The methods utilized to design orbiter attitudes that satisfied the various Space Shuttle program and payload constraints of the Astro-1 Spacelab astronomy mission are described. The premission methods developed for attitude design and how those methods were applied to accomplish the large amount of real-time replanning required during the flight are presented. Some of the attitude concerns for Astro-1 included orbiter window thermal constraints, two separate telescope fields-of-view, tracking and data relay satellite Ku-band access, and telescope sun avoidance.


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    Titel :

    Orbiter attitude design for the Astro-1 Spacelab mission


    Beteiligte:
    Olsen, C. D. (Autor:in) / Echols, R. T. (Autor:in) / Woods, W. K. (Autor:in) / Onken, J. F. (Autor:in) / Horvath, T. J. (Autor:in) / Stewart, R. L. (Autor:in)

    Erscheinungsdatum :

    1992-03-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


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


    Orbiter attitude design for the Astro-1 Spacelab mission

    OLSEN, C. / ECHOLS, R. / WOODS, W. et al. | AIAA | 1992


    Astro-2 Spacelab Instrument Pointing System mission performance

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


    Performance of the Spacelab Astro-1 Mission Heat Pipe Radiator

    Cotton, Joel A. / Hamner, Richard M. / Stallings, Robert D. et al. | SAE Technical Papers | 1985


    Performance of the Spacelab Astro-2 Mission Integrated Radiator System

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