Study assumes that sterilization environment consists of four cycles in which equilibrium temperature of 150 C is maintained for 60 hr; simplified design of lander is used to perform thermal analysis by preparing resistance network corresponding to lumped mass system; it is solved on computer and yields range of thermal gradients and material exposure times for lander during sterilization in sealed canister, which is raised to temperature of 150 C in varying times; sterilization in vacuo and in inert gas is considered; structural response of structural elements is evaluated, as well as effects on entry shield material, bond material, and bond structure.


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    Titel :

    Thermal sterilization of spacecraft structures


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Tenney, J.B. (Autor:in) / Fried, E. (Autor:in) / Crawford, R.G. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1966


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    THERMAL STERILIZATION OF SPACECRAFT STRUCTURES

    TENNEY, J. / FRIED, E. / CRAWFORD, R. | AIAA | 1965



    Thermal sterilization of spacecraft structures.

    Crawford, R. G. / Fried, E. / Tenney, J. B. | NTRS | 1966


    Spacecraft sterilization - thermal considerations.

    Fried, E. / Kepple, R. J. | NTRS | 1965


    Spacecraft sterilization - thermal considerations

    FRIED, E. / KEPPLE, R. | AIAA | 1965