The development of a large aircraft lift device not only requires to provide sufficient aerodynamic performance, but also requires comprehensive consideration of noise and comfort. The lift device is an important system to improve the overall performance of large aircraft, and also a key problem to be studied and solved in current technology development. For the mechanism design of the lift device, the method adopted in this paper is to guide the flaps to a better position by designing a relatively simple hinge flap mechanism, and then select the position with better aerodynamic performance as the new optimized position to obtain the better mechanism position. The mechanism position change combined with aerodynamic performance verification requires a lot of iterative calculations and result optimization. Based on the mechanism design, this article explores a new method of multi-objective optimization calculation, and finally achieves the goal of integrated design of aerodynamic structure. In this paper, the hinged trailing edge flap is selected as the research object, and the combined movement of trailing edge flap rotation and spoiler downward deflection on the aerodynamic performance is comprehensively considered. Using the research method, the integrated design of aerodynamic mechanism is carried out and the design results are obtained.