To optimize the deploying performance of folding wing mechanism for an aircraft, this paper analyzes the folding wing mechanism and proposes a method to optimize the deploying performance of the mechanism. A theoretical model and a dynamic simulation model for the deployment of folding wing mechanism were established, the deploying processing of folding wing mechanism was analyzed and the folding time of the mechanism was given by using the theoretical model. Then, the effect factor on the deploying performance of the mechanism was analyzed, and the orthogonal trial method was used to optimize those structure parameters to obtain a optimized designed scheme. Finally, the mechanism was simulated and optimized by the optimal scheme and the deploying performance of the mechanism was measured by experiments. Experimental results show that the folding time of the mechanism is 0.128 s and the structure stresses at the measuring points are 92 MPa and 80 MPa respectively. Moreover the dynamic model test results of the mechanism show that the folding time of the mechanism is 0.12 s and the structure stresses at the measuring points are 85 MPa and 96 MPa, respectively. The difference of the experimental and simulation results is within 5%. It indicates that the optimal folding wing mechanism promotes the flight performance of the aircraft while the mechanism also basically satisfies the design requirements like the stability, reliability, fast speed, small stress and the impact force.