Design of differential geometric guidance law against maneuvering targets

被引：0
|
作者：
Huang J. [1 ]
Zhang H. [1 ]
Tang G. [1 ]
Bao W. [1 ,2 ]
机构：
[1] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha
[2] China Aerospace Science and Technology Corporation Limited, Beijing
来源：
Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics | 2018年 / 40卷 / 10期
关键词：
Asymptotically convergent sliding-mode surface; Differential geometric guidance law; Double-power adaptive law; Maneuvering target; Missile guidance;
D O I：
10.3969/j.issn.1001-506X.2018.10.20
中图分类号：
学科分类号：
摘要：
In terms of intercepting endoatmospheric maneuvering targets, a differential geometric guidance law is designed based on a generalized differential geometric guidance scheme. Different from forcing the line of sight rate to converge to zero in finite time, a sliding surface is adopted where the line of sight rate asymptotically converges to zero as the relative distance between the missile and the target decreases. Considering the peaking phenomenon of observer estimating target acceleration in the initial stage and the stability difficult to prove for observer-embedded guidance laws, target acceleration is regarded as a disturbance with unknown bound and a double-power adaptive law is proposed to estimate the bound. A modification term is used to eliminate the influence on stability of saturation function replacing sign function and the asymptotic stability of the proposed guidance law is guaranteed by stability analysis. Simulation results indicate that the designed differential geometric guidance law is able to effectively intercept maneuvering targets. In addition, the overload distribution is reasonable and the less energy consumption is required. © 2018, Editorial Office of Systems Engineering and Electronics. All right reserved.
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页码：2288 / 2295
页数：7
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