Volume 38, Number 6, December 2020
|Page(s)||1257 - 1265|
|Published online||02 February 2021|
Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint
China Airborne Missile Academy, Luoyang 471009, China
2 Aviation Key Laboratory of Science and Technology on Airborne Guided Weapons, Luoyang 471009, China
3 Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China
4 School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
A distributed multi-missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three-dimensional multi-missiles cooperative interception of large maneuvering target. According to the finite time consistency theory, an adaptive guidance law based on the integral sliding mode is designed to ensure that all missiles can reach the target at the same time in the terminal guidance process. The longitudinal and lateral acceleration of the line of sight are based on the guidance law of the fast terminal sliding mode surface. The terminal attack angle is constrained, so that the terminal attack Angle can reach the expected value in finite time. The simulation results show that the designed guidance law can achieve the cooperative attack on the maneuvering targets.
Key words: three-dimension / coordination guidance / maneuvering target / impact angle constraint
关键字 : 三维空间 / 协同制导 / 机动目标 / 攻击角约束
© 2020 Journal of Northwestern Polytechnical University. All rights reserved.
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