonic re-entry algorithms. The testbed will also provide NASA with atmospheric entry environments, which are more representative of flight than sounding rocket entries or arcjets, for testing and demonstrating new entry and descent system sensors and evaluating thermal protection system materials. The development, integration, and flight test execution of a mechanically deployed hypersonic decelerator from Low Earth Orbit (LEO) will provide valuable mission relevant performance data of the high temperature fabric forming the primary drag surface of the decelerator. Flight data associated with the performance of thermal protection systems will be used to validate material response models and correlation with representative ground tests used in system development. Recovery of the entry vehicle and decelerator will enable direct material evaluation of the thermal protection system after exposure to the stressing temperatures and aerodynamic loads experienced during entry.The task will focus on enabling NASA access to data on the performance of the hypersonic decelerator and the ability to test LAND technologies, primarily in thermal protection systems. The task will be led and supported by subject matter experts who will attend partnership meetings and review and keep the LAND Domain apprised of the program status and opportunities.
Multifunctional Nanosensor Platform (MNP) is an ultra-compact, light, low-power and highly sensitive instrument for the in situ detection of gases and volatiles. The instrument includes an array of independent gas sensors that are read simultaneously. The operating principle of MNP is simple with no preprocessing of the sample required. As the sensor surface interacts with a target gas species, its electrical properties change, which is measured by the readout. The high surface-to-volume ratio and low electrical noise of MNP sensors result in high sensitivity. This enables the senor to detect extremely low concentrations anticipated on the Moon. The selectivity to target gases is induced by functional groups on the sensors that specifically interact with those species. MNP can be reset by heating the sensors when necessary.The small Size, Weight and Power (SWaP) of MNP allows it to be onboard a small rover and measure exhaust plumes as a function of time and distance from the lander. The lander is known to generate a significant amount of outgassing, which makes it challenging to use any measurement of the volatiles taken on the lander to study the plume-surface interactions. The ability to move away from the lander and measure volatiles directly above the lunar regolith will allow MNP to study plume-surface interactions and better understand the impact of lander-generated volatiles.Under this project, a completely standalone MNP instrument is customized to interface with a small rover provided by the Australian Space Agency, fit within a tight mass and power allocation and operate on the Moon. The sensors within the instrument are customized to make sensitive measurements of the exhaust plume expected in the lunar environment.
Aerocapture is a maneuver that uses the aerodynamic forces generated during an atmospheric pass to decelerate an entry vehicle and deliver an orbiter into an elliptical orbit from an interplanetary trajectory. As the entry vehicle approaches the planet, its cruise stage directs it on a path towards the planet's atmosphere. The entry vehicle is comprised of an aeroshell with thermal protection system that houses the orbiter and its science payload. Once the entry vehicle is on its path to the intended atmospheric entry conditions, the cruise stage is jettisoned, and the entry vehicle continues under its own control. After reaching the atmospheric interface point, the aerodynamic lift and drag forces acting on the entry vehicle begin to build and are used to continually maintain the vehicle's path along a specified trajectory through the atmosphere. The trajectory is designed to dissipate a specific amount of energy and reduce the vehicle's velocity for the targeted science orbit. The entry vehicle exits the atmosphere, and the aeroshell opens to expose the orbiter which is then released. The orbiter, which has now been "captured" into orbit, conducts two additional maneuvers. The first maneuver is to circularize the orbit by raising the orbiter's periapsis with a propulsive burn conducted at apoapsis. The second maneuver is another propulsive burn conducted at periapsis to clean up residual errors and place the orbiter into its final science orbit. The entire aerocapture process is completed within the time frame of a single orbit. The key supporting technologies addressed by the ARRIVAL mission that are needed to implement an aerocapture maneuver include aerodynamic devices, entry vehicle systems, and guidance, navigation, and control algorithms necessary to accurately modulate the aerodynamic forces and maintain the entry vehicle on the aerocapture flight path through the atmosphere of the targeted planetary body.
The Materials and Processes Technical Information Service (MAPTIS), located at maptis.nasa.gov, includes a database of the Materials International Space Station Experiment (MISSE) results. This database with well over one thousand sample records has valuable information such as beginning of life and end of life optical properties used in thermal modeling and atomic oxygen erosion yield. It currently only has data for MISSEs 1 through 8. This effort is to update the MISSE in MAPTIS database as much as possible with the more recent MISSE flights utilizing the Materials International Space Station Experiment Flight Facility (MISSE-FF), a commercial platform for materials experiments, up through MISSE-18. Personnel at Marshall Space Flight Center, Glenn Research Center, and Langley Research Center are cooperating in this effort. The investigators have flown multiple experiments and have previously worked with the MAPTIS database curators to create appropriate records. The investigators will provide preflight and postflight data, which may include mass changes, optical property changes, mechanical property changes, electrical conductivity or static-dissipative property changes, normal light photos to document visual changes, black light photos to document fluorescence shifts, and other data of interest to spacecraft designers. If the material did not survive the flight, that shall be noted. If the material results are proprietary or export-controlled, that shall be noted. More recent results from MISSEs 1 through 8 shall also be included. This also promotes use of the other data in MAPTIS, such as outgassing, offgassing, toxicity, flammability, fluid compatibility, and sensitive optics compatibility testing results for a variety of materials.
The study's objective is to evaluate the feasibility and state of the art (SOA) of in-situ surveillance monitoring and control for additive manufacturing (AM). The technology is important for terrestrial AM and enabling for in-space AM. A foundational framework for addressing gaps of real-time in-process defect detection within AM machine builds will be established. Initially focusing on the laser powder bed fusion and directed energy processes, this effort aligns with NASA's strategic goals of advancing in-situ process monitoring for reliable qualification of AM parts, especially in space environments. The study encompasses a feasibility assessment to determine the sensitivity of AM defects on mechanical properties, focusing on the laser powder bed fusion process but broadly applicable across AM methods. Deliverables will include: (1) A report identifying technical gaps for in-situ process monitoring that support AM qualification. (2) Recommendations for future research and development (R&D) efforts, emphasizing systematic methodologies, experimental systems, and standard approaches. (3) A framework for in-situ process monitoring as a qualification tool for aerospace parts, enabling enhanced reliability in AM processes. This effort will leverage a public-private partnership with the Air Force Research Laboratory (AFRL), the Federal Aviation Administration (FAA), and Auburn University, utilizing contractual resources to conduct research and analysis. The partnership will ensure access to expertise, experimental capabilities, and data necessary to achieve the study's objectives. The approach includes: (1) Collaboration with NASA and industry stakeholders to identify and assess technical gaps. (2) Potential sensitivity studies linking AM defects to mechanical properties. (3) Developing a framework to address in-situ process monitoring challenges and defining next steps for qualification methodologies.
NASA’s Autonomous Robotic Construction of Lunar Surface Infrastructure (ARC-LSI) study is defining the foundational technologies, architectural approaches, and system-level concepts needed to create large-scale, persistent infrastructure on the lunar surface. As NASA prepares for sustained lunar and future Mars exploration, the ability to autonomously construct and assemble infrastructure in situ—rather than relying on Earth-shipped, pre-fabricated systems—emerges as a critical enabling capability for long-duration operations.ARC-LSI focuses on robotic structural assembly as the primary pathway for building essential lunar infrastructure. Through autonomous robotic construction, NASA can efficiently create communication towers, radiation and blast shields, power and logistics platforms, mobility support structures, and crew shelters. This shifts the paradigm from delivering fully pre-integrated spacecraft to developing a sustainable, extensible, and robotically built lunar infrastructure ecosystem. Autonomous assembly reduces logistical burden, improves mission resilience, and lowers long-term cost and risk while enabling continuous human and robotic presence on the Moon.The study investigates scalable construction architectures, integrated robotic workflows, and concepts of operations (ConOps) that support high-priority lunar applications. ARC-LSI examines how modular structures, autonomous robotic systems, and construction sequencing can work together to create the first “built environment” beyond Earth. While structural assembly is the central focus, the study also considers supporting elements—such as power, data, and fluid-transfer outfitting—in the context of enabling complete, functional infrastructure systems. Additional work explores how In-Situ Resource Utilization (ISRU), surface manufacturing, site preparation, anchoring, and foundation strategies could contribute to long-term sustainability.Aligned with the Space Technology Mission Directorate (STMD) strategic goals and the Exploration Systems Development Mission Directorate (ESDMD) Moon to Mars strategy, ARC-LSI addresses Moon 2 Mars need for scalable power systems, surface communication systems, large-scale shielding for lander and habitat protection, and scalable platforms for science and logistics. By establishing the architecture-level understanding and technology pathways for autonomous construction, ARC-LSI positions NASA to build a resilient lunar infrastructure ecosystem that supports near-term missions and enables the next generation of human and robotic exploration.
