A structural performance and resizing (SPAR) finite-element computer program and NASA structural analysis (NASTRAN) finite-element computer programs were used in the thermal stress analysis of the space shuttle orbiter subjected to reentry aerodynamic heating. A SPAR structural model was set up for the entire left wing of the orbiter, and NASTRAN structural models were set up for: (1) a wing segment located at midspan of the orbiter left wing, and (2) a fuselage segment located at midfuselage. The thermal stress distributions in the orbiter structure were obtained and the critical high thermal stress regions were identified. It was found that the thermal stresses induced in the orbiter structure during reentry were relatively low. The thermal stress predictions from the whole wing model were considered to be more accurate than those from the wing segment model because the former accounts for temperature and stress effects throughout the entire wing.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Thermal Stress Analysis of Space Shuttle Orbiter Subjected to Reentry Aerodynamic Heating


    Contributors:
    W. L. Ko (author) / R. A. Fields (author)

    Publication date :

    1987


    Size :

    39 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Space Shuttle Orbiter Aerodynamic Development

    T.E. Surber / D.C. Olsen | AIAA | 1978


    Space Shuttle orbiter aerodynamic development

    SURBER, T. / OLSEN, D. | AIAA | 1974


    Aerodynamic heating of a space shuttle delta-wing orbiter

    Lockman, W. K. / Derose, C. E. | NTRS | 1971


    Aerodynamic Heating of a Space Shuttle delta-Wing Orbiter

    W. K. Lockman / C. E. Derose | NTIS | 1971