The Shuttle Derived Vehicle (SDV) is a proposed unmanned launch system configured using Shuttle elements. The SDV incorporates two solid rocket boosters, an external tank and three Space Shuttle main engines identical to those used in the present Space Transportation System. Two new elements, a recoverable propulsion/avionics module housing the main engines and an expendable payload module, complete the SDV configuration. This paper describes the activities and results of wind tunnel tests conducted to validate the aerodynamic and controllability characteristics of SDV configurations. The configuration variables consisted of the payload module diameter, length and nose shape. The tests were conducted in the NASA/Marshall Space Flight Center 14 inch trisonic wind tunnel. Aerodynamic force and moment data were obtained over a Mach number range of 0.6 to 4.96. The attack and sideslip angles were varied + or - 8.0 deg. Forces and moments were measured by a sting-supported six component strain gage balance.


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    Titel :

    Wind tunnel test evaluation of a Shuttle derived launch system


    Beteiligte:
    Tewell, J. R. (Autor:in) / Buell, D. N. (Autor:in)

    Erscheinungsdatum :

    1986-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Shuttle derived launch vehicle wind tunnel tests

    TEWELL, J. / BUELL, D. | AIAA | 1985


    Shuttle derived launch vehicle wind tunnel tests

    Tewell, J. R. / Buell, D. N. | NTRS | 1985


    Shuttle Derived Launch Vehicles

    Horowitz, Scott / Sauvageau, Donald / O'Dell, Keith | AIAA | 2004


    Shuttle Derived Launch Vehicles

    Sauvageau, D. / O Dell, K. / Horowitz, S. J. et al. | British Library Conference Proceedings | 2004