Qualitative evaluation indicates that low-density charring ablators are most likely to meet all requirements; low density-foamed-silicone (LDFS) and epoxy-modified-silicone (ESM) were subjected to various tests, designed to simulate ground, flight, and entry environmental conditions expected to be encountered; LDFS survived thermal cycling to temperatures as low as -300 F; ESM survived to -275 F; change of base elastomer to phenyl-methyl silicone should give even better low-temperature capability; both heat-protection materials are capable of meeting all mission requirements. (15093)


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    Title :

    Thermal protection systems for mars-entry vehicle


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Hiltz, A.A. (author) / Florence, D.E. (author) / Lowe, D.L. (author)

    Published in:

    Publication date :

    1968


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Thermal protection systems for a Mars-entry vehicle.

    FLORENCE, D. E. / HILTZ, A. A. | AIAA | 1968


    Thermal protection systems for a Mars-entry vehicle

    FLORENCE, D. / HILTZ, A. | AIAA | 1968




    Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System

    Edquist, Karl T. / Hollis, Brian R. / Dyakonov, Artem A. et al. | NTRS | 2007