抄録
The present paper studies behaviors of blade-stiffened CFRP panels under axial compression by using a finite element method. Effect of a debonding between skin panel and stiffener flange on compressive behavior is analyzed and discussed. The debonding is supposed an impact damage. Linear buckling analysis and non-linear post-buckling analysis are conducted. At the debonded area, contact condition is approximately solved by an introduction of a spring element which has a resistant force only in the compressive direction. The some pre-buckling deflection increased proportional to the compression load before buckling owing to the asymmetric lamination at the flange portion, while the predicted linear buckling load agrees well with that obtained from the nonlinear analysis. The results well explain the experimental findings including the little reduction of compressive performance of the stiffened panel due to impact damage. The effect of the partial debonding on the compressive behavior becomes significant when the debonding area reaches the size comparable to that of the wave length of the buckling mode.
