Experimental and Numerical Investigation on the Failure Behaviour of Multi-Stiffener Composite Panel Under Compression

Abstract Multi-stiffener composite panels are the primary components widely used in aircraft structures such as fuselage, wing box, and rear bulkhead, but they typically sensitive to compressive load-induced buckling thin-walled nature of these components. This paper presents a numerical experimental study on failure behaviour multi-stiffener panels. A progressive damage model based Hashin’s criteria was employed laminates, while cohesive zone (CZM) replicate delamination between stiffeners flat skin. The predicted initial threshold ultimate load agree well with data, which validated simulation tool developed this study. mode MSCP then dominated by breakage at their middle cross-section, simultaneously accompanied skin/stiffener interfaces. Results indicated that out-of-plane can cause high level peeling shearing effects interfaces, leading debonding compression increase. subsequently introduced an additional bending effect stiffener, eventually caused stiffeners.