Abstract:

Based on the missile target relative motion equation, an adaptive sliding mode midcourse guidance law with line-of-sight (LOS) angle constraint is proposed. It is proved that the guidance law can drive the guidance system to converge to slidingmode surface within finite time using Lyapunov stability theory. And after the guidance system enters the slidingmode surface, it is proved the LOS angle can converge to its desired values and the LOS angular rate is near zero at the handover time based on integral theory. Further, the guidance law is extended for engagement in threedimensional space. Finally, the simulation is performed against a sinusoidal maneuvering target, and the results show that the guidance law is of strong robustness, and small handover errors.