NASA NTRS · 19880012714
Postbuckling delamination of a stiffened composite panel using finite element methods
Abstract
A combined numerical and experimental study is carried out for the postbuckling behavior of a stiffened composite panel. The panel is rectangular and is subjected to static in-plane compression on two opposite edges to the collapse level. Nonlinear (large deflection) plate theory is employed, together with an experimentally based failure criterion. It is found that the stiffened composite panel can exhibit significant postbuckling strength.
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Natsiavas, S., Babcock, C. D., Knauss, W. G.. 1987-08-01. Postbuckling delamination of a stiffened composite panel using finite element methods. https://ntrs.nasa.gov/citations/19880012714
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