A reevaluation of the Vanguard program objectives in January 1957 resulted in the production of the Vanguard I Satellite, a 6.44-inch-diameter, 3.25-pound sphere with six equally spaced solar cell clusters and six equally spaced antennas mounted on its surface. Experiment requirements necessitated the development of a mechanism to separate the satellite from the third-stage rocket. On the basis of the existing standard separation mechanism, a strap pull-pin girth-ring arrangement was developed. Both the satellite and the separation mechanism were fully tested prior to flight. Successful orbiting and flight operation proved the adequacy of the design.


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    Titel :

    Vanguard I Satellite Structure and Separation Mechanism


    Beteiligte:
    J. T. Shea (Autor:in) / R. C. Baumann (Autor:in)

    Erscheinungsdatum :

    1961


    Format / Umfang :

    20 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    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 Satellite Separation Mechanisms

    R. C. Baumann | NTIS | 1961


    Vanguard Satellite Separation Mechanisms

    Baumann, Robert C. | NTRS | 1961


    Vanguard satellite separation mechanisms

    Baumann, Robert C. | TIBKAT | 1961