Compressive behaviour of thin-skin stiffened composite panels with a stress raiser

The in-plane compressive behaviour of thin-skin stiffened composite panels with a stress concentrator in the form of an open hole or low velocity impa ct damage is examined analytically. Drop weight impact in laminated polymer composites causes matrix cracking, delaminations and fibre breakage, which together can seriously degrade the laminate compressive strength. Experime ntal studies, using ultrasonic C-scan images and X-ray shadow radiography, indicated that the overall damage resembles a hole. Under uniaxial compress ion loading, Oo fibre microbuckling surrounded by delamination grows latera lly (like a crack) from the impact site as the applied load is increased. T hese local buckled regions continued to propagate, first in discrete increm ents and then rapidly at failure load. The damage pattern is very similar t o that observed in laminated plates with open holes loaded in compression. Because of this resemblance, a fracture mechanics model, developed initiall y to predict notched compressive strength, was applied to estimate the comp ression-after-impact (CAI) strength of a stiffened panel; in the analysis t he impact damage is replaced with an equivalent open hole. Also, the maximu m stress failure criterion is employed to estimate the residual compressive strength of the panel. The unnotched compressive strength of the composite laminate required in the analysis is obtained from a three-dimensional sta bility theory of deformable bodies. The influence of the stiffener on the c ompressive strength of the thin-skin panel is examined and included in the analysis. A good agreement between experimental measurements and predicted values for the critical failure load is obtained. (C) 2001 Elsevier Science Ltd. All rights reserved.