Use of microthrust engines in investigations of heating of adjacent spacecraft surfaces by control rocket plume impingement, and radiation from hot nozzle walls offers low cost approach; scaling studies indicate that radiation heat-transfer process from hot nozzle walls is scalable geometrically; scalability of convection heat-transfer process requires that p/x be held constant where p is density of plume gases and x is travel of gases along surface; if scale factor (SF) is ratio of any two corresponding lengths on subscale and full-scale unit, respectively, flow rate of microrocket will be (SF)3 times flow rate of full-scale unit; results of test program conducted.


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    Titel :

    Microthrust engines for investigation of spacecraft surface heating


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Lehrer, S. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1966


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :