J Shanghai Jiaotong Univ Sci ›› 2022, Vol. 27 ›› Issue (6): 823-832.

• Aeronautics and Astronautics •

Impact Angle/Time Constraint Guidance Design Based on Fast Terminal Error Dynamics

QIN Xuesheng (秦雪升), LIU Yuanhe (刘远贺), LI Kebo (黎克波), LIANG Yangang∗ (梁彦刚)

1. (College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China; Human Key Laboratory of Intelligent Planning and Simulation for Aerospace Mission, Changsha 410073, China)
• Received:2022-06-22 Online:2022-11-28 Published:2022-10-13

Abstract: Considering the problem that the optimal error dynamics can only converge at the terminal time, an impact angle/time constraint missile guidance law with finite-time convergence is designed in this paper, which is based on the pure proportional navigation (PPN) guidance law and the fast terminal error dynamics (FTED) approach. The missile guidance model and FTED equation are given first, and the dynamic equation of impact angle/time error based on PPN is also derived. Then, the guidance law is designed based on FTED, and the guidance error can converge to 0 in a finite time. Furthermore, considering the field of view constraint, the guidance law is improved by using the saturation function mapping method. Finally, a numerical simulation example is given to verify the effectiveness of the guidance law, which shows that the guidance law proposed in this paper can make the missile quickly adjust to the desired states in advance, and effectively relieve the overload saturation pressure of the actuator.

Key words: design of guidance law, fast terminal error dynamics, field-of-view angle, impact time, impact angle

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