Dynamic Buckling of an Axially Compressed Cylindrical Shell With Discrete Rings and Stringers

[+] Author and Article Information
C. A. Fisher, C. W. Bert

School of Aerospace, Mechanical and Nuclear Engineering, The University of Oklahoma, Norman, Okla.

J. Appl. Mech 40(3), 736-740 (Sep 01, 1973) (5 pages) doi:10.1115/1.3423082 History: Received May 01, 1972; Revised February 01, 1973; Online July 12, 2010


As an exploratory effort toward improving the crashworthiness of light aircraft cabins, a theoretical analysis was made to predict the dynamic buckling load and buckling time of a stiffened, thin-walled circular cylindrical shell. To provide for the large stiffener spacing in light aircraft, the stiffeners were considered as discrete elements by means of a Dirac delta procedure. The nonlinear governing equations were derived using Hamilton’s principle and the final equations were obtained by means of Galerkin’s method. Solution was carried out by using a Gauss-Jordan technique on the algebraic equations and a Runge-Kutta technique on the nonlinear differential equations. Numerical results are presented for an idealized model of a typical light aircraft cabin.

Copyright © 1973 by ASME
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