基于内模原理的涡轴发动机状态反馈控制方法

Investigation of state feedback control based on internal model principle for an turbo-shaft Engine

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

摘要: 某型涡轴发动机全权限数控系统采用了状态反馈控制方式.根据内模原理, 引入伺服补偿器, 使设计的控制系统不仅具有较强的鲁棒性, 而且在用于指令跟踪时能消除稳态误差;根据性能指标要求设计了状态反馈控制器, 从而提高控制系统的品质.与目前的PID控制方式相比较, 半物理模拟试验结果表明该控制方式有显著的性能改进.
- 航空、航天推进系统 /
- 涡轴发动机 /
- 数控系统 /
- 内模原理 /
- 状态反馈
Abstract: A turbo-shaft engine FADEC system is subjected to the state feedback control mode.Based on the internal principle,a servo-compensator was introduced such that the control system could present strong robustness,and also eliminate steady state errors when tracking with commands.According to performance index,a states feedback controller was also designed to improve the performance of the control system.As compared with PID control method,the test results show an outstanding performance of the control system.
- aerospace propulsion system /
- turbo-shaft engine /
- FADEC /
- internal model principle /
- state feedback

[1]	章霖官译自 NASA-CR-177080.采用LQG/LTR设计方法的GET700发动机多变量控制[R].航空动力装置数字控制技术译文(第一集),无锡:航空工业总公司第六一四所,1995.
[2]	杨征山,李胜泉,章霖官.涡轴发动机涡轮转速控制回路方案研究[J].航空发动机,2005,31(2):46-50.YANG Zhengshan,LI Shengquan,ZHANG Linguan.Research on the power turbine speed control loop of turboshaft engine[J].Aeroengine,2005,31(2):46-50.
[3]	胡寿松.自动控制原理[M].北京:国防工业出版社,1984.
[4]	冯正平,孙建国.航空发动机小偏差状态变量模型的建立方法[J].推进技术,2001,22(1):54-57.FENG Zhengping,SUN Jianguo.Modeling of small perturbation state variable model for aeroengines[J].Journal of Propulsion Technology,2001,22(1):54-57.
[5]	郑大钟.线性系统理论[M].北京:清华大学出版社,1990.
[6]	杨刚,孙建国,李秋红.航空发动机控制系统中的增广LQR方法[J].航空动力学报,2004,19(1):153-158.YANG Gang,SUN Jianguo,LI Qiuhong.Augmented LQR method for aeroengine control systems[J].Journal of Aerospace Power,2004,19(1):153-158.