Preflight predictions of the structural temperature distributions during entry are compared with data from the initial Shuttle flight. Finite element thermal analysis programming was used to model the heat flow on Shuttle structures and actual gas properties of air were employed in the analyses of aerodynamic heating. Laminar, separated, and turbulent heat fluxes were calculated for varying locations on the craft using velocity-attitude and angle-of-attack projections taken from the nominal STS-1 trajectory. Temperature time histories of the first flight are compared with laminar and turbulent flow assumptions and an unpredicted rapid cooling 1800 sec into entry is credited to inaccurate assumptions of structural heat dissipative properties or flow conditions in that time phase of the flight; additional discrepancies in descriptions of heating of the upper fuselage are attributed to a lack of knowledge of the complex flow patterns existing over that area of the Shuttle body.


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    Title :

    Preflight reentry heat transfer analysis of Space Shuttle


    Contributors:
    Ko, W. L. (author) / Quinn, R. D. (author) / Gong, L. (author) / Schuster, L. S. (author) / Gonzales, D. (author)

    Conference:

    Flight Testing Conference ; 1981 ; Las Vegas, NV


    Publication date :

    1981-11-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


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