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火箭发动机燃烧过程的鲁棒非脆弱H_∞控制
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  • 英文篇名:The robust non-fragile H_∞ control for the combustion process in rocket motor
  • 作者:吴玉彬 ; 张合新 ; 朱开锐 ; 李国梁 ; 惠俊军
  • 英文作者:WU Yubin;ZHANG Hexin;ZHU Kairui;LI Guoliang;HUI Junjun;Department of Control and Engineering, Rocket Force University of Engineering;Chongqing Military Agency of the Army;Chinese People's Liberation Army 96037;
  • 关键词:非脆弱 ; 交互式凸组合技术 ; Lyapunov-Krasovskii泛函(LKF) ; 火箭发动机 ; 四重积分
  • 英文关键词:non-fragile;;reciprocally convex combination;;Lyapunov-Krasovskii functional (LKF);;rocket motors;;quadruple-integral term
  • 中文刊名:BZCJ
  • 英文刊名:Explosion and Shock Waves
  • 机构:火箭军工程大学控制工程系;中国人民解放军陆军重庆军代局;中国人民解放军96037部队;
  • 出版日期:2019-03-05
  • 出版单位:爆炸与冲击
  • 年:2019
  • 期:v.39;No.185
  • 基金:国家自然科学基金(61374120)
  • 语种:中文;
  • 页:BZCJ201903012
  • 页数:12
  • CN:03
  • ISSN:51-1148/O3
  • 分类号:101-112
摘要
针对某液体火箭发动机燃烧室的燃烧过程,设计了鲁棒非脆弱H_∞状态反馈控制器。首先,基于一种新型的时滞分割法和交互式凸组合技术,借助于构造一个包含四重积分项的Lyapunov-Krasovskii泛函(LKF),并利用新的积分不等式方法给出了LMI形式的时滞相关有界实判据;其次,在有界实判据的基础上,采用矩阵的合同变换以及变量替代技巧将燃烧过程非线性矩阵不等式线性化,通过求解线性矩阵不等式得到相应的非脆弱H_∞控制器的可行解。模拟结果验证了本文设计方法的有效性。
        In this study we dealt with the robust non-fragile H_∞ controller for the combustion process in liquid propellant rocket motor chambers. In developing a less conservative H_∞ performance analysis criterion, we introduced a Lyapunov-Krasovskii functional comprising quadruple-integral term. Then, based on a new delay-partitioning method, the reciprocally convex combination technique and the integral inequality approach (ⅡA), we formulated the bounded real criterion in terms of linear matrix inequalities(LMIs). Furthermore, based on this bounded real criterion, we translated the nonlinear matrix inequality into the linear matrix inequality by using the matrix congruent transformation and the variable substitution technique, and obtained the parameter expression of non-fragile H_∞ controller by solving the feasible linear matrix inequality. The numerical examples we provided showed the effectiveness of the proposed theoretical results.
引文
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