Study of the multimission capability of a solar electric propulsion spacecraft. The study includes such factors as spacecraft constraints, payload variations with launch opportunity, propellant on-loading and off-loading requirements, and limitations in thrusting time, throttling range and steering. The study determined that a single spacecraft design, with P sub zero = 12 kW and I sub s = 3000 sec launched by a Titan IIIC or Titan IIID/Centaur can be used to conduct at least five diverse missions: Eros rendezvous, 1 AU out-of-ecliptic, Mercury orbiter, Jupiter flyby/probe, and Jupiter orbiter. Flight time and injection velocity vary as needed to achieve the desired payload capability. The mission analysis approach and results are presented.
Mission analysis for design of a SEP multi-mission spacecraft.
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1972 ; San Diego, CA
1972-01-01
Conference paper
No indication
English
SLUB | 1992
|TIBKAT | 1998
|SLUB | 1998
|SLUB | 1996
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