Experimental and numerical analysis of composite fuselage panel impacted by tire burst debris under airworthiness clause

This study focuses on an experimental and numerical simulation investigation on the dynamic response of the composite fuselage panel under the impact of the tire burst debris. According to the parameters specified in the airworthiness clause, the T800/M21C composite material is selected as the research object to carry out the tire debris impact test, and the consistent results are obtained by employing the applicable mesoscopic model of the tire debris, progressive failure model of composite, the interface model and considering the strain rate dependence of the composite material in numerical simulation. The results show that under the airworthiness condition, the peak strain rate of the fuselage panel is about 16 s-1 during the impact of tire debris. The damage modes of the fuselage panel are debonding of the stringers from the skin and local matrix tensile damage. The Puck failure criterion, which considers the angle of the fracture surface of the matrix, is proved to be more suitable for the prediction of matrix damage than the Hashin failure criterion. The developed progressive damage failure impact model can be used in structural analysis and optimization design of aircraft fuselage, providing reference data for airworthiness verification.