To help prioritize lunar surface construction development needs, this multi-Center trades study will explore/trade different lunar infrastructure site preparation concepts of operations (ConOps) for optimum execution. The task will collect/compare preliminary site preparation and geotechnical requirements for emplacing critical infrastructure, define the requirements for site preparation systems, and help fill a large knowledge gap by providing insight into ConOps and system design sensitivities. Creation of infrastructure such as power and communication grids, launch and landing pads (LLPs), shelters, habitats, and roads will require a significant amount of bulk regolith moving for both site preparation and during construction. Site preparation will require capabilities for rock clearing, cut and fill of terrain, leveling, grading, compacting, and trenching in the harsh lunar environment. The ability to dig, haul, and dump bulk regolith can provide: shelter and habitat structures with regolith overburden for radiation, meteorite, and thermal protection; berms and shielding for nuclear power reactors; and LLPs with berms for LLP blast plume containment, to cite a few critical needs. This study will bring together subject matter experts (SMEs) across multiple disciplines and Centers to develop a coordinated vision for the assembly and outfitting of high priority infrastructure, leveraging past and present NASA-led activities. Key elements of the coordinated multi-Center SMEs' effort include the following subtasks:Preliminary designs and site preparation requirements of representative high priority infrastructure will be defined and selected for study in consultation with Exploration Systems Development Mission Directorate (ESDMD) and Industry.Site preparation options and resulting ConOps for selected infrastructure will be collected, compared also with newly conceived approaches, and traded based on prioritized metrics.Both near-term and long-term technology needs for the chosen concept(s) will be defined, including the necessary robotic systems as well as support infrastructure such as power, communications, and navigation requirements, maintenance and repair strategies, etc.Findings from this formulation Internal Task Agreement (ITA) effort will also provide refined input and use cases to better inform the relevant Lunar infrastructure capability goals roadmap development.Technology shortfalls and roadmaps for subsequent assembly and outfitting also will be defined and refine
The purpose of the Optimal AC Lunar Power Transmission Study is to help inform the power community if the currently proposed 1000 Hz AC frequency is ideal for Lunar Surface power transmission when considering mass, reliability, and complexity. This effort directly aligns to NASA's Space Technology Mission Directorate (STMD) Shortfall 1592, High Power, Long-Distance Energy Transmission Across Distributed Surface Assets, and Shortfall 1591, Power Management Systems for Long Duration Lunar and Martian Missions. This task also aligns to STMD's planned LIVE Domain's need to “Provide power through common distribution interfaces to and among assets on the lunar surface". Finally, this study benefits other STMD power technology developments, including Vertical Solar Array Technology (VSAT), LunaGrid-Lite Tipping Point (LGL TP) and Blue Origin and Lockheed Martin in their ongoing work involving the Universal Modular Interface Connector (UMIC).This trade study focuses on identifying the optimal frequency for long-distance, high-power AC transmission on the Lunar Surface and balancing the need for reliable high-power, long-distance AC transmission with the lowest mass power cable. Specifically, this task performed impedence sweeps and full power transmission tests on the cable to assess performance in both a terrestrial setting and a simulated lunar environment within a dirty thermal vacuum (TVAC) chamber, under vacuum conditions and in contact with a lunar regolith simulant JSC-1A, possessing magnetic susceptability properties. Both shielded and unshilded versions of the cable were tested in various configurations, with and without contact with the JSC-1A simulant. The outcome of the testing yielded no significant power losses detected.
Space applications require that primary and regenerative fuel cells operate on pure oxygen rather than the air used by terrestrial fuel cells. While NASA's Space Technology Mission Directorate (STMD) has successfully advanced the H2/O2 fuel cell technology from Technology Readiness Level (TRL) 2 to TRL 5, the inability of space fuel cell stack vendors to deliver reliable space fuel cell stacks that meet NASA's minimum performance requirements indicates that the technology Manufacturing Readiness Level (MRL) remains insufficient for cis-lunar missions. The purpose of this task is to conduct a detailed manufacturing review at all levels of H2/O2 space fuel cell stack assembly to identify manufacturing and quality gaps inhibiting implementation and commercialization of this technology.The Scope of Work includes a thorough manufacturing review at the domestic space fuel cell suppliers who have demonstrated at least TRL4 using the proton exchange membrane (PEM) electrolyte technology used for missions with H2/O2-based propellants and the high temperature solid oxide (SO) electrolyte technology used for missions with CxHy/O2-based propellants. The manufacturers able to participate in this study include Infinity Fuel Cell and Hydrogen, Inc. (IFCH) and Teledyne Energy Systems, Inc. (TESI) for the PEM technology, and Precision Combustion, Inc (PCI) and OxEon Energy (OxEon) for the SO technology. NASA's fuel cell technology leads at Glenn Research Center (GRC) and Johnson Space Center (JSC) will conduct these reviews. The fuel cell technology leads will conduct on-site visits at each of the manufacturers' locations. After each vendor site visit, an informal internal review will occur consisting of the NASA fuel cell subject matter expert (SME) teams from GRC and JSC to discuss findings and recommendations as well as serve as a mechanism to both disseminate expertise and train early career staff. The deliverable final report will progress through internal reviews at both GRC and JSC prior to submission to STMD.
Next-Gen Ultrastable Structures (NGUS) for In-space Observatories and Science Payloads StudyTo identify one or more technologies and concepts which can contribute toward creation of an ultrastable in-space observatory and perform a technical assessment using requirements derived from the Astrophysics 2020 Decadal survey and in collaboration with the Science Mission Directorate (SMD) Habitable Worlds Observatory (HWO) working groups and SMD scientists. A particularly demanding example is the HWO recommended by the Astrophysics 2020 Decadal Survey which requires unprecedented stability and pointing accuracy. Isolated and quiet payloads are necessary to achieve ultrastability (~ 10s of picometers) to enable the coronagraph system on the HWO to reach the desired high level of contrast imaging. The results from this study will be used to identify technology gaps (e.g., materials, structures, active controls) and the associated performance metrics needed to guide follow-on technology road mapping and development efforts. This is a multidisciplinary problem requiring a broad set of skills to understand and effectively addresses the technical issues to develop a roadmap toward solutions. A three-pronged approach will be applied to investigate options for creating ultra stable structures for in-space applications. The team will identify and evaluate:Materials and material arrangements focusing on high stiffness and thermal stability (i.e. low or tailorable coefficient of thermal expansion),Novel mechanical designs and composite arrangements to minimize the influence of thermal loads and vibrations,Active thermal and mechanical systems to maintain dimensional stability within specified tolerances including thermal management, displacement control, and vibration isolation.Suggestions and recommendations will be documented in final report submitted at the end of the 12 month study.
Two-phase heat transfer thermal control refers to the method of managing and controlling temperature in a system by utilizing the heat transfer properties of two-phase fluids. A two-phase fluid involves both liquid and vapor phases, such as when a liquid boils and forms a vapor. This type of thermal control system is particularly effective in applications requiring efficient heat removal, as it can handle large amounts of heat with relatively small temperature changes. Two-phase heat transfer thermal control offers the ability to transfer more heat, with smaller temperature drops and less pump power, and offers potential freeze tolerance and higher heat rejection turn down. However, managing the balance between liquid and vapor phases can be difficult. Factors like pressure, temperature, and the working fluid properties must be carefully controlled to ensure optimal performance since managing the balance between fluid and vapor phases, especially in microgravity, can be difficult.Passive two-phase thermal control (heat pipes, etc.) has been routinely used on flight systems at a tactical level. However, a quantitative assessment of how active (mechanically pumped) and advanced passive two-phase systems can be leveraged at the architectural scale for a spacecraft-level “thermal bus" has been lacking since pre-ISS days. The abilities to share and re-use heat dissipations across the spacecraft and efficiently reject or conserve such heat when the mission phase calls for it can result in mission-enabling savings in resources. Such claims depend on the mission parameters, and given the substantial advances made and the key role that thermal management plays in future missions, a focused study is needed to assess that applicability to identified shortfalls and to determine the possibilities, metrics, and areas for future focus.
