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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    Title :

    Thermal sterilization of spacecraft structures


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Tenney, J.B. (author) / Fried, E. (author) / Crawford, R.G. (author)

    Published in:

    Publication date :

    1966


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



    Thermal sterilization of spacecraft structures.

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


    THERMAL STERILIZATION OF SPACECRAFT STRUCTURES

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


    Spacecraft sterilization - thermal considerations.

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


    Spacecraft sterilization - thermal considerations

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