The feasibility and practicality of employing an aerobraking trajectory for return of the reusable space tug from geosynchronous orbit was investigated. The aerobraking return trajectory modes employ transfer ellipses from high orbits which have low perigee altitudes wherein the earth's sensible atmosphere provides drag to reduce the tug return delta velocity requirements and thus decrease the required return trip propulsive energy. Aerodynamics, aerothermodynamics, trajectories, guidance and control, configuration concepts, materials, weights and performance were considered. Sensitivities to trajectory uncertainties, atmospheric anomalies and reentry environments were determined. New technology requirements and future studies required to further enhance the aerobraking potential were identified.


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    Title :

    Space tug aerobraking study. Volume 1: Executive summary


    Contributors:
    Corso, C. J. (author) / Eyer, C. L. (author)

    Publication date :

    1972-04-12


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


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