Mathematical method of establishing airplane free vibration characteristics is presented which is restricted to airplane self-equilibrating motions in degrees of freedom using cantilevered component modes and discrete-particle structural component distribution; equations of motion are developed using energy principles; process determines vibration analysis effectivity, that is, inertia and stiffness expressions are specified in certain system generalized coordinates and resulting eigensystem solutions are obtained using digital computer; example illustrates application of method.


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    Title :

    Airplane vibrations using cantilevered component modes


    Additional title:

    SAE -- Paper


    Contributors:

    Conference:

    SAE Meeting ; 1968 Vibrations



    Publication date :

    1968


    Size :

    10 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :


    Airplane Vibrations Using Cantilevered Component Modes

    Schultz, William H. | SAE Technical Papers | 1968





    Experimental study of natural vibrations of cantilevered triangular plates

    Gustafson, P.N. / Stokey, W.F. / Zorowski, C.F. | Engineering Index Backfile | 1953