Abstract：In this paper, a finite time convergent guidance law is designed considering the missile flight control system (FCS) dynamic response characteristic. The mathematical model of relative motion is built and the FCS is considered as a first-order system. And then, the modeling error and target maneuvering acceleration are regarded as disturbance, which can be estimated and compensated by introducing the extended state observer (ESO). The robustness of the guidance system against the maneuver target can be improved by using back-stepping method and integrating the FCS. The proposed law can guarantee the line of sight (LOS) rate converges to a small bounded neighborhood of zero in finite time. Numerical simulation was carried out, and the feasibility and superiority of the proposed guidance law were verified.
陈泽宏, 钟继鸿, 赵宏宇, 王鉴. 基于扩张状态观测器的有限时间收敛制导律[J]. 空天防御, 2019, 2(3): 25-30.
CHEN Zehong, ZHONG Jihong, ZHAO Hongyu, WANG Jian. Finite Time Convergent Guidance Law Based on Extended State Observer. Air & Space Defense, 2019, 2(3): 25-30.
