In view of the effect of coning motion on missile stability, a nonlinear mathematical model of missile coning motion control was established. By introducing the concept of complex attack angle, the nonlinear model that was difficult to be resolved by analytical means could be transformed to a general resolvable model. According to the linear model of the missile complex attack angle motion equations, the range of stability control of the guidance and control system parameters were deduced, the influence of damping loop and control loop of control system on the stability of missile coning motion was analyzed, and the method to judge the stability of coning motion control was proposed. Simulation results validate the feasibility and correctness of this method, which provides a reference for the design of missile coning motion of guidance and control system.