Experimental and numerical study of bending-induced buckling of stiffened composite plate assemblies

Despite their importance in benchmarking numerical simulations, buckling tests still feature compromises between component-level and high-fidelity large-scale tests. For example, compression-induced cannot capture the through-thickness or span-wise stress gradients wing skins. Consequently, results obtained often require careful interpretation conservative considerations before applying to a structure. Alternatively, system-level test can be used, yet at considerably increased time expense. There has been little progression towards capturing behaviour simplified test. Herein, for assessment, three-point bending is which quick, simple implement, cost-effective compared existing conventional methods. The proposed method relies on subjecting panel with auxiliary stiffeners introduce skin. bend because it provides readily controllable loading boundary conditions. location of neutral plane tailored via design stiffeners, thus allowing control gradient induced This applicable stiffened structures subject (e.g., aircraft wingboxes). Numerical models are used explore limits comparing against traditional coupon full-scale structural level experimentally demonstrated thermoplastic composite made automated fibre placement. approach shown reliably using simpler more cost-efficient setup than