Major technical challenges which were met in the design and development of the Space Shuttle Orbiter Radiator System are discussed. This system rejects up to 30 kW of waste heat from eight individual radiators having a combined surface area of 175 sq m. The radiators, which are deployable, are mounted on the inside of the payload bay doors for protection from aerodynamic heating during ascent and re-entry. While in orbit the payload bay doors are opened to expose the radiators for operation. An R21 coolant loop accumulates waste heat from various components in the Orbiter and delivers the heat to the radiators for rejection to space. Specific challenges included high acoustically induced loads during lift-off, severe radiating area constraints, demanding heat load control requirements, and long life goals. Details of major design and analysis efforts are discussed. The success of the developed hardware in satisfying mission objectives showed how well the design challenge was met.


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    Titel :

    Challenges in the development of the orbiter radiator system


    Beteiligte:
    Williams, J. L. (Autor:in) / Oren, J. A. (Autor:in) / Modest, M. F. (Autor:in) / Howell, H. R. (Autor:in)


    Erscheinungsdatum :

    1985-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Space shuttle orbiter radiator system

    Williams, J. / French, R. | Tema Archiv | 1977


    Qualification of the Space Shuttle Orbiter Radiator System

    Howell, H. R. / Williams, J. L. | SAE Technical Papers | 1982


    Orbiter Radiator Panel Solar Focusing Test

    Howell, Harold R. / Rankin, J. Gary | SAE Technical Papers | 1983


    Shuttle Orbiter Radiator Performance during the OFT Program

    Benko, Donald J. | SAE Technical Papers | 1983