民机复合材料结构修理容限确定方法研究

In order to solve the problem of repair tolerance in the actual repair process of civil aircraft composite structure, by which it is judged whether to repair or not. Based on the existing results and shortcomings, this paper proposes two complete solutions and procedures for the repair tolerance of composite structure, focusing on how to determine the upper limit of repair under the consideration of both economy and safety. Then taking the composite stiffened wall panel under compression as an example, considering the damage of perforation, combined with finite element analysis, these two methods are used to try to calculate the repair tolerance of the stiffened panel respectively. The results show that the repair tolerance results of the same composite stiffened wall panel obtained by the two schemes are relatively close and reasonable, which proves the feasibility of these two methods, and provides a reference for the engineering damage assessment of civil aircraft composite structure.