In design study of modularized electric-propulsion system adaptable to several planetary missions, two spacecraft designs were derived; one, sized for Titan III-M could perform Mars orbiter/lander missions during 1971 to 1979 launch opportunities; second, sized for SLV-3C/Centaur, could perform Jupiter flyby mission; based on optimum design points, 9.6-kw system for Mars orbiter, and 17-kw system for Jupiter flyby spacecraft were designed; these ion-engine systems, consisting of thruster arrays, storage and feed systems, and powerconditioning and control systems, are designed to satisfy requirements of mission, reliability, solar power source, and spacecraft integration; designs were based on state-of-art mercury-bombardment ion thrusters. (17791)
Solar-electric propulsion systems for unmanned space missions
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 11
1968
7 pages
Article (Journal)
English
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