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The incorrect selection of force nodes during the attitude adjustment process can lead to a significant decrease in the load-bearing capacity of the wing panel. Therefore, accurately locating the force nodes can reduce the deviation of the panel attitude adjustment. Therefore, research is being conducted on the wing panel positioning and flexible attitude adjustment technology under force position collaborative control. According to the principle of force position collaborative control, establish a force position structural model of the wing wall panel; And based on the description conditions of mechanical synergy, calculate the impedance effect of wing force position; By homogeneous transformation of positioning coordinates, a specific wing panel positioning model is derived to achieve wing panel positioning based on force position collaborative control. Analyze the flexible equivalent force of the wing panel, refer to the calculation results of the attitude adjustment displacement, determine the absolute vector of displacement, define the position of the free point of the attitude adjustment, complete the construction of the target model of the flexible attitude adjustment, and realize the design of the wing panel positioning and flexible attitude adjustment method under the coordinated control of force and position. The experimental results show that the application of the above algorithm can control the positioning coordinate error between the attitude adjustment force node and the standard force point within 3mm, and can solve the problem of reduced bearing capacity of the wing wall panel caused by incorrect selection of attitude adjustment force nodes, which is in line with practical application requirements.