涡轴发动机LQ/<em>H</em><sub>∞</sub>抗扰控制方法

廖光煌; 李秋红; 卢辰昊; 黄金泉

涡轴发动机LQ/H_∞抗扰控制方法

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国航空工业集团公司航空动力控制系统研究所, 江苏无锡 214063

基金项目: 中央高校基本科研业务费专项资金(NZ2012104)

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出版历程
- 收稿日期: 2011-10-17
- 刊出日期: 2012-09-28

Disturbance rejection control method for turboshaft engines based on LQ/H_∞

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Aviation Motor Control System Institute, Aviation Industry Corporation of China, Wuxi Jiangsu 214063, China

摘要

摘要: 提出了抑制涡轴发动机负载干扰的线性二次型(LQ)/H_∞控制算法,以总距为干扰建模,利用线性矩阵不等式求得既满足LQ指标又对干扰具有H_∞性能约束的状态反馈控制律.提出修正指令抑制干扰策略.采用比例微分控制将总距变化转换为动力涡轮转速指令的修正,实现增大或减小机动飞行中动力涡轮转速指令,抑制实际转速的下垂或超调.仿真结果表明:该控制方法能有效抑制干扰并具有良好的实时性.
- 涡轴发动机 /
- 抗扰控制 /
- 线性二次型 /
- H_∞ /
- 变指令
Abstract: The linear quadratic (LQ)/H_∞ control method was proposed for turboshaft engines to reject disturbance.The collective pitch was treated as disturbance during modeling.The state feedback law was obtained based on linear matrix inequality (LMI), and it satisfied both LQ index and H_∞ disturbance rejection index.The disturbance rejection method based on reference adjustment was proposed.The adjustment of power turbine rotor speed reference was achieved by proportional derivative (PD) control according to collective pitch variation,and the overshoot or droop of the real speed was suppressed during maneuver.Simulation results show that the methods proposed can suppress the disturbance effectively and run in realtime.
- turboshaft engine /
- disturbance rejection control /
- linear quadratic /
- H_∞ /
- reference variation

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参考文献(15)

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