NASA's RoboCap team identifies and creates opportunities for high value robotic technology infusion by connecting U.S. industry and NASA investments with Moon to Mars (M2M) exploration architectural gaps.Key efforts in the study phase: +Business Case Definition for Space Robotics+Technology Roadmap Development for NASA Exploration Programs+Publication of a Summary Report on Space Robotics Business Cases, Current Technology Development Efforts and Needs+Bridging U.S. industry and NASA stakeholders by utilizing existing technology onramps (SBIR, ACO, etc.)+Held a workshop with NASA ESDMD leaders from LAT and EHP to discuss architecture gaps, roadmaps, robotic technology opportunities+Established a NASA Autonomous Systems and Robotics Community of PracticeRoboCap Business Case Application Areas:+Lunar surface logistics automation services: The M2M Lunar Architecture Team identified delivery of crew-scale cargo from landers to use locations as an important early technical gap. Automated delivery services save crew time and reduce crew EVA risk.+Lunar surface power grid outfitting automation services: Some options call for transmitting power over km-scale distances from fission reactors or solar towers to other surface assets. Automated cable outfitting services save crew time and reduce crew EVA risk.+Commercial LEO station utilization automation services: Commercial LEO station operating costs are dominated by cost to launch crew and crew consumables. Automated dexterous manipulation services to sustain most utilization through uncrewed periods greatly reduce cost and improve return on investment.The Moon to Mars (M2M) program is driving innovation in robotic technologies to support future space missions. A key component of this effort involves assessing and enhancing robotic capabilities to address specific logistical and operational challenges. The technology focuses on improving robotic systems for efficient cargo handling, particularly at the sub-pallet level, using advanced facilities like the JSC Integrated Mobile Evaluation Testbed for Robotics Operations (iMETRO). Additionally, it supports other critical use cases such as connector/cable deployment, assembly, and science equipment utilization, which are essential for establishing a sustainable presence on the lunar and Martian surfaces.The development process addresses several technical challenges, including general-purpose robotic manipulation for human-scale logistics, surface-based lunar logistics management, robotic actuation for long-duration operations, sensing for autonomous robotic operations, and robust robotic intelligence for high-tempo autonomous operations. These advancements are crucial for ensuring that robotic systems can operate reliably and autonomously over extended periods. The program integrates prior research efforts and partnerships with industry and academic partners to advance these technologies.The implementation strategy involves a multi-center study with regular reporting to track progress and guide future development. This includes conducting comprehensive robotics demonstrations and tests, preparing detailed reports on outcomes, and providing quarterly status updates and bi-annual technology roadmap updates. An annual comprehensive report synthesizes the year's findings, progress on addressing identified shortfalls, and recommendations for future work and technology maturation efforts. By addressing current gaps and maturing key technologies, the program aims to ensure the success of future lunar and Martian missions through efficient, autonomous, and reliable robotic systems.
Lunar Dynamic Power Conversion Study (DYNAPOW-Study) is designed to address a draft Foundational Capability in the Advanced Power and Thermal category identified by NASA's Space Technology Mission Directorate (STMD). This Foundational Capability is titled “Radioisotope based electrical and thermal energy generation utilizing non-plutonium sources." DYNAPOW aims to develop a roadmap for the maturation of Stirling-based dynamic power conversion technologies for spaceflight. This effort will include the following efforts.- Task 1. Perform a study to document the current watt-class state-of-the-art (SOA) Stirling-based radioisotope power systems and identify gaps hindering application of dynamic radioisotope power systems (RPS).- Task 2. This study will also evaluate the production rates for 238Pu-based and non-238Pu radioisotope fuels as potential heat source for lunar objectives, including mobility and scientific return. The report will also provide observations to the landscape of alternate isotopes and their applicability for use in spaceflight missions of varying durations and power levels.- Task 3. Develop a roadmap to increase the technology readiness level (TRL) of Stirling-based radioisotope power systems (RPSs) in the watt (W) class, with the goal of flying a mature technology that can enable future lunar science objectives and other spaceflight applications.A high-level description on how this mature Stirling-based technology could enhance development of kilowatt (kW) class fission surface power (FSP) will be included as complimentary to the roadmap. The deliverables of this study will also include proposal of follow-on efforts with a clear path to answer questions and develop confidence in baselining this technology for future lunar science and technology demonstration missions.
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The core Flight System (cFS) is NASA's most widely used flight software (FSW) framework and has been extensively used on many processors. These processors typically have associated ecosystems with SW development boards and SW tools tailored for the cFS. cFS enables reuse, rapid development, and portability through its dynamic run-time environment, layered architecture, and component-based design. Its three main components – the platform support package, operating system abstraction layer, and the core flight executive – give system designers the tools and flexibility they need to implement a robust FSW that has powered 40+ small to large class NASA missions. Currently NASA is developing the HPSC ecosystem which is based on the rad hard PIC-64 processor. The core of the HPSC design is an industry standard, open-source instruction set architecture, bundled with significant fault tolerance, radiation tolerance, and a full security suite as well as all the software required to run it. SW development boards for the PIC-64 are currently available with flight boards expected in 2026. The HPSC also includes a suite of features and industry-standard interfaces and protocols. SW tools need to be developed to facilitate the use of cFS on the PIC-64 based hardware to reduce the cost of implementing cFS/HPSC mission architectures. The technology to be developed will provide missions with a standard hardware/software package. cFS SW support packages will initially be developed for the use of RTEMS, Linux, and VxWorks operating systems running on commercially available PIC-64 based development boards allowing the use of key PIC-64 functionality.
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Project Objective
This project is attempting to develop metal organic frameworks (MOFs) that are not produced at an industrial scale to capture hydrogen remaining in carbonous exhaust gases produced from chemically processing human-exhaled carbon dioxide. The goal of this (Cooperative Agreement Notice) CAN is to develop MOF test candidates, use the formulation and synthesis instructions developed to take them to mass production, and to test them in the sub-scale test bed at MSFC.
Project Description
The long-term goal of Closed ECLSS Air Revitalization (CLEAR) is to fully reutilize carbon dioxide chemical reduction waste products. This is initially performed using a Sabatier reaction that converts carbon dioxide to methane and water. Water is recovered to the environmental control and life support system (ECLSS), while methane is further processed. Current Methane Post-Processor Assembly (MPPA) technologies recover hydrogen from methane (C:H=1:4) by reducing it to acetylene (C:H=1:1) or ethylene (C:H=1:2), but the hydrogen gas that is formed needs to be captured and separated from the other gases. MOFs are sorbents capable of capturing the carbonous chemical gases allowing pure hydrogen to be separated, captured, and repurposed in another process. Hydrogen can be used as a liquid propellant for exploration, or can be used to increase the reaction efficiency of the Sabatier reactor (forming more water).
Project Results and Conclusions
In FY25, a small-scale testbed was developed at Marshall Space Flight Center to test three different task-selective MOF candidates that could purify a hydrogen from a specialty gas mix that simulates MPPA processes. NKMOF-1-Ni was developed through this CAN to be upscaled by Framergy, Inc.
In FY26, a PR is in place to upscale this MOF from a 1-5g scale to 2-kg scale. The MOF will be tested at Ohio State University to validate initial data on adsorption isotherms and stability of the MOF pellet, and will be tested in the testbed at MSFC.
Life Support Systems: This technology will close the air revitalization loop of efficient use of human-exhaled carbon dioxide waste which will enable future exploration missions beyond the moon.
In-Situ Resource Utilization: Further investigation is being performed regarding the capture of acetylene and ethylene gases including potential use in off-Earth manufacturing of polyacetylene or polyethylene plastics, respectively.
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.
For cables with DC current:
•Red plague is severe, occurs faster, and covers a larger area than without DC current. The current causes expansion of silver cover cracks in the cables which further enhanced the transfer of oxygen and corrosion products, thereby accelerating corrosion of copper.
•Corrosion (longitudinal) spreads much faster along the cables in the direction of DC current.
•Under 90° F and 90% Relative Humidity, the corrosion (longitudinal) progresses about 10 inches in the first year while it (transversal) is about 23.18 microns in the first year for a strand of 230μm-radius.
•Under 70° F and 40% RH, the corrosion (longitudinal) spreads along the cable direction to about 0.4 inches in the first year.
•The atmospheric spread/depth of corrosion for long term periods was predicted using the power function and power linear model.
Benefits include: 1) Establishing a solid database to predict the corrosion status of cables with different history so that possible failures in aerospace systems due to the cables will be prevented; 2) Training students to tackle the future challenges in NASA systems; and 3) Developing new knowledge and technology related to corrosion of cables through publications and patent application, which also can be used by manufacturers to improve the quality of their products.
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Exploration (Lunar and Mars) surface Extravehicular Activities (EVA)s will have physically and cognitively demanding tasks for crew with high injury risk. In addition, crews will perform a larger quantity of EVAs with far less rest between EVAs than ever before. The Spacesuit Fit & Injury Technologies (SFIT) work develops suit-independent, generalizable tools to predict, monitor, and mitigate EVA crewmember injury. The SFIT project will prioritize technology development based on the Injury Modes and Effects Analysis (IMEA) to mitigate highest impact spacesuit fit and injury modalities/scenarios.
Suited injury characterization, prediction, monitoring, and mitigation technologies will enable planning, training, operations, and system design for all suited mission phases in an Extravehicular Activity (EVA) suit and for anticipated crewmember capabilities and anthropometries. Once established, validated tools from the Spacesuit Fit & Injury Technologies (SFIT) project will be provided to the Extravehicular Activity and Human Surface Mobility Program (EHP) to inform suit design(s), training, and operations.
Existing FY25 scope that has high return on investment across multiple fission-based disciplines, with a focus on risk reduction and regulatory path finding.
