Integrated guidance/autopilot design for missiles with impact angle constraints

被引：5
|
作者：
Xu, Qingjiu [1 ]
Yu, Jiandong [2 ]
Yu, Jinyong [1 ]
Yang, Xiuzhen [1 ]
机构：
[1] Naval Aeronaut Engn Inst, Dept Automat Control, Yantai 264001, Peoples R China
[2] Naval Aeronaut Engn Inst, Dept Management, Yantai 264001, Peoples R China
来源：
2006 IEEE INTERNATIONAL CONFERENCE ON INFORMATION ACQUISITION, VOLS 1 AND 2, CONFERENCE PROCEEDINGS | 2006年
关键词：
D O I：
10.1109/ICIA.2006.305835
中图分类号：
TP18 [人工智能理论];
学科分类号：
081104 ; 0812 ; 0835 ; 1405 ;
摘要：
A scheme of integrated guidance/autopilot design for missiles with impact angle constraints is studied in this paper. When the integrated guidance/antopilot model yaw plane is formulated, the guidance/control law with impact angel constraints is designed based on the backstepping idea and VSC theory. For the unavailable information of the maneuvering target, an estimating method is given. Finally, to verify the effectiveness and rightness of the integrated design scheme, the simulation of some missile has been made, the simulation results have shown that high accuracy of hitting target with impact angle constraints can be got.
引用
收藏
页码：75 / 79
页数：5
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