A state-of-the-art preliminary design for typical wing areas is developed. Seven medium-density ablators (with/without honeycomb, flown on Apollo, Prime, X15A2) are evaluated. The screening tests include: (1) leading-edge models sequentially subjected to ascent heating, cold soak, entry heating, post-entry pressure fluctuations, and touchdown shock, and (2) virgin/charred models subjected to bondline strains. Two honeycomb reinforced 30 pcf elastomeric ablators were selected. Roughness/recession degradation of low speed aerodynamics appears acceptable. The design, including attachments, substructure and joints, is presented.


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    Title :

    Initial development of an ablative leading edge for the space shuttle orbiter


    Contributors:
    Daforno, G. (author) / Rose, L. (author) / Graham, J. (author) / Roy, P. (author)

    Publication date :

    1974-03-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Initial development of an ablative leading edge for the Space Shuttle orbiter.

    Daforno, G. / Graham, J. / Tompkins, S. | NTRS | 1973


    Initial development of an ablative leading edge for the Space Shuttle orbiter

    DAFORNO, G. / GRAHAM, J. / TOMPKINS, S. | AIAA | 1973


    Initial Development of an Ablative Leading Edge for the Space Shuttle Orbiter

    G. Daforno / L. Rose / J. Graham et al. | NTIS | 1974


    Ablative leading edge design concepts for the shuttle orbiter

    Graham, J. W. / Mosher, D. A. / Victer, I. | NTRS | 1971