A study has been conducted to analytically and experimentally determine the structural and thermal performance benefits of composite isogrid structures for a range of spacecraft applications. The analytical results indicated that an isogrid panel can be constructed to meet both the bending stiffness and mass requirements for a range of spacecraft applications, but with a slightly greater panel height compared to the conventional designs. Thermal analysis indicated that the isogrid concept offers the prospect of lower operating temperatures relative to that experienced with honeycomb panels. A comparative cost analysis has also been conducted between the isogrid and honeycomb sandwich constructions.


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    Title :

    Composite isogrid structures for spacecraft components


    Contributors:
    Silverman, E. (author) / Rhodes, M. (author) / Dyer, J. (author)


    Publication date :

    1998


    Size :

    10 Seiten


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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