Non-smooth guidance law with terminal angular constraints for missiles against surface targets

被引：0

作者：

Zhang Gongping ^{[1
]}

Ma Kemao ^{[2
]}

Yan Liang ^{[1
]}

机构：

[1] Luoyang Optoelctro Technol Dev Ctr, Luoyang 471099, Peoples R China

[2] Harbin Inst Technol, Control & Simulat Ctr, Harbin 150001, Peoples R China

来源：

PROCEEDINGS OF THE 38TH CHINESE CONTROL CONFERENCE (CCC) | 2019年

基金：

中国国家自然科学基金;

关键词：

Homing missiles; Terminal angular constraints; Maneuvering targets; Input-to-state stability; IMPACT; INPUT;

D O I：

10.23919/chicc.2019.8866019

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

Guidance law with terminal angular constraints is considered for an air-to-surface missile against a surface target. To guarantee the finite-time convergence property, a non-smooth continuous guidance law is designed in the engagement of the missile against a non-maneuvering target. By taking the target's maneuver as an external disturbance input, the designed guidance law is also applicable to a maneuvering target, which is justified through the performance analysis using the input-to-state stability theory. Simulation is conducted, and the simulation results verify the theory proposed in the paper.

引用

页码：3898 / 3903

页数：6

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