The Orbiter entry guidance system controls the Space Shuttle Orbiter from the initial atmospheric penetration point to the point at which an earth relative velocity of 2500 feet/second is reached. At the latter point, control of the Orbiter is transferred to the terminal area energy management system. The entry guidance system is based on the concept that the range to be flown during entry is a unique function of the drag deceleration profile flown throughout the entry. The range prediction during entry is based on analytic equations which are simple drag deceleration functions of earth relative velocity above Mach 10.5 and energy with respect to the earth below Mach 10.5. Flight through the entry corridor is accomplished by linking these simple drag deceleration functions together in series in order to define a drag deceleration reference profile. The results of the first three Space Shuttle missions have not only verified the entry guidance concept but have also demonstrated the stability of the guidance system.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Atmospheric guidance techniques and performance


    Beteiligte:
    Harpold, J. C. (Autor:in) / Gavert, D. E. (Autor:in)

    Kongress:

    Guidance and Control Conference ; 1982 ; San Diego, CA


    Erscheinungsdatum :

    1982-01-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Atmospheric guidance techniques and performance

    HARPOLD, J. / GAVERT, D. | AIAA | 1982


    Exo-Atmospheric Mid-Course Guidance

    Gutman, Shaul / Rubinsky, Sergey | AIAA | 2015



    Four-dimensional guidance of atmospheric vehicles

    Stiharu-Alexe, Ilie / O'Shea, Jules | AIAA | 1996


    Atmospheric Reentry Guidance of Manned Spacecraft

    Wang, Z. / Han, C. / Beijing University of Aeronautics and Astronautics | British Library Conference Proceedings | 1994