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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Summary and Status of 5 Mechanical Pumped Fluid Loop (MPFL) Projects Currently in Process at the Jet Propulsion Laboratory (JPL) for the Planned Europa Mission, Mars 2020, Ecosystem Spaceborne Thermal Radiometer Experiment on Space Station (ECOSTRESS), Orbiting Carbon Observatory (OCO-3), and Cold Atom Lab (CAL)
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Inflatable Solar Sails for Low-Cost Robotic Mars Missions
This paper presents an evaluation of the use of solar sails based on inflatable-structures technologies to perform low-cost robotic planetary missions.
Human Mars Mission In-Space Transportation Sensitivity for Nuclear Electric / Chemical Hybrid Propulsion
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Increased Risk of Exposure Induced Death Associated with Clonal Hematopoiesis of Indeterminate Potential for Mars Mission Scenarios
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Crewed Mars Mission Mode Options for Nuclear Electric/Chemical Hybrid Transportation Systems
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Mars Mission Duration Guidance for Human Risk Assessment and Research Planning Purposes
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Crewed Mars Mission Concepts
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Risk of Exposure Induced Death Associated with Clonal Hematopoiesis of Indeterminate Potential for Mars Mission Scenarios
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Brayton Cycle Power Conversion Model for MW-Class Nuclear Electric Propulsion Mars Missions
A Brayton cycle based power conversion system for a nuclear electric propulsion application was modeled in Simulink as part of NASA’s space nuclear program in order to explore the impact of technology assumptions on the power conversion system performance and capabilities. The thermodynamic processes and algorithms within the model are documented, including a higher fidelity reactor model. Assumptions are chosen based on literature and subject matter expert review, and example results and capabilities of the model are shown. The effects of the turbine inlet and compressor inlet temperature on radiator area and thermal efficiency are discussed. For a He-Xe closed Brayton cycle, radiator areas as low as 650 m2/MWe are shown, with corresponding thermal efficiences at roughly 20% for the minimal radiator area solutions.
Brayton Cycle Power Conversion Model for MW-Class Nuclear Electric Propulsion Mars Missions
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