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Flutter and Vibration Analysis by a Modal Method

William P. RoddenEdith F. FarkasHeather A. Malcom

其他書名	Analytical Development and Computational Procedure
出版	Space Systems Division, Air Force Systems Command, United States Air Force, 1963
URL	http://books.google.com.hk/books?id=-vYXr4jY7IkC&hl=&source=gbs_api

註釋A modal solution of the flutter and vibration problems for a multiple component system is presented. The formulation requires the aerodynamic characteristics in the form of aerodynamic influence coefficients, and the structural and inertial characteristics in the form of free vibration modes and frequencies and a mass matrix for each component. The use of a rigid-body modal matrix permits a general analysis for a system free in space with up to six rigid-body degrees of freedom. The solution also utilized a newly developed subroutine for finding the eigenvalues and eigenvectors of a non-Hermitian matrix having close roots, and obtains the corresponding values of frequency, required structural damping, and velocity of the flutter system. The Aerospace IBM 7090 Computer Program No. LD014A provides the flutter or vibration solution for a system composed of as many as 20 flexible components, each of which may have up to 50 control points. The solution is carried out by a modal (series) method choosing a series of up to 40 cantilever and/or free-free vibration modes to approximate and control point deflections. The program may be used to find the vibration characteristics of a composite system if the cantilever vibration characteristics of the components are known. (Author).