Abstract：Joint surface stiffness parameter identification of complex structure of aircraft using optimization method is proposed in this article. The least square of the modal test mode of vibration and calculation mode is used as the objective function. The modal frequency is used as the constraint. The joint surface stiffness is used as the optimized parameter. This method is simple and feasible, and the joint surface stiffness can be identified more accurately with parameter identification. The modal calculation accuracy can be significantly improved and a more accurate model can be provided for the subsequent dynamic modeling and vibration analysis.
