Reevaluation of Vanguard program objectives in Jan 1957 resulted in production of 6.44-in. diam, 3.25-lb sphere with 6 equally spaced solar cell clusters and 6 antennas mounted on its surface; development of mechanism to separate satellite from third-stage rocket; satellite and strap pull pin girth ring arrangement were fully tested prior to flight; successful orbiting and flight operation proved adequacy of design.


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    Title :

    Vanguard I satellite structure and separation mechanism


    Additional title:

    NASA -- Tech Note


    Contributors:
    Shea, J.T. (author) / Baumann, R.C. (author)


    Publication date :

    1961


    Size :

    13 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


    Vanguard I Satellite Structure and Separation Mechanism

    Shea, John T. / Baumann, Robert C. | NTRS | 1961


    Vanguard I satellite structure and separation mechanism

    Shea, John T. / Baumann, Robert C. | TIBKAT | 1961


    Vanguard I Satellite Structure and Separation Mechanism

    J. T. Shea / R. C. Baumann | NTIS | 1961


    Vanguard satellite separation mechanisms

    Baumann, R.C. | Engineering Index Backfile | 1961


    Vanguard Satellite Separation Mechanisms

    R. C. Baumann | NTIS | 1961