Wang Zhikai, Fu Wenxing, Fang Yangwang, Zhu Supeng, Wu Zihao, Wang Mingang
School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China.
Unmanned System Research Institute, Northwestern Polytechnical University, Xi'an 710072, China.
ISA Trans. 2022 Oct;129(Pt B):257-270. doi: 10.1016/j.isatra.2022.02.043. Epub 2022 Mar 4.
This paper proposes a prescribed-time cooperative guidance law (PTCGL) against maneuvering target with variable line-of-sight (LOS) angle constraint for leader-following missiles, where the convergence times of the state errors can be arbitrarily set. The leader missile against the maneuvering target is provided as the modified proportional navigation (MPN) guidance law. The proposed PTCGL for follower missiles consist of two parts, in LOS direction, the range-to-go (Rgo) is selected as a co-variable, avoiding the estimation of time-to-go (Tgo), and a novel second-order nonlinear consensus protocol is developed to design the PTCGL; in normal LOS direction, considering the variable LOS angle constraint, the cooperative guidance law is designed with the proposed prescribed-time sliding model control (PTSMC) method. Besides, the prescribed-time convergence of Rgo and LOS errors are proved. Finally, the effectiveness and superiority of the proposed PTCGL with leader-following strategy is illustrated by numerical simulation results.
本文针对具有可变视线（LOS）角度约束的机动目标，提出了一种用于前导-跟随导弹的预设时间协同制导律（PTCGL），其中状态误差的收敛时间可以任意设定。针对机动目标的前导导弹采用改进比例导引（MPN）制导律。所提出的用于跟随导弹的PTCGL由两部分组成，在视线方向上，选择剩余距离（Rgo）作为协变量，避免了飞行时间（Tgo）的估计，并开发了一种新颖的二阶非线性一致性协议来设计PTCGL；在垂直于视线方向上，考虑可变视线角度约束，采用所提出的预设时间滑模控制（PTSMC）方法设计协同制导律。此外，证明了Rgo和视线误差的预设时间收敛性。最后，通过数值仿真结果说明了所提出的具有前导-跟随策略的PTCGL的有效性和优越性。
