A six-degree-of-freedom simulation analysis was conducted to examine the effects of the lateral-directional static aerodynamic stability and control uncertainties on the performance of the automatic (no manual inputs) entry-guidance and control systems of the space shuttle orbiter. To establish the acceptable boundaries of the uncertainties, the static aerodynamic characteristics were varied either by applying a multiplier to the aerodynamic parameter or by adding an increment. Control-system modifications were identified that decrease the sensitivity to off-nominal aerodynamics. With these modifications, the acceptable aerodynamic boundaries were determined.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Entry Dynamics of Space Shuttle Orbiter with Lateral-Directional Stability and Control Uncertainties at Supersonic and Hypersonic Speeds


    Beteiligte:
    H. W. Stone (Autor:in) / R. W. Powell (Autor:in)

    Erscheinungsdatum :

    1977


    Format / Umfang :

    103 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch