Abstract:

To solve the planar intercept problem, a guidance law is designed using the variable structure sliding mode control method, considering the missile autopilot dynamic delay of the first order. The sliding mode can converge to zero in finite time with application of the guidance law, which makes the line of the sight rate decrease to zero within the guidance phase, therefore, a high guidance accuracy is obtained. The finite time convergence and robustness can be guaranteed as long as the variable structure is greater than the rate of the target acceleration, which reduces the wobbling of the guidance system evidently. Finally, it can be demonstrated through the simulation results, that good performance and high accuracy can be reached by the proposed guidance law, when there are great dynamic delay of the autopilot or some escape maneuver of the target.