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考虑自动驾驶仪延迟的三维光滑自适应滑模制导律
  • ISSN号：1673-5048
  • 期刊名称：《航空兵器》
  • 时间：0
  • 分类：O415.5[理学—理论物理;理学—物理]
  • 作者机构：Center for Control Theory and Guidance Technology,Harbin Institute of Technology, School of Automation,Harbin University of Science and Technology
  • 相关基金：Sponsored by the National Natural Science Foundation of China(Grant No.61174037);the Science Fund for Creative Research Groups of the National Natural Science Foundation of China(Grant No.61021002);the National Basic Research Program of China(Grant No.2012CB821205)
作者： 宋俊红[1], 宋申民[1], 张金鹏[2]
关键词： output, feedback, SLIDING, mode, HYPERCHAOTIC, FRACTION, output feedback sliding mode, hyperchaotic, fraction
中文摘要：

An output feedback sliding mode controller is designed for the stabilization of fractional order hyperchaotic systems including uncertainties in the state matrix and the output matrix. On the basis of auxiliary system,a sliding mode control law with output feedback characteristics is researched by studying the structure decomposition of fractional order hyperchaotic systems. Based on fractional order Lyapunov stability theorem,a switching surface is designed by using linear matrix inequality( LMI) method. Using a simple adaptation,an improved sliding mode controller is given to guarantee the existence of the sliding mode. Moreover,numerical simulations are performed to confirm the effectiveness and feasibility of the stabilization control scheme.

英文摘要：

An output feedback sliding mode controller is designed for the stabilization of fractional order hyperchaotic systems including uncertainties in the state matrix and the output matrix. On the basis of auxiliary system,a sliding mode control law with output feedback characteristics is researched by studying the structure decomposition of fractional order hyperchaotic systems. Based on fractional order Lyapunov stability theorem,a switching surface is designed by using linear matrix inequality( LMI) method. Using a simple adaptation,an improved sliding mode controller is given to guarantee the existence of the sliding mode. Moreover,numerical simulations are performed to confirm the effectiveness and feasibility of the stabilization control scheme.

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期刊信息
  • 《航空兵器》
  • 主管单位:中国航空工业集团公司
  • 主办单位:中国空空导弹研究院
  • 主编：樊会涛
  • 地址：河南省洛阳市030信箱3分箱
  • 邮编：471009
  • 邮箱：hkbq2016@163.com
  • 电话：0379-63385246
  • 国际标准刊号：ISSN：1673-5048
  • 国内统一刊号：ISSN：41-1228/TJ
  • 邮发代号:
  • 获奖情况:
  • 1994年获科技情报成果二等奖,1996年获总公司优秀科技期刊三等奖,2002年获——集团“九五”优秀科技情报出版物二等奖
  • 国内外数据库收录:
  • 被引量:2911