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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    Titel :

    Space tug aerobraking study. Volume 1: Executive summary


    Beteiligte:
    Corso, C. J. (Autor:in) / Eyer, C. L. (Autor:in)

    Erscheinungsdatum :

    1972-04-12


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Space Tug Aerobraking Study. Volume 1 Executive Summary

    C. J. Corso / C. L. Eyer | NTIS | 1972


    Space Tug Aerobraking Study. Volume 2 Technical

    C. J. Corso / C. L. Eyer | NTIS | 1972


    Space Tug Aerobraking Study. Volume 2: Technical

    Corso, C. J. / Eyer, C. L. | NTRS | 1972


    Autonomous Aerobraking Development Software: Phase 2 Summary

    Cianciolo, Alicia D. / Maddock, Robert W. / Prince, Jill L. et al. | NTRS | 2013


    Aerobraking for space exploration

    Eldred, Charles H. | NTRS | 1992