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Spacecraft Power Systems - MIT OpenCourseWare

Spacecraft Power Systems David W. Miller John Keesee Electrical Power System EPS. Power Energy Power Power Regulation Source Storage Distribution and Control Power Sources Primary Batteries Radioisotope Secondary Battery Thermionic converter Fuel cell Thermoelectric converter Regenerative fuel cell Photovoltaic Chemical dynamic Solar dynamic Nuclear Flywheel Storage Electrodynamics Tethers Propulsion-charged tether Power Source Applicability 100. NUCLEAR THERMIONICS. SOLAR DYNAMIC AND. FUEL CELL PHOTOVOLTAIC. NUCLEAR. LOAD Power (kW). 10. CHEMICAL.

high temperature source • Temperature gradient between the p-n junction provides the electrical output • High temperatures – Lead telluride (300 – 500 deg C, silicon germanium >600 deg C • Excess heat must be removed from the spacecraft

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  High, Temperatures, Mit opencourseware, Opencourseware, High temperature, Spacecraft

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