Axially Symmetric Creep Buckling of Circular Cylindrical Shells in Axial Compression

[+] Author and Article Information
N. J. Hoff

Department of Aeronautics and Astronautics, Stanford University, Stanford, Calif.; Lockheed Missiles and Space Company

J. Appl. Mech 35(3), 530-538 (Sep 01, 1968) (9 pages) doi:10.1115/1.3601247 History: Received November 09, 1967; Revised February 26, 1968; Online September 14, 2011


The creep-buckling phenomenon of circular cylindrical shells subjected to axial compression is studied in the presence of initial imperfections when the creep strain rate is proportional to a power of the stress with the exponent greater than unity. A closed-form solution is obtained for the critical time; that is, for the finite time at which the analysis predicts the development of indefinitely large displacements.

Copyright © 1968 by ASME
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