航空学报 > 2006, Vol. 27 Issue (5): 773-777

航空发动机H/LTR控制试验验证

杨刚1,2, 孙健国1, 姚华2, 臧军2, 刘爱萍2, 易学飞2, 张力辉2   

  1. 1. 南京航空航天大学 能源与动力学院, 江苏 南京 210016;2. 中国航空动力控制系统研究所, 江苏 无锡 214063
  • 收稿日期:2005-03-10 修回日期:2005-09-05 出版日期:2006-10-25 发布日期:2006-10-25

Experimental Verification of H/LTR Method for Aeroengine Control Systems

YANG Gang1,2, SUN Jian-guo1, YAO Hua2, ZANG Jun2, LIU Ai-ping2, YI Xue-fei2, ZHANG Li-hui2   

  1. 1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;2. China Aviation Motor Control System Institute, Wuxi 214063, China
  • Received:2005-03-10 Revised:2005-09-05 Online:2006-10-25 Published:2006-10-25

摘要: 用半物理模拟试验验证了多变量鲁棒控制在航空发动机中的应用,给出了航空发动机中H/LTR控制模块的设计过程及注意事项。从半物理模拟试验结果可见:与LQG/LTR控制器不同,H/LTR控制器能在半物理模拟试验环境下稳定控制航空发动机;H/LTR控制器具有优良的噪声抑制功能;基于包线内一点设计的H/LTR控制器可适用于包线内其他区域的加力与非加力状态下的爬升、加速等仿真试验,验证了H/LTR方法的鲁棒性。推进了多变量鲁棒控制设计方法在航空发动机中的实际应用。

关键词: 航空发动机, H/LTR, LQG/LTR, 半物理模拟试验

Abstract: The application of multivariable robust control methods to aeroengines was testified by a semi-physical simulation. The detailed design procedure of an H/LTR control module for the aeroengine control system was also included. From the simulation results, it is clear that the H/LTR controller stabilized the whole system in semi-physical simulation environment. This is much different from the LQG/LTR controller that is unstable under the same condition. Further more, one can find that the H/LTR method has good noise rejection property. Thirdly, the controller, based only on the intermediate power level of one point in the envelope, offers satisfactory performance for a large area in the envelope in the augmented and un-augmented simulation. Therefore, it is experimentally testified that H/LTR method is a multivariable robust control design method that can be practically applied to engineering environment. Finally, the success of this semi-physical simulation shows that the research of multivariable control methods has a big progress in the direction of practical application to aeroengine control system.

Key words: aeroengine, H/LTR, LQG/LTR, semi-physical simulation

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