An optimal thermal protection system design for a spacecraft operating in extreme environments of thermal and acoustic loading is of significant importance for today's military space missions. These military space missions tend to push the envelope of the spacecraft's capabilities to the extreme, requiring robust performance of all key systems to assure a successful mission. Because thermal protection system protects the entire spacecraft, its survival from these extreme conditions is critical to the safety of the mission. The design criteria for the thermal and acoustic loading conditions tend to be conflicting. To reduce thermal stress, free boundaries that allow for expansion of the thermal protection system are desirable. However, the random sound pressure level fluctuations associated with, for example, engine noise during ascent, subject the thermal protection system to a wide-band random excitation. Therefore, if the thermal protection system possesses low frequency modes, damaging strains could result. To limit the magnitude of the strains, higher frequency (stiffer) designs with fixity at the boundary are desirable. Therefore, when designing the thermal protection system within these two simultaneous operating environments, the safe operating region is often severely restricted. This research aims at evolving a design that satisfies these two design requirements.


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    Titel :

    Topology optimization for an evolutionary design of a thermal protection system


    Weitere Titelangaben:

    Topologieoptimierung des Wärmeschutzschildes von Raumfahrzeugen


    Beteiligte:

    Erschienen in:

    AIAA Journal (online) ; 44 , 11 ; 2663-2671


    Erscheinungsdatum :

    2006


    Format / Umfang :

    9 Seiten, 20 Bilder, 3 Tabellen, 18 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




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