Experimental and simulation study on explosion impact of a typical wall panel structure

Abstract

The damage effect of the explosion shock wave generated by the explosion of the air to air missile warhead on the aircraft skin structure is influenced by various factors，and the function mechanism is relatively com plex，so that a large number of experimental and computational samples are required to evaluate the damage of shock waves to aircraft skin structures accurately. The static explosion experiments of aluminum alloy reinforced plates with fixed supports are performed，and their dynamic response and deformation patterns under shock wave loading are analyzed. The finite element analysis software LS-DYNA is used to simulate the structural response under explosive impact，and the simulation model is validated by comparing with the experimental results. The results show that the target plate is prone to tensile failure with tearing at the fixed boundary when the hole area ratio of the reinforced plate exceeds 1‰，and increasing the hole diameter or the number of holes enhances the risk of perforation damage between holes. The target deformation increases with the incident angle of explosion，and the target deflection can increase by more than 30% when the angle increases from 30° to 60° at a constant explosion distance.

Keywords

• explosion shock wave
• wall panel structure
• dynamic response
• numerical simulation
• experimental study