An account is given of the flight testing development phase of the Space Shuttle Orbiter. Because of its low lift-to-drag ratio, the Orbiter must make its 280-kt landing approach in the lower atmosphere with a steep descent angle of 19 deg, pulling up at 1800 feet altitude to a 1-1.5 deg descent angle, and finally gliding to a landing at 195 kt. The Orbiter has almost neutral aerodynamic static stability in pitch and yaw, requiring the use of electronic stabilization to augment the vehicle's natural stability. Attention is given to the flight test program, which comprised the first four flights of the Space Shuttle, and which substantially relied on preflight analysis to establish confidence in Shuttle flight performance. Also discussed are the solar radiation absorption and aerodynamic heating characteristics


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Flight testing of the Space Shuttle


    Beteiligte:
    Brand, V. D. (Autor:in)

    Erschienen in:

    CIDA ; 6 , 6, 19


    Erscheinungsdatum :

    01.01.1981


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Space shuttle orbital flight testing

    Hartsfield, H. W., Jr. | NTRS | 1979


    Space Shuttle orbital flight testing

    Hartsfield, H. W., Jr. | NTRS | 1979


    Aerodynamic flight testing of the Space Shuttle Orbiter

    Barton, R. L. / Culp, M. A. | NTRS | 1985


    Aerodynamic Flight Testing of the Space Shuttle Orbiter

    Culp, Micheal A. / Barton, Richard L. | SAE Technical Papers | 1985


    Space Shuttle flight operations.

    Carlton, R. L. | NTRS | 1973