A wind tunnel test program of some complexity was used to define the aerodynamic forces exerted on the space shuttle solid rocket boosters and orbiter/external tank during staging. In these tests, problems associated with the use of up to three models in close proximity and with the need to simulate high pressure separation motor plumes were handled in a unique and effective manner. A new method was developed for efficiently organizing data which is a function of a large number of independent variables. Data derived from the test program drastically reduced previous estimates of aerodynamic uncertainties and allowed certification of the separation system at the design maximum staging dynamic pressure. Reduction of flight data has implicitly verified the staging aerodynamics data base and its associated uncertainties.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Shuttle booster separation aerodynamics


    Contributors:


    Publication date :

    1983-10-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English