An investigation was performed to examine the feasibility of an escape tube as an aid in crew bailout from the Shuttle Orbiter at subsonic speeds. The deployable escape tube extended from the main side hatch downwards. Wind-tunnel tests with scaled models demonstrated that successful bailout was possible when the tube exit was at least 1 foot below the wing leading edge. The aerodynamics of the Orbiter were only slightly degraded with the tube deployed. Several tube designs were investigated, the most promising of which was an inflatable elastic/fabric 'Airmat' configuration. Loads on the tube were within capability of current airmat technology.


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    Titel :

    Shuttle crew escape tube study



    Kongress:

    AIAA Flight Test Conference ; 1988 ; San Diego, CA, United States


    Erscheinungsdatum :

    01.01.1988


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Shuttle crew escape tube study

    WARE, GEORGE / SPENCER, JR., BERNARD / PRIDE, JR., JOSEPH et al. | AIAA | 1988


    NASA Space Shuttle Advanced Crew Escape Suit Development

    Barry, Daniel M. / Bassick, John W. | SAE Technical Papers | 1995


    NASA Space Shuttle Advanced Crew Escape Suit Development

    Barry, D. M. / Bassick, J. W. / SAE | British Library Conference Proceedings | 1995



    Advanced Crew Escape Suit

    Online Contents | 1995