The determination of optimal trajectories for the aeroassisted flight experiment (AFE) is discussed. 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 ordinary differential equations (ODEs) describing the atmospheric pass. The atmospheric entry conditions are given, and the atmospheric exit conditions are adjusted. Two possible transfers are considered: (1) indirect ascent to a 178 NM perigee via a 197 NM apogee; and (2) direct ascent to a 178 NM apogee.


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    Title :

    Optimal Trajectories for the Aeroassisted Flight Experiment


    Contributors:
    A. Miele (author) / T. Wang (author) / W. Y. Lee (author) / Z. G. Zhao (author)

    Publication date :

    1989


    Size :

    25 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English