The determination of optimal trajectories for the aero-assisted flight experiment (AFE) is investigated. The intent of this experiment is to simulate a GEO-to-LEO transfer, where GEO denotes a geosynchronous Earth orbit and LEO denotes a low Earth orbit. The trajectories of an AFE spacecraft are analyzed in a 3D-space, employing the full system of 6 ODEs describing the atmospheric pass. The atmospheric entry conditions are given, and the atmospheric exit conditions are adjusted in such a way that the following conditions are satisfied: (1) the atmospheric velocity depletion is such that, after exiting, the AFE spacecraft first ascends to a specified apogee and then descends to a specified perigee; and (2) the exit orbital plane is identical with the entry orbital plane. The final maneuver, not analyzed here, includes the rendezvous with and the capture by the space shuttle.


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    Titel :

    Optimal Trajectories for the Aeroassisted Flight Experiment. Part 3: Formulation, Results, and Analysis


    Beteiligte:
    A. Miele (Autor:in) / T. Wang (Autor:in) / W. Y. Lee (Autor:in) / Z. G. Zhao (Autor:in)

    Erscheinungsdatum :

    1989


    Format / Umfang :

    59 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch