Four- and five-impulse trajectories for manned Mars stopover missions are compared with respect to initial mass in Earth orbit (IMEO) to determine advantages or disadvantages associated with use of three-impulse outbound or inbound segments; three-impulse trajectory segments are generated using analogy between primer vector on low-thrust transfer and corresponding impulse-thrust transfer; results obtained apply specifically to Mars missions in 1980 time period with Earth entry speed of 60,000 fps; results of other mission types studied.
Earth-orbit masses for five-impulse Mars stopover missions in 1980
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 5
1968
5 pages
Article (Journal)
English
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OPTIMIZATION OF INTERPLANETARY STOPOVER MISSIONS
AIAA | 1963
|Earth-orbit weights for manned mars missions.
NTRS | 1965
|