NTP is an open-ended project focused on developing enabling technologies for nuclear thermal propulsion and demonstrating the robust functionality of those technologies through ground and flight testing. NTP systems have capabilities that can be directly leveraged, or readily evolved, for future NASA missions that include cis-lunar operating systems, deep-space science systems, and small and large cargo transportation systems for Mars human exploration. The technology challenges NTP is focused on solving are primarily driven by the extreme operational requirements for the fission reactor. Technology maturation investments are focused on finding solutions to the technology gaps for a reactor operating at temperatures exceeding 2800 K with a flowing hydrogen environment. The coupled effects between an operating reactor, integrated turbine machinery, and the thermal/neutronic balance also require investment in modeling and simulation capabilities to design NTP systems and predict how they will work in space.
The completion of the Cold Flow Test (CFT) Engineering Development Unit (EDU) testing provides data for validation of a variety of fluid flow, instrumentation, and space reactor control model and results in a return on the investment in CFT design and fabrication that was completed earlier in the FY2025.
Research feasibility for carbon dioxide (CO2), humidity (H2O), and trace contaminant removal system from vehicle Environmental Control and Life Support System (ECLSS) as applied to mobile space suit application in a Portable Life Support System (PLSS).
After an extravehicular activity (EVA), the CDRILS-M system ionic liquid could be circulated in the vehicle CDRILS system to recover the CO2/H2O and regenerate the ionic liquid.
The traditional approach to planetary defense consists of momentum transfer between the impactor and the threat that changes the threat orbit such that it misses the Earth, which is generally known as “deflection.” The PI approach is different in that we do not use momentum transfer, but rather energy transfer. We do not mitigate the threat by requiring it to miss the Earth, but rather we explore mitigating the threat by pulverizing it and then using the Earth's atmosphere as a shield. This turns out to be incredibly effective and allows for extraordinarily short mitigation time scales. The PI method involves an array of small hypervelocity kinetic penetrators that disassemble and fragment an asteroid or small comet (more generally referred to as “bolides”). The resulting material from the breakup is referred as “fragments.” The method effectively mitigates the threat by using the Earth’s atmosphere to dissipate the fragment energy. This system allows for a practical and low-cost terminal solution to planetary defense using existing technologies. The approach works in extended time scale interdiction modes where there is a large warning time, as well as in short interdiction time scenarios with intercepts of minutes to days before impact. In the terminal interdiction mode, the bolide fragments of roughly
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NTP is an open-ended project focused on developing enabling technologies for nuclear thermal propulsion and demonstrating the robust functionality of those technologies through ground and flight testing. NTP systems have capabilities that can be directly leveraged, or readily evolved, for future NASA missions that include cis-lunar operating systems, deep-space science systems, and small and large cargo transportation systems for Mars human exploration. The technology challenges NTP is focused on solving are primarily driven by the extreme operational requirements for the fission reactor. Technology maturation investments are focused on finding solutions to the technology gaps for a reactor operating at temperatures exceeding 2800 K with a flowing hydrogen environment. The coupled effects between an operating reactor, integrated turbine machinery, and the thermal/neutronic balance also require investment in modeling and simulation capabilities to design NTP systems and predict how they will work in space.
The Earth-Moon economy needs a transportation infrastructure to support mobility using an efficient, evolvable system that has reduced reliance on Earth resources. Nuclear thermal propulsion systems can produce thrust levels comparable to chemical systems with a propellant mass efficiency that is two or more times greater than conventional chemical systems. The combination of propellant efficiency and high thrust has applications as an effective cislunar transportation system while also enabling fast transit to exploration and science target destinations throughout the solar system. Nuclear energy can provide solar-independent power for years with minimum need for refueling and maintenance.
A rotating detonation rocket engine improves performance over a conventional rocket engine by harnessing the increase in pressure provided by detonative combustion for thrust generation. The detonation wave propagates in an annular combustor and runs transverse to the flow direction at very high speeds, often requiring only a few inches to accomplish propellant mixing and combustion. RDRE combustors are also attractive because they can be very short, allowing for improved integration with vehicles, such as upper stages or landers. RDRE's have been shown to operate with a wide variety of propellants, including hypergolic propellants, and can operate over a wide throttling range. Operation with cryogenic propellants has also been demonstrated. Regeneratively cooled chambers have been demonstrated with run times up to several minutes at a time. Current research is focused on injector technology to prevent coupling of the pulsed combustor flow with the propellant supply manifolds, developing optimized combustor contours, and nozzles optimized for unsteady flow. All of these technical challenges will need to be addressed in order to achieve full theoretical performance. Related technologies include high heat flux combustor cooling concepts, advanced instrumentation for high speed oscillatory flows, and advanced computational modeling tools and techniques. This last area includes specialized combustion kinetic models that simultaneously capture detonative and deflagrative behavior correctly, assessments of required numberical accuracy and grid density, wall heat transfer modeling in an unsteady environment, and the development, demonstration, and validation of lower order models that can be incorporated into higher fidelity simulations for parameters such as skin friction loss and heat transfer to reduce model run times.
This portfolio contains multiple cryogenic model development activities, both CFD and Nodal, with the overall goal of developing and validating pre-predictive models against cryogenic experimental data for the following operations: Self-Pressurization, Mixing, Autogenous and GHe Pressurization, Line and Component Chill-down, Tank Chill-down, Tank Fill and Drain, Tank Venting, and Liquefaction. Results from these development activities will be infused into analyses supporting NASA mission applications.
CFM Modeling Portfolio addresses capability gaps for predicting cryogenic fluid behavior in 1-G and microgravity environments for use as design tools for future NASA missions. The CFM data captured during experimental operations greatly influences the ability of using the data to develop CFM models and conduct simulations that accurately and functionally represent the need of future NASA large-scale CFM demonstrations and missions.
Carnegie Mellon University in Pittsburgh will lead Institute for Model-based Qualification & Certification of Additive Manufacturing (IMQCAM) aiming to improve computer models of 3D-printed – also called additively manufactured – metal parts and expand their utility in spaceflight applications. The institute will be co-led by Johns Hopkins University in Baltimore.
Metal parts 3D-printed are made from powdered metals, which are melted in specific ways and shaped into useful parts. Such parts could be useful for things like rocket engines – giving more flexibility to create new parts when designs change – or as part of a human outpost on the Moon, where bringing pre-fabricated parts would be expensive and limiting. However, efficient certification and use of such parts requires high-accuracy predictions of their characteristics.
"The internal structure of this type of part is much different than what's produced by any other method," said Tony Rollett, principal investigator for the institute and US Steel professor of metallurgical engineering and materials science at Carnegie Mellon University. “The institute will focus on creating the models NASA and others in industry would need to use these parts on a daily basis.”
Detailed computer models, known as digital twins, will allow engineers to understand the parts' capabilities and limitations – such as how much stress the parts can take before breaking. Such models will provide the predictability of part properties based on their processing that is key for certifying the parts for use. The institute will develop digital twins for 3D-printed parts made from spaceflight materials that are commonly used for 3D printing, as well as evaluating and modeling new materials.
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The recently established NASA Artemis mission reflects the growing interest of sending humans to colonize the Moon and Mars, and to explore more of our solar system. However, long-term space exploration requires technologies that can protect astronauts and space equipment from extreme space environments, such as extreme temperatures and carcinogenic radiation. While Carbon nanotubes have been investigated as space materials, boron-nitrogen nanotubes (BNNT) are just as mechanically strong, and can provide higher thermal resistance and radiation-shielding capabilities to address these harsh conditions. Furthermore, BNNT and BNNT polymer composites display unique piezoelectric properties that are scalable and useful in vibrational sensors and soft actuators. Experimentally finding the ultimate set of modifications and geometries that can produce BNNT and BNNT-polymer composites with the best properties under extreme space conditions may be infeasible, costly, and time-consuming. This project thus aims to accelerate this optimization process using virtual prototyping: We will employ computer simulations and first-principle calculations to understand the mechanisms governing the properties of multi-functional BNNTs and their composites. This fundamental knowledge, along with machine-learning algorithms, can then search for the set of parameters that give the best overall properties of these multifunctional materials for extreme space conditions. Moreover, this project can inform the design of theoretically new structures with mechanical, piezoelectric, and radiation-shielding properties superior to current state-of-the-art aerospace materials. If awarded, I would like to request a grant start date of August 23, 2021, which aligns with the start of the Fall semester at my host institution, Rice University.
This project could inform the design of theoretically new structures with mechanical, piezoelectric, and radiation-shielding properties superior to current state-of-the-art aerospace materials.
