A transient thermal analysis of a Carbon/Carbon (C/C) Mars Entry Non-Ablative Aeroshell Assembly was performed to determine the maximum temperatures it would reach during a Mars entry. The purpose of this thermal analyses was to (1) determine the maximum temperatures of the 5 layers and the close-out which make up the aerothermal shield and (2) to transmit these temperatures from SINDA/G finite difference format to finite element format in COSMOS/M structures/dynamic models using Technical Alliance Group (TAG) developed SINDA/ G temperature translator software (STT).


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    Titel :

    Thermal Engineering of Mars Entry Non-Ablative Aeroshell Part 1


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:

    Kongress:

    International Conference On Environmental Systems ; 1999



    Erscheinungsdatum :

    1999-07-12




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch





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