冲击载荷作用下机身壁板破坏效应及结构优化

Under the constraint of a non-containment explosion-proof structure, the damage effect of shock wave and plug on the fuselage panel was studied. Taking the fuselage panel locating at the impact position of the directional non-containment explosion-proof structure as the research object, through finite element numerical simulation, the failure mode and degree by the shock wave and plug acting on the body panel at different positions under the constraint of the non-containment explosion-proof structure were analyzed. Then, in order to limit the damage range of the fuselage panel, the structure of the fuselage panel at the impact position was optimized. The results show that the main failure modes of the fuselage panel under shock wave impact are skin shear plug, rib tearing along and perpendicular to the tendons, and rib fracture, while under plug impact, the skin is torn along and perpendicular to the tendons and the ribs are broken. The influence of impact position on the damage degree of the fuselage panel under plug impact is more obvious than that of shock wave impact. The position of the plug impact bar has less influence on the damage of the fuselage panel as a whole, so it is a better impact design scheme. Vertical reinforcement has obvious restraint effect on the crack expansion of the fuselage panel under the two impact modes, but the restraint effect is better while under the action of the plug impact bar. When the plug hits at the position between two tendons or at a single rib, the damage area of the vertical reinforcement panel is reduced by 56% and 39% respectively. The research results provide a guidance for the structural design of non-containment explosion-proof vessels for civil aircrafts and the structural design of fuselage panels at the impact position.