Abstract:

For the problem of intercepting a high-speed large maneuvering target with an accelerating missile， it is assumed that the missile has constant axial acceleration and adjusts its acceleration direction by controlling the attack angle. Assuming that the target exhibits a constant lateral maneuver， this paper proposes an accurate time-to-go estimation method. The sliding mode surface is designed so that the missile first corrects the initial heading error and then flies in a straight line to the target. A non-homogeneous disturbance observer is introduced to quickly estimate the acceleration of the target. A super-twisting algorithm is applied to implement the guidance law. The finite-time stability of the proposed guidance law is proved. Through the simulation comparison with the guidance to collision law， it is verified that the proposed guidance law improves the capture area of the missile. It can intercept the target whose maneuvering ability is close to that of the missile when the initial heading error is small.

Key words: accelerating missile, non-homogeneous disturbance observer, super-twisting sliding mode, high-speed large maneuvering target, capture area

摘要：

针对加速导弹拦截高速大机动目标问题，假设导弹具有恒定的轴向加速度，通过控制攻角调整导弹加速度方向。假定目标恒定侧向机动，提出了一种精确的剩余飞行时间估计方法。设计滑模面使导弹先修正初始航向偏差，然后直线飞向预测命中点。引入了非齐次干扰观测器来快速估计目标的加速度，应用超螺旋算法实施了制导律。证明了所提制导律的有限时间稳定性，并通过和GC（guidance to collision）制导律的仿真对比，验证了所提制导律提高了导弹的捕获域，能够在初始航向误差较小时，拦截机动能力接近导弹的大机动目标。

关键词: 加速导弹, 非齐次干扰观测器, 超螺旋滑模, 高速大机动目标, 捕获域