Nonlinear buckling analysis of the conical and cylindrical shells using the SGL strain based reduced order model and the PHC method

Liang, K. and Ruess, M. (2016) Nonlinear buckling analysis of the conical and cylindrical shells using the SGL strain based reduced order model and the PHC method. Aerospace Science and Technology, 55, pp. 103-110. (doi: 10.1016/j.ast.2016.05.018)

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Abstract

Thin-walled conical and cylindrical shells subjected to axial compression often show a snap-back response in the presence of buckling. Newton iterations based path-following methods cannot trace reliably the snap-back response due to the extremely sharp turning angle near the limit point, and the original Koiter–Newton method also meets difficulties to achieve a complete post-buckling response beyond the limit point. In this paper, the improved Koiter–Newton method is proposed to trace the post-buckling path of cylinders and cones, in the framework of the reduced-order modeling technique. The polynomial homotopy continuation (PHC) method is used to solve the lower-order nonlinear reduced order model reliably and efficiently. The simplified Green–Lagrange (SGL) kinematics which consider the stress redistribution after buckling are implemented into the construction of the reduced order model to produce accurate results for curved shells. The numerical results presented reveal that the improved method is a robust and efficient technology to achieve the entire nonlinear response for the snap-back case.

Item Type:Articles
Additional Information:The research leading to these results received funding from the European Community’s Seventh Framework Programme ([FP7/2007–2013]) under grant agreement No. 282522. This research work was also sponsored by Laboratory Independent Innovation project of Qian Xuesen Laboratory of Space Technology.
Status:Published
Refereed:Yes
Glasgow Author(s) Enlighten ID:Ruess, Dr Martin
Authors: Liang, K., and Ruess, M.
College/School:College of Science and Engineering
Journal Name:Aerospace Science and Technology
Publisher:Elsevier
ISSN:1270-9638
Published Online:24 May 2016
Copyright Holders:Copyright © 2016 Elsevier Masson SAS
First Published:First published in Aerospace Science and Technology 55:103-110
Publisher Policy:Reproduced in accordance with the copyright policy of the publisher

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