Experimental and Numerical Investigation on Compressive Stability of Stiffened Composite Panel with Multiple Stringers and Frames

Tianliang Qin, Lei Peng, Bo Ma, Yanan Chai, Feng Yao, Jifeng Xu

Abstract


The stability of stiffened composite panels is the primary problem in aircraft design. This work investigates the compressivebuckling and postbuckling behaviors of a stiffened composite panel with seven hat stringers and three frames. Both thecompressive experiment and Finite Element(FE) analysis are carried out for the buckling and postbuckling responses of thestiffened composite panel under compressive load. A new test setup is designed for the compressive experiment, where thetransverse deflections of the frame ends are constrained by six in-plane movable jigs when compressive load is applied. TheDigital Image Correlation (DIC) technique is used to measure the buckling modes and strain distributions of the skin in theexperiment. The detailed buckling developments are recorded by DIC technique at different load levels. In addition, the strainson different sections of the skin and stringers are recorded by strain gauges to monitor the strain changes during thepostbuckling process. Meanwhile, the nonlinear FE analysis using the Riks method is carried out in Abaqus. The skin, stringersand frames are modeled using shell elements. The adhesive bonded joints are simulated by Tie constraints. The bolted joints aresimulated by the combination of beam elements and distributing coupling elements. The maximum strain criterion is used topredict the ultimate failure. The numerical model is validated by comparing the predicted buckling load, buckling modedevelopments and ultimate failure region with the experimental results.


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