This paper describes the design and performance of the Astro Integrated Radiator System (IRS). The system was recently ground tested and proven successful in rejecting approximately 400 watts of heat. The radiator was constructed from an aluminum panel configured to form two orthogonal planes. Heat pipes were adhesively bonded and riveted to the radiator to isothermalize the surface. The IRS was subjected to a full thermal vacuum test to validate the thermal math model and to qualify the radiator for space flight. The thermal performance met prescribed temperature limits with margins at both extremes, and no mechanical failures occurred.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Performance of the Spacelab Astro-1 Mission Heat Pipe Radiator


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:

    Kongress:

    Intersociety Conference on Environmental Systems ; 1985



    Erscheinungsdatum :

    1985-07-01




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Performance of the Spacelab Astro-2 Mission Integrated Radiator System

    Watkins, Hugh H. / Hamner, Richard M. | SAE Technical Papers | 1996


    Flight Performance of the Spacelab Astro-1 Mission Integrated Radiator System

    Hornsby, Linda S. / Hamner, Richard M. | SAE Technical Papers | 1991


    Astro-2 Spacelab Instrument Pointing System mission performance

    Wessling, is C, I, Francis / IISingh, S | AIAA | 1995


    Orbiter attitude design for the Astro-1 Spacelab mission

    Olsen, C. D. / Echols, R. T. / Woods, W. K. et al. | NTRS | 1992


    Orbiter attitude design for the Astro-2 Spacelab Mission

    Horvath, T / Grimaldi, R / Onken, J et al. | AIAA | 1995