When the flying spacecraft was approved for development, a power unit for the hydraulic system had to be developed. Unlike other systems on the orbiter, there was no precedent in earlier spacecraft for a hydraulic system nor for the power unit to drive the hydraulic pumps. The only prototypes available were airplane auxiliary power units (APU), which were not required to operate in the severe environments of a spacecraft nor to have the longevity of an orbiter hydraulic power unit. The challenge was to build a hydraulic power unit which could operate in 0g or 3g, in a vacuum or at sea level pressure, and at -65 F or 225 F, which would be capable of restarting while hot, and which would be capable of sustaining the hydraulic loads for the life of the orbiter. The basic approach to providing hydraulic power for the orbiter was to use a small, high speed, monopropellant fueled turbine power unit to drive a conventional aircraft type hydraulic pump. The stringent requirements imposed on the orbiter APU quickly made this machine different from existing aircraft APUs.


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    Titel :

    Space shuttle orbiter auxiliary power unit development challenges


    Beteiligte:
    Lance, R. (Autor:in) / Weary, D. (Autor:in)


    Erscheinungsdatum :

    01.01.1985


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Space Shuttle Orbiter Auxiliary Power Unit

    Weary, D. / Baughman, J. / Wicklund, L. et al. | SAE Technical Papers | 1982


    Space Shuttle Orbiter auxiliary power unit

    Mckenna, R. / Wicklund, L. / Baughman, J. et al. | NTRS | 1982


    Space Shuttle Orbiter auxiliary power unit status

    Reck, M. / Loken, G. / Horton, J. et al. | NTRS | 1991


    Space Shuttle Orbiter improved auxiliary power unit

    Hagemann, D. W. / Wicklund, L. L. / Loken, G. R. et al. | NTRS | 1984


    Space Shuttle Orbiter Auxiliary Power Unit Status

    Loken, G. / Baughman, J. / Horton, J. et al. | SAE Technical Papers | 1991