Objective of design study was to show feasibility of system; to uncover specific problem areas, Mars orbiter mission utilizing Saturn IB/Centaur boost vehicle was chosen as mission model; design constraints evaluated include requirements of mission, interface problems between spacecraft and propulsion system, and characteristics of state-of-art ion engine subsystems; that is, thruster, feed system, power conditioning, and controls; conceptual design of 48-kw-propulsion system is developed.
Design of solar-electric propulsion system for interplanetary spacecraft
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 2
1967
7 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Interplanetary spacecraft design using solar electric propulsion
Tema Archive | 1974
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