Trajectory design issues beyond those under consideration in the Aeroassist Flight Experiment (AFE) program and more in line with the Shuttle design concept are presented. This is deemed necessary as flight regimes encountered in Lunar/Mars aerocapture trajectories at Mars and return-to-earth will provide more stringent requirements on vehicle design than AFE and are not exactly quantifiable at this time. Investigations are conducted of areas where explicit trajectory control is practical and can most directly influence constraints critical to vehicle design for manned and unmanned interplanetary missions. Primary consideration is given to the ability to control vehicle heating during entry, and this particular area of Shuttle entry design is discussed in detail.


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    Titel :

    Lunar/Mars earth return aerocapture heating constraint


    Beteiligte:
    Cuthbert, P. A. (Autor:in) / Tigges, M. A. (Autor:in) / Bryant, L. E. (Autor:in)

    Kongress:

    AIAA/AAS Astrodynamics Conference ; 1990 ; Portland, OR, United States


    Erscheinungsdatum :

    01.01.1990


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


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    Lyne, J. E. / Tauber, M. E. / Braun, Robert D. | NTRS | 1992


    Parametric study of manned aerocapture. I - Earth return from Mars

    LYNE, J. E. / NASA, Ames Research Center / Moffett Field et al. | AIAA | 1992


    Parametric entry corridors for lunar/Mars aerocapture missions

    Ling, Lisa M. / Baseggio, Franco M. / Fuhry, Douglas P. | NTRS | 1991


    Parametric Entry Corridors for Lunar/Mars Aerocapture Missions

    L. M. Ling / F. M. Baseggio / D. P. Fuhry | NTIS | 1991