Design of passive thermal control system for 3600-lb NASA OAO, built by Grumman Aircraft Engineering Corp, is presented; spacecraft structure can be designed to operate at average of either -22 or + 32 F and maintain required thermal stability of plus or minus 18 F irrespective of pointing angle during its 1-yr lifetime; telescope thermally linked to OAO central tube and insulated from space environment will be maintained within 3 F of spacecraft structure; design uses Alzak skins as thermal control surfaces; analyses of spacecraft thermal balance and electronic equipment design.


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    Titel :

    Thermal design of orbiting astronomical observatory


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    1964


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



    Engineering design of orbiting astronomical observatory

    Scott, Jr., W.H. | Engineering Index Backfile | 1963


    The Orbiting Astronomical Observatory Thermal Test Program

    P. Caruso / C. Dan / D. Mengers et al. | NTIS | 1970


    The Orbiting Astronomical Observatory thermal test program

    CARUSO, JR., P. / DAN, JR., C. / MENGERS, D. et al. | AIAA | 1969