Rigid strengthening method for large aviation thin-wall component based on optimized layout of flexible tool

The invention discloses a flexible tool optimized layout-based aviation large thin-wall component rigidity strengthening method, which comprises the following steps of: establishing a thin-wall component-flexible tool system dynamic model by adopting a multi-body system transfer matrix method to obtain a total transfer equation and a total transfer matrix of a system; adopting a self-adaptive genetic algorithm, coding the number of supports and the positions of the supports based on the spatial geometric information of the thin-wall component and the flexible tool, substituting the coded number and the coded positions into a total transfer equation and a total transfer matrix, obtaining the inherent frequency of the system, calculating a target function value, and carrying out optimization operation on optimization parameters; and the optimal supporting scheme of the flexible tool for the thin-wall component is obtained through loop iteration. According to the method, rapid optimization of the flexible tool o