Improved rocket propulsion directly translates to reduced fuel requirements and increased payloads for space flight. Rotating detonation rocket engines (RDREs) have the potential to provide significant performance gains in thrust-per-fuel ratio, design trade space, and mass savings compared to traditional rocket engines, and are attractive candidates for NASA lander, launch, and attitude-control applications. However, it is not currently known how to optimally design an RDRE injector, chamber, or nozzle to achieve what theory suggests is possible, so NASA needs capability for improved understanding of RDRE behavior. Because in situ diagnostics are limited and detailed computation is too computationally intensive for design iteration, I propose to develop a reduced-order computational model, capturing the important features of the flow, with emphasis on understanding the associated chaotic dynamics, for which no model currently exists. My model will run fast enough for use in design iteration and will be used to accelerate NASA’s ongoing RDRE development by quickly providing predictions for many design parameters. This improvement in evaluation turn-around time will allow for more detailed exploration of the design parameter space. In particular, I aim for this model to identify the geometric and operating parameters that determine the development of different wave modes in RDREs. Experiments have shown that current RDREs do not consistently exhibit the same wave modes and that different wave modes can produce different engine performance. Inconsistency in engine performance inhibits both practical use and efficient development of the technology, so the results of this work will inform optimal design practices and significantly advance NASA and industry development of RDREs. Thus, this work will enable the designs with the most favorable properties to be more quickly identified and iteratively refined to improve desired performance measures, directly supporting ongoing NASA development of next-generation RDRE design.
No details available.
Space travel to planets and moons with a sensible atmosphere requires an atmospheric entry vehicle to deliver payloads safely from orbit to the surface. The entry vehicle generally has a blunt forebody to withstand heating during the high-speed entry phase. However, blunt-body vehicles become dynamically unstable once they slow down to supersonic and transonic speeds. The instabilities cause the angle-of-attack to oscillate, gain amplitude in time and diverge to a point where the vehicle tumbles, resulting in a catastrophic event. The physical mechanisms leading to the dynamic stability and its characteristics remain challenging after decades of meticulous work due to massive flow separation, complex wake flow, and unsteady pressure field of dramatically changing flight and flow conditions of the descending and decelerating vehicle. This proposed research aims to develop hybrid physics-data modeling approaches for space exploration. We focus on innovating a holistic physics-guided machine learning framework for characterizing the dynamic stability and performance of reentry vehicle systems. Our framework is, therefore, motivated to provide a trustworthy learning platform with enhanced model fusion, feature engineering, and symbolic regression capabilities. We will explore the feasibility of new learning approaches to elucidate new physical insights in describing vehicle stability and identify how to utilize multimodal resources extracted from experiments and high-fidelity simulations effectively
No details available.
Vision: The vision of the Joint AdvaNced PropUlsion InStitute (JANUS) is to enable and proliferate the flight of high-power electric propulsion (EP) systems. Successful completion of the proposed studies will establish physics-based limits, mitigation techniques, and extrapolation procedures to provide a probabilistic assessment of the in-space performance and lifetime of high-power (~100 kW) EP devices. The assessment will come from measurements made in ground-based test facilities combined with predictive engineering models. To realize this vision requires a significant advance in our understanding of the limitations of test facilities, physics-based numerical models, mitigation technique efficacy, and in-space operation of EP devices.
To perform the required research, JANUS has mobilized a comprehensive team of world-class researchers who are subject-matter experts in the relevant research areas. The home institutions of the principal participants are Georgia Tech (Walker, Saeedifard), U. of Michigan (Jorns, Foster, Gallimore, Gorodetsky), U. of California, Los Angeles (Wirz, Marian), U. of Illinois (Rovey, Levin, Chew), Colorado State U. (Williams, Yalin), Penn State U. (Cusson), U. of Colorado (Boyd), Stanford U. (Hara), and Western Michigan (Lemmer).
Background: The solicitation states that state-of-the-art approaches to correlate ground-test results to in-flight performance and wear are insufficient for the operation of high-power EP devices (> 100 kW). This stems from ground-based EP test facilities interacting with thruster operation. The resultant ground-based thruster operation does not represent in-space performance or lifetime. These facility effects include elevated pressure from residual, inadequately pumped gas in the test facility, contaminants from the facility interacting with the thruster, and uncertain electrical paths through the thruster plume and the test facility walls. Over the past 40 years, facilities, test methodologies, and numerical models have been established for EP devices approaching 20 kW. For low-power Hall effect thrusters (HETs) and gridded ion thrusters (GITs), we have a high degree of confidence in ground tests largely due to flight experience. However, the existing test facility infrastructure and tools are not directly extensible to high-power devices (~100 kW). High-power EP technology cannot be realized without first improving our testing and modeling capabilities. There are gaps in the understanding of these facility effects that will require the combined expertise of the JANUS team to identify and model.
To improve our testing and modeling capabilities for high-power EP, we must address knowledge gaps in four categories. (1) Thruster performance is perturbed by facility pressure effects. The elevated facility background pressure and the resultant increase in neutrals lead to increases in gas ingestion by the thruster, charge-exchange ions production, and plume divergence that collectively reduce confidence in the prediction of performance in space. Absolute standards for a sufficiently low background pressure to ensure ground tests reliably correlate to in-space performance do not exist. (2) Thruster lifetime is masked by facility contamination. The high-energy particle flux to the facility walls increases rates of backsputtering. Test facilities are lined with graphite to minimize this effect, but experiments still show deposition, layering, flaking, and spalling of films deposited on thruster and facility surfaces. The net effect of contaminant coating of the thruster is reduced confidence in predictions of thruster lifetime. (3) The large volume of dense, conductive plasma expelled from the thruster electrically couples it to the test facility. The effects of this interaction include low resistance paths between thruster surfaces and the test facility, modified electron mobility, and facility-enhanced beam neutralization. These processes only occur in the ground-test facility, thus reducing confidence in predictions of stability and performance. (4) Only disparate, limited spatial and temporal models exist for EP devices, plumes, and sputtering. The models must be integrated and furthermore must include the impact of uncertainty in experiment and model fidelity as well as be rigorously verified and validated.
Research Objectives: Several key capabilities must be achieved to close the four gaps and realize our vision. The research objectives that align with these capabilities are to: (1) define new standards and requirements for when the test environment is sufficiently “space-like” for high-power EP testing; (2) develop procedures and techniques for facility design, upgrades, and thruster operation to meet testing requirements; (3) demonstrate tools and methodologies based on physics-based models to make probabilistic assessments of in-space performance and lifetime from measurements made in non-optimal test facilities; and (4) educate and train the next generation of engineers and scientists to implement high-power EP.
Research Plan: JANUS will address the challenge of predicting the performance and life of high-power EP devices in-space through a fully integrated research program with four interdependent research pillars: (1) Thruster Testing, (2) Facility Fidelity, (3) Diagnostics and Fundamental Studies, and (4) Physics-based Modeling and Integration. The effort will focus on HETs and GITs operating on xenon and krypton gases. The extension of the modeling, mitigation techniques, and standards to high-power testing will require the combined efforts of all four pillars.
To ensure efficient integration of these efforts and achieve practical results in the five-year timeline, JANUS will use uncertainty quantification (UQ) and sensitivity of the overall thruster performance and life models to drive and accelerate the modeling and experimental inquiries. Unexplained physics and unknown properties will be treated as sources of uncertainty in the performance and life models that impact confidence in the predictions. Thus, the UQ and sensitivity analyses will accelerate the research by focusing the efforts of the team on processes that require higher-fidelity simulations and more in-depth targeted experimental investigations to update models and reduce the uncertainties in predictions. We leverage this insight to develop mitigation strategies to compensate for these effects via modeling and experiments. Systematic evaluation of these mitigation strategies will lead to new standardized tools, techniques, and ground-testing methodologies to achieve the ultimate goal of extending the results of high-power ground tests to in-space operation. This innovative research integration plan will produce research efforts, tools, and databases that represent a huge return on investment and were not conceived in the past because of insular, disjointed investigations.
Impact: This effort will deliver several new tools, strategies, and guidelines for evaluating existing infrastructure and designing new infrastructure for testing high-power EP. These include validated models for the response of HETs and GITs to the facility, new physics-based standards for testing and modeling that encapsulate best practices for mitigating and/or compensating for facility effects, and new standardized diagnostic techniques for characterizing the effects of the facility on thruster operation. We will collaborate with government and industry partners to incorporate our advancements into present and future research and development processes. Furthermore, JANUS will employ and graduate many university graduate students. Our work will transform them into engineers and scientists with the skills needed to enable the development of high-power EP technology. Just as the Roman god Janus stood at the intersection of new beginnings, so will this Institute represent a crucial gateway for the transition of the next generation of propulsion technologies for space exploration from the laboratory to space.
Establishing a sufficient space-like environment is crucial for evaluating and predicting high-power propulsion system behavior and ensuring mission success. JANUS will utilize physics-based modeling, high-power thruster testing, novel diagnostic development, and fundamental experiments to advance mitigation strategies to overcome the limits of current ground testing capabilities.
