In order for Shuttle payload heat rejection systems to have relatively universal applicability, they must be designed to overcome several current radiator design limitations. Specifically, radiator systems for most Shuttle payload space missions will need to be compactly stored during launch, subsequently deployed in orbit and, in many cases, be reliable for a long period of time in the micrometeroid environment. Thus, the primary technical objective of development activity has been to develop a low-cost space radiator system that can overcome one or all of these limitations. Four separate advanced space radiator concepts have been pursued in an integrated effort to develop multi-payload use, low-cost heat rejection systems which can overcome the limitations of current radiator systems. (Peters)


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    Titel :

    Radiator heat rejection options for shuttle payloads


    Weitere Titelangaben:

    Wahl eines Kuehlerwaermeabfuhrsystems fuer Raumfahrtanwendungen


    Beteiligte:
    Ellis, W.E. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1979


    Format / Umfang :

    16 Seiten, 14 Bilder, 7 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Integrating Shuttle payloads

    Jean, O. C. / Lester, R. C. | NTRS | 1977


    Shuttle entry technology payloads

    Siemers, P. M., III | NTRS | 1975


    Communication with Shuttle payloads

    Springett, J.C. / Udalov, S. | Tema Archiv | 1978


    Development of shuttle payloads

    Murphy, J. T. | NTRS | 1977


    Small payloads for the Shuttle

    Nygaard, M. A. | NTRS | 1982