This paper presents the methodology used in optimizing extended propulsion time NEP missions considering realistic thruster lifetime constraints. These missions consist of a powered spiral escape from a 700-km circular orbit at the earth, followed by a powered heliocentric transfer with an optimized coast phase, and terminating in a spiral capture phase at the target planet. This analysis is most applicable to those missions with very high energy requirements such as outer planet orbiter missions or sample return missions where the total propulsion time could greatly exceed the expected lifetime of an individual thruster. This methodology has been applied to the investigation of NEP missions to the outer planets where examples are presented of both constrained and optimized trajectories.
Optimization of extended propulsion time nuclear-electric propulsion trajectories
Astrodynamics Specialist Conference ; 1981 ; Lake Tahoe, NV, US
1981-08-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Optimal Earth-Moon Trajectories Using Nuclear Electric Propulsion
Online Contents | 1997
|Optimal Earth-Moon Trajectories Using Nuclear Electric Propulsion
British Library Conference Proceedings | 1996
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