基于零控脱靶量的大气层内拦截弹制导律

A Zero-Effort Miss Distance-Based Guidance Law for Endoatmoshperic Interceptor

本文基于零控脱靶量的概念,提出了一种用于拦截螺旋机动弹道导弹的末制导律。首先,在线性运动模型下推导了零控脱靶量的计算公式。选择零控脱靶量作为滑动模态进行制导律设计,并在此基础上对滑模的到达条件进行了讨论。最后,通过与最优制导律和基于目标视线角速率的滑模制导律的仿真比较,验证了本文提出的制导律的性能。仿真结果同时表明,该制导律不但对螺旋目标的加速度波动不敏感,而且具有较好的鲁棒性。

A terminal zero-effort miss （ZEM）-based guidance law is presented for endoatmospheric interceptors against spiraling ballistic missiles. The ZEM,which is derived by the linearized kinematics and dynamics,is chosen as sliding mode and then the sliding mode control theory is employed to design the guidance law. Also,the conditions to reach the sliding surface are investigated. Finally,the effectiveness of the presented guidance law is tested in a real interception scenario. It is shown that the guidance law is not sensitive to the target＇s spiraling maneuver compared with the optimal guidance law and line-of-sight-based sliding mode guidance law,especially when there is measurement noise in the system.