System studies have shown that Earth entry test could be used to demonstrate value of atmospheric sensing instrumentation systems to be used during descent into Martian atmosphere, in its "proofing " of operation of aerodynamic retardation systems, and in demonstration of communications link operation under actual conditions of vehicle motion and plasma sheath blackout; factors and limitations of test are discussed; hypothetical test program for small (28 in. diam. 30-lb) Mars atmospheric probe illustrates application of type of test, using three-stage Scout as launch vehicle.


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    Title :

    Earth entry flight test of mars entry vehicles


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Beuf, F.G. (author) / Katz, G.D. (author) / Kern, R.J. (author)

    Published in:

    Publication date :

    1966


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Earth entry flight test of mars entry vehicles

    BEUF, F. / KATZ, G. / KERN, R. | AIAA | 1965


    Earth entry flight test of Mars entry vehicles.

    BEUF, F. G. / KATZ, G. D. / KERN, R. J. | AIAA | 1966


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