The Advanced Computational Center for Entry System Simulation (ACCESS) is a comprehensive team of world-leading experts from five U.S. universities (Colorado, Illinois, Kentucky, Minnesota, New Mexico) and three international collaborators (Oxford University, National Research Center-Bari, Instituto Superior Tecnico-Lisbon). Our vision for ACCESS is to radically advance the analysis and design of entry systems through development of a tightly integrated interdisciplinary simulation framework employing high-fidelity validated physics models, driven by quantified uncertainty and reliability, and enabled by innovative algorithms and high-performance computing.
A NASA Entry System (ES) involves the Thermal Protection System (TPS), including both the heat shield and backshell, along with the supporting structure. An ES is essential to many of NASA’s highest priority space exploration missions, including lunar return to Earth (Artemis), Titan entry (Dragonfly), sending people to Mars (Mars Human Lander), and return of Mars samples to Earth (Earth Entry Vehicle, EEV). Based on the key attributes of these missions, the critical physical processes that drive ES design involve flow phenomena (e.g., chemistry, radiation, turbulence), material response (e.g., ablation) and structural response (e.g., fracture). The ACCESS research plan includes analysis of Dragonfly, Mars Human Lander, and the EEV.
Entry System analysis and design capabilities currently employed by NASA and its contractors are workable for Artemis, but have critical limitations for the more challenging environments of future missions. A first significant limitation with state-of-the-art (SOA) analysis capabilities is that the uncertainties associated with predicting key quantities of interest are so large that it is not always possible to close on a design cycle. For example, a margin of 100% for turbulent surface heating augmentation is typically employed for Mars entry, and a margin of 40% was used for radiative surface heating for lunar return. Such large uncertainties arise directly from limitations in the accuracy of modeling the key physical phenomena and represent a significant challenge for meeting design requirements, e.g., EEV has a reliability requirement of less than 1 in 106 that cannot be met by SOA analysis capabilities.
A second significant challenge for the design of ES for NASA reference missions concerns the currently available analysis tools. NASA and the contractors employ a number of computational codes for analysis of ES. However, these tools are labor intensive to apply, their computational performance is limited in part by not taking advantage of emerging computer architectures, and they do not integrate uncertainty and reliability.
To address these challenges, the ACCESS research plan involves four tightly coupled tasks:
Task 1: Kinetic Rate and Physical Processes
Task 2: Integrated Simulation Framework
Task 3: High Fidelity Modeling of TPS Features, Damage, and Failure
Task 4: Uncertainty Quantification and Reliability.
ACCESS will drive down design margins and quantify uncertainty through an innovative, multidisciplinary research approach. The entry missions targeted involve an enormous number of gas-phase and radiative processes. For example, an ablating hydrocarbon TPS can require chemistry mechanisms with about 40 species and 150 reactions. Backshell heating from radiation can also be significant. To reduce the margin, rates for all key reactions must be estimated using reliable experimental data and scalable statistical inference techniques, and the resulting uncertainty must be quantified. In Task 1, theoretical chemistry will identify the key reactions and determine new rates as needed including those for production of electronically-excited states that radiate. The overall kinetics mechanism, including both ground-state and excited-state reactions, will be evaluated through direct comparisons with experimental data generated in world-class facilities. The quantification of uncertainty associated with the rates will be established in collaboration with Task 4. The rates, along with the quantified uncertainty, will be integrated into the overall simulation tool in Task 2. In Task 3, models for gas-surface kinetics, constructed from molecular beam experimental data, must first be applied at the mesoscale for material response modeling. Our novel approach uses simulations of representative volume elements (RVEs). The RVE simulations will use detailed kinetics information (Task 1) and specific meso-structures (Task 3) as inputs, and will quantify each of the mesoscale modeling components required by the material response model; namely, oxidation evolution, porous flow trends, and thermal, structural, and radiative properties. The RVE simulations will provide natural variability in these models and associated parameters (distribution functions), which is crucial to model a full TPS including uncertainty and reliability. The novel stochastic material response framework (Task 3) will be directly coupled to the overall simulation tool (Task 2) and will be developed within the proposed UQ framework (Task 4). This comprehensive approach spans all of the Tasks and all of the ACCESS universities. Such innovative and multidisciplinary integrated research is absolutely essential to achieving the Vision of ACCESS of reducing the overall margins and improving the reliability for the analysis and design of an ES.
The primary product of ACCESS is the Integrated Simulation Framework (ISF) that will completely change the paradigm in comparison to SOA capabilities for the analysis and design of ES. The ISF will be developed in Task 2, will integrate the key products of all other Tasks, and will take as its starting point the widely used US3D computational fluid dynamics code. As a fundamental construct in its design, US3D allows the integration of simulation capabilities for a broad range of physical phenomena through specification of plugins. The use of plugins with well-defined interfaces makes it possible to transfer capabilities developed in ACCESS for US3D into other simulation frameworks of NASA and its contractors. Task 4 addresses UQ at the level of individual phenomena in the flow and TPS areas (Tasks 1 and 3) and for overall simulations through the ISF (Task 2). The UQ for Tasks 1 and 3 will break new ground for detailed quantification of uncertainty through close coupling between modeling and experiments. Instead of “validating” the physics models, the contribution of inaccuracy and uncertainty of individual processes to overall risk in the ES design will be quantified and transmitted through the system level simulation. One significant challenge in Task 4 for UQ and reliability is the high computational cost of each full ISF simulation, which may limit the number of sensitivity data points that are generated. To address this challenge, novel algorithms will be explored, such as Discontinuous Galerkin methods and meshless techniques, that have the potential to significantly reduce the time to set up and execute large-scale simulations. Also, key ISF algorithms will be adapted for execution on Peta/Exa scale computer architectures to reduce run time. Emerging UQ approaches will be employed that make careful use of lower fidelity physical models to achieve results consistent with more expensive higher fidelity models but at drastically reduced cost. The successful outcome of the overall Vision for ACCESS will deliver an integrated simulation framework for the comprehensive and affordable design of ES with quantified uncertainty and reliability estimates that will be ready for adoption by NASA and its contractors.
The ACCESS institute will advance the analysis and design of NASA entry systems by developing a fully integrated, interdisciplinary simulation capability. ACCESS will focus on thermal protection systems, which protect spacecraft from aerodynamic heating, as well as prediction of the extreme environments experienced during entry. It will develop game-changing capabilities through the use of high-fidelity, validated physics models. This advancement will be enabled by innovative numerical algorithms, high-performance computing, and uncertainty quantification methods, with the goal of enabling computational entry system reliability assessments.
The Moon-to-Mars Planetary Autonomous Construction Technology (MMPACT) project is a NASA Space Technology Mission Directorate (STMD) Game Changing Development (GCD) project led by MSFC with partners including ICON Technology of Austin TX, Dr. Holly Shulman of Blue Star Advanced Manufacturing (BSAM), and other companies and universities in lesser roles. MMPACT is managed at Marshall Space Flight Center (MSFC) through the Science and Technology Office (STO). The MMPACT project focuses on the utilization of lunar in-situ materials for the on-demand construction of large-scale infrastructure elements like habitats, berms, landing pads, blast shields, walkways, foundations/floors, storage facilities, and roads. These structures will provide protection of crewmembers, hardware, and electronics while on the surface of an extraterrestrial body to enable on-location surface exploration. MMPACT chose to pursue the Laser Vitreous Material Transformation (VMX), developed by ICON, as the baselined construction material for development. Risk mitigation materials include molten extrusion (ICON) and microwave sintering of regolith (BSAM). These 100% regolith-based material process technologies can be used to reduce launch mass, building time, material waste, and personnel exposure to hazardous environments. Utilizing in-situ resources for the construction of extraterrestrial infrastructure elements will increase the efficiency of space missions by reducing the quantity of materials transported from Earth to surface destinations. The goal of the MMPACT project is to develop, deliver, and demonstrate on-demand capabilities to protect crewmembers and create infrastructure on the lunar surface via construction of landing pads, habitats, shelters, roadways, berms, and blast shields using lunar regolith-based materials. The project continues towards this end.
A rotating detonation rocket engine improves performance over a conventional rocket engine by harnessing the increase in pressure provided by detonative combustion for thrust generation. The detonation wave propagates in an annular combustor and runs transverse to the flow direction at very high speeds, often requiring only a few inches to accomplish propellant mixing and combustion. RDRE combustors are also attractive because they can be very short, allowing for improved integration with vehicles, such as upper stages or landers. RDRE's have been shown to operate with a wide variety of propellants, including hypergolic propellants, and can operate over a wide throttling range. Operation with cryogenic propellants has also been demonstrated. Regeneratively cooled chambers have been demonstrated with run times up to several minutes at a time. Current research is focused on injector technology to prevent coupling of the pulsed combustor flow with the propellant supply manifolds, developing optimized combustor contours, and nozzles optimized for unsteady flow. All of these technical challenges will need to be addressed in order to achieve full theoretical performance. Related technologies include high heat flux combustor cooling concepts, advanced instrumentation for high speed oscillatory flows, and advanced computational modeling tools and techniques. This last area includes specialized combustion kinetic models that simultaneously capture detonative and deflagrative behavior correctly, assessments of required numberical accuracy and grid density, wall heat transfer modeling in an unsteady environment, and the development, demonstration, and validation of lower order models that can be incorporated into higher fidelity simulations for parameters such as skin friction loss and heat transfer to reduce model run times.
The Entry Systems Modeling project (ESM) develops mission-focused models and simulation tools that improve performance, reduce risk, and enable new capabilities for planetary entry, descent, and landing (EDL) across the Solar System. Project developments span four critical EDL technical areas:Thermal Protection System (TPS) Materials – multiscale models of material properties and reliability, ablative response of the heatshield, and damage and failure modes in entry conditions;Shock Layer Kinetics & Radiation – first principles to engineering models of radiation resulting from specific gas compositions associated with planetary destinations of interest;Aerosciences – advanced computational and experimental techniques focused on vehicle dynamic stability, parachute inflation and dynamics, turbulent heating, and advanced numerical methods for computational fluid dynamicsGuidance Navigation & Control – end-to-end simulation capability for mission concept of operations (CONOPS) and new guidance and control methods to enable precision landing of high-mass spacecraft.Unique ground test facilities are leveraged to support model validation and uncertainty quantification, including TPS testing in arc jets, radiation analysis for given gas compositions in shock tubes, and aero-testing in a variety of wind tunnels across the Agency. The Project, on request, integrates modeling from the four technical areas to conduct systems level analyses on missions – past, present, and future – to glean new insights into mission performance and provide benchmarks for mission design. Model and simulation tool products resulting from ESM activities have been infused, and continue to be infused, into the Agency's strategic scientific missions and flight projects, including Mars2020, Orion/Artemis, Mars Sample Return Earth Entry System and Sample Retrieval Lander, Dragonfly, and DAVINCI.
The Strategic Astrophysics Technology program (SAT) supports focused development efforts for key technologies to the point at which they are ready to feed into major missions in the three science themes of the Astrophysics Division: Exoplanet Exploration, Cosmic Origins, and the Physics of the Cosmos. This program is specifically designed to address middle technology readiness level (TRL) "gaps" between levels 3 and 6: the maturation of technologies that have been established as feasible, but which are not yet sufficiently mature to incorporate into flight missions without introducing an unacceptable level of risk.
We propose to research and plan development for a Radio Access Network (RAN) design for Lunar exploration based on the current 3GPP standards for 5G NR in Release 17, and capable of continuous integration of new 3GPP releases. This upgradeability will represent a significant departure from a rigid hardware approach, for instance used in planned 4G LTE demonstration, and will enable the best use of lunar network assets given their uncertain schedules, lifetimes, and ever-changing mission needs. This approach fuses the excellent properties of NASA’s work on Software Defined Radio (SDR) platforms with 3GPP-based system architecture and standards. Resulting hardware and software designs based on SDRs for the gNodeb and User Equipment (UE) will be suitable for development into a low Size Weight and Power (SWaP) long life lunar environment tolerant package for operational deployment. We will address the neartime RAN Intelligent Controller (RIC) and control applications, traditional non-RAN core network and the non-realtime RIC and control applications. We will collaborate with NASA to assess 5G application from today’s plans through service initiation, growth and development to define the general requirements for distributed network control (5G core network and Open-RAN (O-RAN) RIC) and 3GPP gNodeB and UE functionality. We will then identify adaptations of O - RAN components necessary to provide 5G distributed network functions and associated hardware and software which meets the demands of lunar exploration. From this research, we will define a path forward for Phase II development of a prototype gNodeB hardware/software platform. We will also investigate sidelink architectures and capabilities for PNT that can be integrated over time through software updates. The envisioned outcome is a hardware/software package suitable to be integrated with any systems that are deployed such as Astronaut suits, robotic explorers, fixed platforms, orbiting relays, and Gateway.
Potential NASA application is to enable mobile and fixed radio frequency wireless communications capability for lunar exploration that meets 3GPP standards for 5G and beyond through providing Open Radio Access Network (O-RAN) central and distributed control implemented in gNodeB elements, User Equipment interfaces, distributed and centralized unit functions, and RAN intelligent controller functions implemented in a low size, weight and power package and enable NASA to purchase such communications as a service.
Non-NASA applications for Non-Terrestrial Networking control of 5G and beyond are growing in importance and maturity. These include edge applications for robustness, resiliency, and expansion beyond what ground based commercial cellular networks expect, and bringing 5G connectivity to satellite networks, high altitude air vehicles to enable 5G and beyond communications capabilities.
Soil moisture and data products with 10m ground range resolution generated by the SSSASAfRaS mission are of high interest to NASA scientists performing research in hydrology and solid Earth processes. The proposed evolving systems framework algorithms, coordination with low SV resources and dynamical/ad hoc inter-spacecraft communications network, distributed fault detection and mitigation, and graceful degradation of performance, can be applied to a multitude of NASA missions ranging from Earth observation to small body exploration to drones.
Precision agriculture practitioners and farm consultants can benefit from the soil moisture data products of the SSSASAfRaS mission. The evolving systems theory and algorithms can be used in terrestrial sensor nets. Relative localization and collision avoidance algorithms can be applied to air traffic decongestion for UAS and to driverless car traffic management.
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. Ohalo III will serve as a testbed for the validation of crop production systems and technologies on the ISS. Ohalo III is a prototype crop production system that will validate water delivery, volume optimization, and advance knowledge on crop production operations which will inform design decisions for a future crop production system intended to be deployed on the Deep Space Transit mission. Ohalo III is being designed, built, and tested at the NASA Kennedy Space Center and the project and hardware development goals include the following:
Target launch to ISS no earlier than August of 2026
Ohalo III will serve as a platform to develop advance water delivery and volume optimization concepts that will enable future crop production operations on long duration exploration missions. Following these evaluations, Ohalo III will continue to serve as the first operational crop production system in space where it 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 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.
Project Objective
The work by the University of Texas at El Paso (UTEP) and Marshall Space Flight Center (MSFC) seeks to develop In-space joining for manufacturing structures and components in microgravity via robotic autonomous and semi-autonomous methods.
Project Description
In-space joining for manufacturing structures and components via laser beam welding and other melt-fusion and even solid-state processes will be greatly enhanced by robotic autonomous and human-in-the-loop semi-autonomous methods.
The work by UTEP and MSFC seeks to incrementally develop this very technology. Initially, the work will be developed in 2D on an air table, where the robotic components swarm consisting of three robots, two fixturing and one welding arm bearing, will glide and maneuver on the air table via pulsed air jets on their individual platforms thereby simulating thrusters. Eventually this 2D complex dance will be generalized to 3D.
Currently the entirety of the 2D fixturing and alignment, guidance and setup has been perfected. The avionics and telemetry work well enough to bring, align and fixture two plates abutting to within NASA specifications for the subsequent laser weld for the join.
The robotic arm bearing the laser (say) is being tested for space operations onboard a near future planned orbital sounding payload mission.
As mentioned, the eventual goal will be to combine these all into a 3D payload for microgravity testing of the swarm if unconnected and independent, or the multi armed robot(s) if a combined design is preferred, both approaches being incorporated and incorporate-able for future designs and missions.
Project Results and Conclusions
Currently the entirety of the 2D fixturing and alignment, guidance and setup has been perfected. The avionics and telemetry work well enough to bring, align and fixture two plates abutting to within NASA specifications for the subsequent laser weld for the join.
The robotic arm bearing the laser (say) is being tested for space operations on board a near future planned orbital sounding payload mission.
As mentioned, the eventual goal will be to combine these all into a 3D payload for microgravity testing.
Microgravity and vacuum environments are hard to work. Therefore builds of joined structures and components would benefit from robotics, autonomous or even as human assists. The project is working on gradual development of these manufacturing in-space technologies. If successful, the low Earth orbit (LEO) environment could see enhanced manufacturing capability in the foreseeable (near) future. Scaffolds and super structures for gas stations and research laboratories assembly and manufacturing are well within the stated goals of applications for an autonomous or even astronaut assisting, i.e., semi-autonomous joining/welding manufacturing platform(s).
Project Objective
A comprehensive characterization of AM GRCop-42 deposited using infra-red (IR) laser and green laser sources are vital to quantify the potential differences in part quality including microstructure, mechanical, and fatigue properties. This is essential to ensure the safe and successful implementation of AM GRCop-42 processed with different lasers.
Project Description
The project is centered on explaining the interrelationship among microstructural characteristics, mechanical properties at both micro- and macro- (global) scales, and the fatigue performance under force control conditions (R=0.1, 103 to 5×106 cycles) of thin-wall LP-DED GRCop-42 specimens fabricated by green laser and infra-red laser. The hypothesis behind the proposed investigation would then be that the lower heat input required to fully melt the powder during green laser deposition will result in different mechanical properties than the traditional infra-red laser due to different solidification behavior. Therefore, the properties cannot be assumed to be the same for both fabrication processes. Such factors significantly impact key microscopic features, including grain structure (e.g., size, orientation) and volumetric defect characteristics, thereby exerting critical effects on mechanical properties, particularly local properties, and fatigue performance. Therefore, material properties, such as strength and elongation, cannot be assumed to be equal between the two deposition methods.
By undertaking this study, we will not only address a critical gap in the understanding of how different laser sources (green versus infra-red) affect the properties of AM GRCop-42 but also provide invaluable insights that can drive the development of more efficient and cost-effective manufacturing processes as well as characterization methods. This research holds the potential to significantly advance the field of high-performance materials for aerospace applications, aligning with strategic priorities in both academic and industrial settings. Furthermore, the findings from this project could inform the development of new standards and guidelines for the AM industry, ensuring the production of superior quality components for future aerospace innovations.
Project Results and Conclusions
We completed the investigation of the mechanical and microstructural properties of additively manufactured GRCop-42 and GRCop-84 alloys, focusing on correlating nanoindentation metrics with tensile properties to determine the hardness-strength relationship. We found out that L-PBF GRCop-42 samples, characterized by finer and more homogeneous grain structure along with moderate crystallographic texture, exhibit enhanced mechanical performance compared to their LP-DED counterparts. The next step of the project is high cycle fatigue (HCF) tests with R value of 0.1 that is ongoing.
From a manufacturing standpoint, the relationships between the AM heat input sources, the characteristic features of grain structure, and their impacts on local and global mechanical properties, as well as the fatigue performance are quantified. This knowledge will facilitate the optimization of build parameters to enhance part quality, ensuring reliable and efficient implementation of AM GRCop-42 in rocket engine combustion chambers. In particular, the detailed fatigue analysis will provide critical insights into the material's long-term performance under cyclic loading conditions, contributing to safer and more durable LP-DED aerospace components.
Project Objective
The objective of this project is to improve understanding of additive manufactured and polished surface texture on aerodynamics and heat transfer for GRX-810 turbine blade surfaces through experimental wind tunnel linear cascade turbine test section.
Project Description
GRX-810 is an additively manufactured NASA alloy with longer creep life and higher ultimate strength at high temperatures than available nickel-based superalloys. Due to these properties, GRX-810 is a potentially enabling material for turbomachinery which operates in high temperature environments. The long-term goal is to infuse additively manufactured GRX-810 as a commercial turbomachinery material. The primary obstacle to commercial aerospace infusion is a lack of understanding of the effects of post processing, which is required for additively manufactured components, on turbine aerodynamic and thermal performance, both of which are critical for engine designers to understand.
Project Results and Conclusions
Hardware constructed included six GRX-810 turbine blades manufactured with laser powder bed fusion with varying surface enhancements such as built condition, chemical milling micromachining, abrasive flow machining, electropolishing chemical mechanical polishing and conventional machining. A transonic five-bladed linear cascade wind tunnel test section was equipped to measure surface heat transfer with the transient impulse response infrared thermography and a one-dimensional spatially varying traverse to measure wake profile losses. Aerodynamic loss parameters including pressure loss coefficient, integrated aerodynamic loss, and entropy generation were measured and compared for each surface condition. Spatially resolved heat transfer coefficients, adiabatic wall temperature, and reconstructed heat flux were determined for each surface condition. Results were delivered to industry in a journal publication. A Master’s thesis was produced as a result of this project.
The benefit of this project is that experimental heat transfer and aerodynamic turbomachinery data with additively manufactured laser powder bed fusion GRX-810 is transferred to commercial aerospace industry and academia. The effects of surface texture for GRX-810 and laser powder bed fusion surfaces with various surface finishing techniques on turbine performance is quantified. Broader applications of GRX-810 micro surfaces with various surface enhancement post processing methods on heat and mass transfer is better understood through this experiment for industry use of GRX-810 in engine components.
Project Objective
This project seeks to develop a surface coating for transparent windows (made of, for example, silicon glass or polycarbonate), exposed to the lunar surface, that reduces adhesion of the coated surface to lunar regolith/dust.
Project Description
The objective is to develop a high-conductivity, low-surface-energy coating for transparent windows to mitigate dust adhesion in a lunar environment. To achieve the objective, the following are being performed:
- Deposit transparent diamond-like carbon coatings using pulsed laser deposition with parameters and doping materials leading to low transparency, low surface energy, low surface roughness, high electrical conductivity, good coating adhesion to the glass/polycarbonate substrate, and high hardness; and
- Evaluate the films for transparency, surface energy, surface roughness, electrical conductivity, hardness, and resistance to solid particle erosion and three-body abrasive wear.
Project Results and Conclusions
The University of Tennessee Space Institute (UTSI), the external project lead, successfully deposited transparent continuous low-roughness diamond-like carbon (DLC) coatings on silicon glass. Attempts have been made to deposit coatings on polycarbonate, but instances of coating cracks have been identified; work continues for coatings on polycarbonate. The DLC coatings have been optimized with alumina (Al2O3) as a dopant to increase the transparency. Other dopants were tried, including silicon and magnesium fluoride (MgF2), but Al2O3 (at 25% of the whole DLC/Al2O3 composition) produced the best combination of high transparency (the most important property for a transparent substrate), high hardness (for wear resistance), relatively low roughness, and low surface energy (for low surface adhesion). The best deposition temperature is still being determined. Current specimens have deposition temperatures of 100° C, 150° C, and 200° C; specimens with coatings deposited at these temperatures are being studied.
Solid particle erosion tests have so far shown wear of the entire coating thickness for DLC coatings even at moderate particle speeds. This likely indicates that thicker coatings are required for use at the lunar surface. UTSI is looking at methods to deposit at higher thickness. Abrasive wear tests will be completed before the project end date.
New materials must be developed for the harsh conditions on the Moon, as NASA looks to a long-term presence there. Transparent surfaces must be protected against lunar dust adhesion - adherence of too much dust will degrade the ability of people to see through it. Such surfaces must also be protected from excessive abrasive wear and erosive wear caused by the abrasive dust. A coating like this could be useful for Habitat Systems and Human Landing Systems (HLS). HLS and HLS commercial partners have shown interest in dust coatings and other technologies under development.
With the prospect of dust storms on Mars, a coating like the one being developed here might also be beneficial for Mars.
Project Objective
Igneon Aerospace (Hyperion) is addressing the relatively limited market availability of low-toxicity thrusters by developing small spacecraft-scale thrusters which can use multiple blends of the the Advanced Space Craft Energetic Non-Toxic (ASCENT) family of ionic liquid propellants.
Project Description
Igneon Aerospace (formerly Hyperion) aims to develop and demonstrate a new generation of low-toxicity monopropellant thrusters that use ASCENT and its blends (e.g., DM-4) developed by the Air Force Research Laboratory (AFRL). The goal is to provide affordable, high-performance, and both low-cost and relatively easily manufacturable thruster products for small spacecraft.
Goals of this project include:
Project Results and Conclusions
With FY25, Igneon has successfully designed both the 0.2-N and the 22-N ASCENT thruster per the Cooperative Agreement Notice (CAN) with NASA MSFC. The 0.2-N thruster components were successfully manufactured, assembled, and subsequently performed acceptance testing with ASCENT, estimating a move from TRL-4 to TRL-6. Hyperion has recently overcome challenges with acquisition of the DM-4 propellant blend as well as longer than anticipated lead times for the manufacturing of the 22-N thruster. This has led to the need for an extension of this effort. Igneon hopes to complete a 0.2-N thruster test campaign with DM-4 as well as an eventual assembly and test of the 22-N thruster.
Project benefits include increasing thruster options for small spacecraft which use non-toxic propellants in small and larger thruster classes. Additional benefits include reduction in cost and overall lead time of manufacturing small satellite non-toxic thrusters. Also, the thrusters produced by Igneon will demonstrate use for various blends of ASCENT; this will allow for a wider range of applications for dual-mode (chemical and electrospray) propulsion systems and mission classes.
ARMS is a low size, weight, and power (low SWaP) non-contact temperature measurement system. It addresses long-standing problems associated with reliably obtaining measurements of high temperatures on structures during high speed and reentry flight. ARMS can be adapted to provide however many measurements a given platform requires. Successes to date have earned it a FY24 Flight Opportunity.
ARMS will significantly increase the ROI of flight testing high speed vehicles by reliably collecting high temperature data that can be used to validate models and greatly aid mishap investigations. This will in turn benefit the national ability to field high speed and reentry systems.
No details available.