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| Terminal Angle Constraint Sliding Mode Guidance Law Design Based on Fixed-time Convergence |
| ZHANG Xiaoyu1,2，ZHANG Peng2，ZHENG Xin3，NI Yuanhua1 |
1. College of Artificial Intelligence, Nankai University, Tianjin 300350, China；
2. College of Intelligent Systems Science and Engineering, Harbin Engineering University, Harbin 150001, Heilongjiang, China；
3. Shanghai Academy of Spaceflight Technology, Shanghai 201109, China |
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Abstract In order to improve the target destruction by the missile and achieve successful interception of the target in a bounded finite time, a terminal angle constraint sliding mode guidance law based on fixed-time convergence is proposed. Firstly, a plane guidance system model of missile intercepting target is established, and the target maneuver is regarded as unknown bounded disturbance. Secondly, a fixed time disturbance observer is used to observe the disturbance of the guidance system. Thirdly, the terminal angle constraint guidance law is designed based on fixedtime convergence sliding mode control and fixed-time disturbance observers. The fixed-time stability of the guidance system is proved, and the convergence domains of guidance system states are given. Finally, it is verified that the designed guidance law can achieve intercepting the target at a specified angle while ensuring accurate interception via numerical simulations.
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Received: 16 July 2020
Published: 29 September 2020
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2020, Vol. 3 
