Numerical and experimental simulations of the postbuckling response of laminated anisotropic panelsNumerical simulations are used in conjuction with experiments to study the buckling and postbuckling responses and failure initiation of flat unstiffened composite panels. The numerical simulations are conducted using two-dimensional shear-flexible finite elements. The effect of the laminate stacking sequence on the buckling and postbuckling responses is studied. Correlation between numerical and experimental results is good through buckling, but the numerical models overestimate the postbuckling stiffness of the panels. To explain the discrepancies in the postbuckling stiffnesses, analytic sensitivity derivatives are calculated and are used to study the sensitivity of the buckling and postbuckling responses to variations in different material and lamination parameters of the panel. Experimental results indicate that failure occurs along a nodal line. Numerical results show that the location of failure initiation corresponds to that of the maximum transverse shear strain energy density in the panel, which occurs at the edge of the panel at a nodal line.
Document ID
19900042255
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Noor, Ahmed K. (NASA Langley Research Center; George Washington University Hampton, VA, United States)
Starnes, James H., Jr. (NASA Langley Research Center Hampton, VA, United States)
Waters, W. Allen, Jr. (Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 90-0964
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference