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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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At least 271 records · Page 15
All sourcesNASA NTRSDOE OSTI
NASA NTRSDate not supplied

Design and Development of a Fluid Immersion Cooled, SiC MOSFET, 37.5 kW, Bi-Directional Motor Converter

NASA's SUb-sonic Single Aft eNgine (SUSAN) aircraft is a concept aircraft whose architecture is that of a subsonic regional jet transport aircraft. SUSAN contains a single turbofan engine coupled to an electrified aircraft propulsion (EAP) system. To provide a path towards this goal, a 25% scale version of the SUSAN aircraft is being researched. A main component of the 25% power train is the Motor And Generator Intelligent Converter (MAGIC). This paper presents the design, development, and initial test results from MAGIC, a 37.5 kW, fluid immersion cooled, silicon carbide (SiC) MOSFET-based, bi-directional converter and controller.

Immersion↗
NASA NTRSDate not supplied

Qualification Progress and Mission-Enabling Capabilities of the 12-kW Hall-Effect, Advanced Electric Propulsion System (AEPS) Thruster

An update of the 12 kW Advanced Electric Propulsion System (AEPS) qualification and flight thruster status is provided. Three flight thrusters completed acceptance testing in 2025 and have been delivered to NASA. Environmental qualification is complete and preparations are under way for long-duration life-demonstration testing. Programmatic lessons learned associated with risk management, contract oversight, and requirement definition during the fabrication and assembly are discussed. In addition, the extensibility of the AEPS thruster to enable a variety of NASA missions is presented.

Electric Propulsion↗
NASA NTRSDate not supplied

Qualification Progress and Mission-Enabling Capabilities of the 12-kW Hall-Effect, Advanced Electric Propulsion System (AEPS) Thruster

An update of the 12 kW Advanced Electric Propulsion System (AEPS) qualification and flight thruster status is provided. Three flight thrusters completed acceptance testing in 2025 and have been delivered to NASA. Environmental qualification is complete and preparations are under way for long-duration life-demonstration testing. A brief overview of three of SEP’s programmatic lessons learned are discussed: risk management, contract oversight, and requirement definition. In addition, the extensibility of the AEPS thruster to enable a variety of NASA missions is presented.

Mars Exploration↗
NASA NTRS1971

The 20 kW battery study program

Six battery configurations were selected for detailed study and these are described. A computer program was modified for use in estimation of the weights, costs, and reliabilities of each of the configurations, as a function of several important independent variables, such as system voltage, battery voltage ratio (battery voltage/bus voltage), and the number of parallel units into which each of the components of the power subsystem was divided. The computer program was used to develop the relationship between the independent variables alone and in combination, and the dependent variables: weight, cost, and availability. Parametric data, including power loss curves, are given.

Source record↗
NASA NTRS1972

Practical considerations for Abel inverting of photographic data with application to the analysis of a 15-kW wall-stabilized arc-light source

Temperature profiles were measured for agron atmospheric pressure by using absolute line and continuum intensity and were compared with stark width and shift measurements. A detailed analysis of the engineering aspects of setting up for Abel inverting deta photographically is presented. The merits of using photographic detection and of using continuum radiation for temperature profile analysis are discussed. The importance of empirically determining the optical depth is emphasized by discrepancies between measured (two-path) and calculated estimates.

Snow, W. L.↗