A sensitivity analysis of the factors which affect a successful abort maneuver following a space shuttle launching is presented. Wind tunnel tests were conducted using optimum simulation techniques and data acquisition procedures. Static stability, dynamic stability, and local loads were investigated. It is concluded that parallel abort separation of the space shuttle components is possible at both high and low dynamic pressures. Successful separation is dependent upon configuration, Mach number, rocket exhaust impingement and relative position and attitude of the stages.


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    Title :

    Abort separation of the shuttle


    Contributors:


    Publication date :

    1972-02-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


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