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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    Title :

    Microthrust engines for investigation of spacecraft surface heating


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Lehrer, S. (author)

    Published in:

    Publication date :

    1966


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :