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| Buckling and Post-Buckling of Curved Hat-Stiffened Composite Panels Under Combined Internal Pressure and Axial Compression |
| WANG Houbing, LI Xinxiang, WEI Jingchao, LEI Anmin, CHENG Linan |
| (Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure Static and Fatigue, Aircraft Strength Research Institute of China, Xi’an 710065, China) |
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Abstract Experiments on curved hat-stiffened composites panel with 7 stringers and 4 frames were conducted to investigate the buckling load, buckling mode, post-buckling carrying capacity and failure characterization under combined internal pressure and axial compression. The results show that the axial buckling load of the curved hat-stiffened composites panel is increased by the internal pressure when the panel is subjected to combined mechanical loads, and the panel has no buckle before failure. Based on the linear stability theory of shallow composites shell, the analytical methods for the buckling load of the curved hat-stiffened composites panel were presented by utilizing Rayleigh-Ritz method and Kirchhoff hypothesis under internal pressure, axial compression, combined internal pressure and axial compression, an empirical method was proposed to estimate the failure load of the curved hat-stiffened composites panel under combined internal pressure and axial compression. The results by both the present methods and experiments agree very well, the empirical method is clear and concise, which is easy to be applied in design of curved hat-stiffened composites panel.
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2020, 
