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.


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    Title :

    Earth-orbit masses for five-impulse Mars stopover missions in 1980


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Doll, J.R. (author)

    Published in:

    Publication date :

    1968


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :