Saturn IB/Centaur- and Atlas/Centaur-launched electric propulsion vehicles employing near-future-solar cell power supplies (50 to 100 lb/kwe) are shown to be attractive systems for performing close solar probe emission; performance calculations include optimization of launch vehicle burnout velocity, electric stage specific impulse and power level, and thrust orientation for constant specific impulse thrusters; results obtained for constant-power operation of thrusters and solar-cell-powered electric systems.
Solar-electric propulsion system performance for close solar probe mission
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 4
1967
7 pages
Aufsatz (Zeitschrift)
Englisch
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