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- W2079470044 abstract "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." @default.
- W2079470044 created "2016-06-24" @default.
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- W2079470044 date "1972-01-17" @default.
- W2079470044 modified "2023-10-02" @default.
- W2079470044 title "Mission analysis for design of a SEP multi-mission spacecraft" @default.
- W2079470044 doi "https://doi.org/10.2514/6.1972-51" @default.
- W2079470044 hasPublicationYear "1972" @default.
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