SDRE Optimal Sliding Mode Guidance Law Design with Attack Angle Constraint

被引：0
|
作者：
Li, Yuan-Sheng [1 ]
Zhao, Xin [1 ]
She, Si-Hong [1 ]
Ma, Meng-Chen [2 ]
Song, Shen-min [2 ]
机构：
[1] Syst Engn Res Inst, Beijing 100094, Peoples R China
[2] Harbin Inst Technol, Harbin 150001, Peoples R China
来源：
PROCEEDINGS OF THE 38TH CHINESE CONTROL CONFERENCE (CCC) | 2019年
关键词：
guidance law; terminal sliding mode; SDRE; optimal guidance; autopilot; IMPACT TIME;
D O I：
10.23919/chicc.2019.8865531
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
This paper presents an analysis for two-dimensional terminal guidance problem considering target maneuvering and missile autopilot characteristics. A State Dependent Riccati Equation(SDRE) optimal guidance law with attack angle constraint for target nonmeneuvering is designed based on SDRE method. Based on the non singular terminal sliding mode surface, a SDRE optimal adaptive non singular terminal sliding mode guidance law is proposed using SDRE method for target maneuvering. The stability of the closed-loop system with respect to the proposed control scheme is proved via Lyapunov theory, and the results of numerical simulations are presented to demonstrate the effectiveness of the proposed approach.
引用
收藏
页码：3815 / 3820
页数：6
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