Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

被引:11
|
作者
Ai, X. L. [1 ]
Shen, Y. C. [2 ]
Wang, L. L. [3 ]
机构
[1] Beijing Inst Technol, Sch Aerosp Engn, Beijing 100081, Peoples R China
[2] Beijing Inst Elect Syst Engn, Beijing 100854, Peoples R China
[3] Beijing Inst Space Long March Vehicle, Beijing 100076, Peoples R China
来源
AERONAUTICAL JOURNAL | 2019年 / 123卷 / 1267期
关键词
Integrated guidance and control; Impact angle constraint; Actuator saturation; Aerodynamic uncertainties; Manoeuvring targets; SLIDING-MODE GUIDANCE; MISSILE GUIDANCE; DESIGN; LAW;
D O I
10.1017/aer.2019.71
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
This paper considers the integrated guidance and control (IGC) problem for impact angle constrained interception against manoeuvring targets with actuator saturation constraint. Based on the backstepping technique, an adaptive IGC law is presented to address this problem, where a fixed-time differentiator is proposed to estimate the derivatives of virtual control inputs to avoid the inherent problem of "explosion of complexity" suffered by the typical backstepping. Furthermore, an auxiliary first-order filter is introduced into the IGC law to cope with the actuator saturation constraint. The stability of the closed-loop system is strictly proved. Finally, the superiority of the proposed IGC law is verified by comparison simulations.
引用
收藏
页码:1437 / 1453
页数:17
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