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.
Airplane vibrations using cantilevered component modes
SAE -- Paper
SAE Meeting ; 1968 Vibrations
1968
10 pages
Conference paper
English
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Airplane Vibrations Using Cantilevered Component Modes
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