基于LMI的超燃冲压发动机鲁棒PI控制器设计  

LMI-based Robust PI Controller Design for Scramjet

作　　者：卢彬[1] 史新兴[1] 林敏[1] 牛军[1] 鲍文[2] 

机构地区：[1]中国航天科工集团三院第三十一所,北京100074 [2]哈尔滨工业大学高超声速技术研究中心,哈尔滨150001

出　　处：《战术导弹技术》2011年第3期94-97,共4页Tactical Missile Technology

摘　　要：首先将燃油供给系统作为超燃冲压发动机的主导动态,并假设燃油供给系统为惯性环节,构建了超燃冲压发动机推力闭环控制系统.然后基于LMI理论提出了一种单输入单输出系统PI控制器参数整定方法,并给出了该控制器存在的一个充分条件.最后基于该方法设计了超燃冲压发动机单点喷油推力闭环控制系统的PI控制器,仿真结果表明,该控制器具有良好的鲁棒性.Fuel supply system is taken as main dynamics of scramjet and assumed as an inertial link to construct a scramjet thrust closed-loop control system. A LMI-based single-input single-output system is proposed for defining PI controller parameters. A sufficient condition for the existence of the designed controller is given. Finally, a PI controller for scramjet thrust closed-loop control system with single-point fuel injection is designed based on the proposed method. The simulation results show that the controller is provided with good robustness.

关 键 词：超燃冲压发动机 线形矩阵不等式 PI控制器 

分 类 号：V433[航空宇航科学与技术—航空宇航推进理论与工程]