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fuzzy control strategy for hypersonic missile autopilot with blended aero-fin and lateral thrust 发自小木虫Android客户端 |
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peng_weishi
新虫 (初入文坛)
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2楼2016-06-01 20:05:59
lzg020716
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peng_weishi: 金币+1 2016-06-02 15:30:29
peng_weishi: 金币+9, 谢谢 2016-06-02 23:57:32
sunshan4379: LS-EPI+1, 感谢应助！ 2016-06-03 19:54:27
peng_weishi: 金币+1 2016-06-02 15:30:29
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sunshan4379: LS-EPI+1, 感谢应助！ 2016-06-03 19:54:27
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Fuzzy control strategy for hypersonic missile autopilot with blended aero-fin and lateral thrust 作者:Yang, PF (Yang, Peng-fei)[ 1 ] ; Fang, YW (Fang, Yang-wang)[ 1 ] ; Chai, D (Chai, Dong)[ 1 ] ; Wu, YL (Wu, You-li)[ 1 ] PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART I-JOURNAL OF SYSTEMS AND CONTROL ENGINEERING 卷: 230 期: 1 页: 72-81 DOI: 10.1177/0959651815611567 出版年: JAN 2016 查看期刊信息 摘要 An aerodynamic force and lateral thrust blended control autopilot is designed for the near-space air-breathing hypersonic missile with low overload cruise phase due to angle of attack restriction. The nonlinear longitudinal short-period motion model of a hypersonic missile is built, and several fuzzy control strategies are applied in overload command allocation, so as to decouple the aerodynamic and direct force subsystems. The adaptive sliding mode control approach is proposed for aerodynamic subsystem to handle the model uncertainties and atmospheric environment disturbances. A two-dimensional fuzzy controller is designed for direct force subsystem to reduce the dependence of the accurate model. The simulations show that the proposed blended controller can overcome the effects of disturbances and improve the delay effect by reason of weak aerodynamic to realize satisfied tracking performance. The simulations are also given to illustrate the validity of the blended control law in long period. The results show that the blended controller can achieve a good tracking performance throughout the cruise phase. The maneuverability of this dual-controlled hypersonic missile, with blended aero-fin and divert-control lateral jets, is enhanced obviously in cruise phase. 关键词 作者关键词:Blended control; lateral thrust; hypersonic missile; fuzzy control; adaptive sliding mode control KeyWords Plus:GUIDANCE; DESIGN 作者信息 通讯作者地址: Chai, D (通讯作者) Air Force Engn Univ, Sch Aeronaut & Astronaut Engn, Xian 710038, Peoples R China. 地址: [ 1 ] Air Force Engn Univ, Sch Aeronaut & Astronaut Engn, Xian 710038, Peoples R China 电子邮件地址:chaidong2012@gmail.com 基金资助致谢 基金资助机构 授权号 National Natural Science Foundation of China 60874040 Natural Science Foundation of Shaanxi Province 2014JQ8339 查看基金资助信息 出版商 SAGE PUBLICATIONS LTD, 1 OLIVERS YARD, 55 CITY ROAD, LONDON EC1Y 1SP, ENGLAND 类别 / 分类 研究方向:Automation & Control Systems Web of Science 类别:Automation & Control Systems 文献信息 文献类型:Article 语种:English 入藏号: WOS:000367582600007 ISSN: 0959-6518 eISSN: 2041-3041 期刊信息 目录： Current Contents Connect® Impact Factor (影响因子): Journal Citation Reports® 其他信息 IDS 号: DA1VC Web of Science 核心合集中的 "引用的参考文献": 12 Web of Science 核心合集中的 "被引频次": 0 |
3楼2016-06-01 22:11:11
peng_weishi
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4楼2016-06-01 22:50:32