The results of an analysis of the effects of transverse vibration of a spinning, flexible, free-flight rocket during its guidance phase on its attitude motion subsequent to end of guidance (EOG) are presented. Two models of a spinning, flexible, free-flight rocket are described. One is a simple two-body model. The other is a 'continuous' model. A physical explanation is given for the way transverse vibration during the guidance phase causes the appearance of a transverse angular rate at EOG. The two-body model is used to obtain a simple equation from which estimates of the transverse angular rate can be found. Typical results from the two models are presented and agreement between the results is shown.


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    Titel :

    An Analysis of the Effects of Transverse Vibration on the Attitude Motion of Free-Flight Rockets


    Beteiligte:
    J. E. Cochran (Autor:in) / G. A. Castleberry (Autor:in) / S. D. Rew (Autor:in)

    Erscheinungsdatum :

    1979


    Format / Umfang :

    103 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Free-Flight Rocket Attitude Motion Due to Transverse Vibration

    John E. Cochran D.E. Christensen | AIAA | 1980





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