视线角约束自适应滑模中制导律

基于导弹和目标相对运动方程,设计了视线角约束自适应滑模中制导律。应用Lyapunov稳定性理论证明了该制导律能使制导系统在有限时间内收敛至滑动模态面;当制导系统进入滑动模态面后,基于积分理论证明了中末制导交班时刻视线角能够收敛至期望值且视线角速率可以收敛至零附近。进一步将该制导律扩展到三维空间的拦截问题。最后,针对拦截正弦机动目标进行了仿真。结果表明:设计的制导律鲁棒性强,引起的交班误差小。

Adaptive sliding mode midcourse guidance law with constraint on LOS angle

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.