Research, test, and demonstration experiments necessary for establishing a data base that will permit construction of large, lightweight flexible space structures meeting on-orbit pointing and surface precesion criteria are discussed. Attention is focused on the wrap-rib proof-of-concept antenna structures developed from technology used on the ATS-6 satellite. The target structure will be up to 150 m in diameter or smaller, operate at RF levels, be amenable to packaging for carriage in the Shuttle bay, be capable of being ground-tested, and permit on-orbit deployment and retraction. Graphite/epoxy has been chosen as the antenna ribs material, and the antenna mesh will be gold-plated Mo wire. A 55-m diam reflector was built as proof-of-concept with ground-test capability. Tests will proceed on components, a model, the entire structure, and in-flight. An analytical model has been formulated to characterize the antenna's thermal behavior. The flight test of the 55-m prototype in-orbit offers the chance to validate the analytical model and characterize the control, mechanical, and thermal characteristics of the antenna configuration.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Technology requirements for large flexible space structures


    Beteiligte:
    Wada, B. K. (Autor:in) / Freeland, R. E. (Autor:in) / Garcia, N. F. (Autor:in)

    Erscheinungsdatum :

    1983-10-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch







    Microdynamic Design Requirements for Large Space Structures

    Peterson, Lee / Hinkle, Jason | AIAA | 2003


    Microdynamic Design Requirements for Large Space Structures

    Peterson, L. / Hinkle, J. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2003