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Compression-Loaded Composite Panels With Elastic Edge Restraints and Initial PrestressA parametric study of the effects of test-fixture-induced initial prestress and elastic edge restraints on the prebuckling and buckling responses of a compression-loaded, quasi-isotropic curved panel is presented. The numerical results were obtained by using a geometrically nonlinear finite element analysis code with high-fidelity models. The results presented show that a wide range of prebuckling and buckling behavior can be obtained by varying parameters that represent circumferential loaded-edge restraint and rotational unloaded-edge restraint provided by a test fixture and that represent the mismatch in specimen and test-fixture radii of curvature. For a certain range of parameters, the panels exhibit substantial nonlinear prebuckling deformations that yield buckling loads nearly twice the corresponding buckling load predicted by a traditional linear bifurcation buckling analysis for shallow curved panels. In contrast, the results show another range of parameters exist for which the nonlinear prebuckling deformations either do not exist or are relatively benign, and the panels exhibit buckling loads that are nearly equal to the corresponding linear bifurcation buckling load. Overall, the results should be of particular interest to scientists, engineers, and designers involved in simulating flight-hardware boundary conditions in structural verification and certification tests, involved in validating structural analysis tools, and interested in tailoring buckling performance.
Document ID
20050215457
Acquisition Source
Langley Research Center
Document Type
Technical Publication (TP)
Authors
Hilburger, Mark W. (NASA Langley Research Center Hampton, VA, United States)
Nemeth, Michael P. (NASA Langley Research Center Hampton, VA, United States)
Riddick, Jaret C. (Army Research Lab. Hampton, VA, United States)
Thornburgh, Robert P. (Army Research Lab. Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 2005
Subject Category
Composite Materials
Report/Patent Number
L-19162
ARL-TR-3572
NASA/TP-2005-213906
Funding Number(s)
OTHER: 23-376-10-30-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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