Issue |
JNWPU
Volume 38, Number 6, December 2020
|
|
---|---|---|
Page(s) | 1257 - 1265 | |
DOI | https://doi.org/10.1051/jnwpu/20203861257 | |
Published online | 02 February 2021 |
Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint
带有攻击角约束的大机动目标协同攻击制导律
1
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
Received:
14
May
2020
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.
摘要
针对三维空间内多枚空空导弹协同攻击高速大机动目标末制导问题,提出了一种分布式有限时间协同制导律设计方法。视线方向加速度根据有限时间一致性理论设计了基于积分滑模面的自适应制导律,保证了在末制导过程所有导弹能够同时达到目标;视线纵向和视线侧向的加速度均采用基于快速终端滑模面的制导律,同时对末端攻击角进行约束,使得末端攻击角能够在有限时间达到期望值。仿真算例验证了所提出的制导律能够实现对机动目标的协同攻击。
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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