The results are presented of a study to show the effect on flyback trajectories of constant inertial attitude during the fuel dissipation phase of a return-to-launch-site abort. It is shown that the value of the constant inertial attitude can be chosen to shape the flyback trajectory. (Author)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Return-to-Launch-Site Trajectory Shaping


    Beteiligte:
    R. L. Bown (Autor:in)

    Erscheinungsdatum :

    1975


    Format / Umfang :

    22 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch







    Return to Launch Site Trajectory Aeroheating for a Resuable Booster AIAA Paper

    Hellman, B. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2007


    United Trajectory Design Method for Return to Launch Site of Suborbital Reusable Launch Vehicle (AIAA 2017-2108)

    Hao, Qiao / Peng, Sun / Xinguo, Li | British Library Conference Proceedings | 2017