Design of finite-time cooperative guidance law for hypersonic vehicles in dive phase

被引：0

作者：

Tang B. ^{[1
]}

Xi J. ^{[1
]}

Liu T. ^{[2
]}

Li B. ^{[3
]}

机构：

[1] College of Missile Engineering, Rocket Force University of Engineering, Xi'an

[2] Air Force Early Warning Academy, Wuhan

[3] The First Military Representative Office of Rocket Force Equipment Department in Xi'an, Xi'an

来源：

Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2021年 / 47卷 / 10期

关键词：

Adaptive disturbance observer; Cooperative guidance law; Finite-time theory; Hypersonic vehicle; Sliding mode control;

D O I：

10.13700/j.bh.1001-5965.2020.0363

中图分类号：

学科分类号：

摘要：

Focusing on the problem that multiple hypersonic vehicles in the dive phase attack a stationary target or a slowly moving target, a cooperative guidance law with Line-of-Sight (LOS) elevation and LOS azimuth constraint is designed based on finite-time theory. Firstly, the guidance process of the dive phase is divided into two directions: horizontal and longitudinal. Secondly, in the longitudinal LOS direction, the relative position difference and LOS velocity difference are introduced as errors into the guidance law, and the errors come from the hypersonic vehicles participating in the attack and their neighbors. Finally, in order to achieve the convergence of the horizontal and longitudinal LOS angles, the finite-time sliding mode guidance law is designed, and the upper bound of the time-varying disturbance is estimated by the designed adaptive disturbance observer. The finite-time convergence of the proposed cooperative guidance law is proved by Lyapunov function. The simulation results show that the proposed cooperative guidance law is correct and effective. © 2021, Editorial Board of JBUAA. All right reserved.

引用

页码：2105 / 2117

页数：12

共 32 条

[1] CHUANG C H, MORIMOTO H., Periodic optimal cruise for a hypersonic vehicle with constraints, Journal of Spacecraft and Rockets, 34, 2, pp. 165-171, (1997)
[2] PHILLIPS T H., A common aero vehicle(CAV) model, description and employment guide, pp. 7-8, (2003)
[3] WANG Q, RAN M P, ZHAO Y., Reentry guidance for hypersonic vehicle based on predictor-corrector method, Journal of Beijing University of Aeronautics and Astronautics, 39, 12, pp. 1563-1567, (2013)
[4] HE C Y., Optimal reentry guidance for hypersonic vehicles, pp. 48-57, (2011)
[5] ZHANG X F, ZHANG H P, YANG Y, Et al., Improved secant method-based predictive reentry guidance for hypersonic vehicle, Tactical Missile Technology, 1, pp. 56-63, (2016)
[6] ZHU J W, LIU L H, TANG G J, Et al., Optimal guidance with multi-targets for hypersonic vehicle in dive phase, 2013 6th International Conference on Recent Advances in Space Technologies (RAST), pp. 341-346, (2013)
[7] HOU D L, WANG Q, SUN X J, Et al., Finite-time cooperative guidance laws for multiple missiles with acceleration saturation constraints, IET Control Theory & Applications, 9, 10, pp. 1525-1535, (2015)
[8] DIAO Z S, SHAN J Y., Continuous finite-time stabilization guidance law for terminal impact angle constrained flight trajectory, Journal of Astronautics, 35, 10, pp. 1141-1149, (2014)
[9] SONG J H, SONG S M, XU S L., A cooperative guidance law for multiple missiles to intercept maneuvering target, Journal of Astronautics, 37, 12, pp. 1306-1314, (2016)
[10] SONG J H, SONG S M, XU S L., Cooperative guidance law for multiple missiles with impact angle constraints, Journal of Chinese Inertial Technology, 24, 4, pp. 554-560, (2016)

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