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The traditional missile guidance system is improved and designed to improve the missile's path tracking effect. Firstly, the Dubins curve is introduced to plan the missile's trajectory, and the missile guidance strategy is designed based on sliding mode control. The autopilot system adopts the cascade proportional integral controller. The Dubins curve can create a smoother reference trajectory for the missile, reducing the overshoot and oscillation of the missile. Sliding mode control obtains the reference azimuth by calculating the relative distance between the missile and the reference trajectory, and then realizes the tracking of the reference trajectory, which can improve the response speed and anti-interference ability of the guidance system. The effect of missile tracking path is simulated, and the error and oscillation of the missile's tracking trajectory before and after the introduction of the dubins curve is compared. The dubins curve is used as the simulation path, and the simulation results of the traditional proportional guidance strategy and the improved sliding mode control guidance strategy are compared, which proves the feasibility of the improved guidance system design, and discusses the characteristics of its path tracking performance.