Method of analysis for determining transient forced flexural vibrations of accelerating missiles and space vehicles is presented; equations of motion are in matric form and may be adapted to computers; matric formulation for problem is written to include effects of engine gimballing resulting from structural coupling of flight control system, inertial axial loads along missile, variable shear stiffness, structural damping, structurally coupled aerodynamic forces and arbitrary transient forces applied along missile; only basic data for system are required in matrices.


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    Title :

    Transient vibrations of missiles and space vehicles


    Additional title:

    Aircraft Eng


    Contributors:
    Benfield, W.A. (author) / Cox, H.L. (author) / Chan, S.P. (author)

    Published in:

    Publication date :

    1962


    Size :

    17 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Transient Vibrations of Missiles and Space Vehicles

    Benfield, W.A. / Cox, H.L. / Chan, S.P. | Emerald Group Publishing | 1962