用于涡轴发动机传感器故障诊断的未知输入观测器干扰矩阵估算

杨超; 王曦; 时瑞军; 周剑波; 高世煌; 覃道亮

doi:10.13224/j.cnki.jasp.2016.04.024

用于涡轴发动机传感器故障诊断的未知输入观测器干扰矩阵估算

doi: 10.13224/j.cnki.jasp.2016.04.024

杨超^1,2,
王曦^1,2,
时瑞军³,
周剑波³,
高世煌³,
覃道亮^1,2

1. 北京航空航天大学能源与动力工程学院, 北京 100191;
2. 先进航空发动机协同创新中心, 北京 100191;
3. 中国航空工业集团公司中国航空动力机械研究所, 湖南株洲 412002

基金项目:

航空科学基金(2011ZB510019)

详细信息

作者简介:
杨超(1989-),男,天津人,硕士,主要研究方向为航空发动机控制及故障诊断.E-mail:chtjyc@126.com

中图分类号: V233.7
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- 被引次数: 0
出版历程
- 收稿日期: 2014-08-12
- 刊出日期: 2016-04-28

Estimation of unknown input observer disturbance matrix for fault diagnosis of turboshaft engine sensors

1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;
3. China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou Hunan 412002, China

摘要

摘要: 针对处理涡轴发动机控制系统传感器故障诊断问题时有着良好性能的未知输入观测器展开研究,分析了与系统建模误差相关的干扰矩阵对未知输入观测器观测出的系统状态准确度的影响,提出了一种基于全阶状态观测器的涡轴发动机系统模型干扰矩阵的估算方法,该方法对某一固定工况下的干扰矩阵估算十分准确,使得根据此干扰矩阵设计出的未知输入观测器可以完全不受系统建模误差的影响.在此基础上,又给出了一种适应于更广泛工况范围的干扰矩阵近似方法,使得变工况下的未知输入观测器一样不受建模误差的影响.仿真结果表明:基于该方法估算出的干扰分布矩阵可以保证观测器具有良好的性能,在变工况下对发动机输出量估计残差的二范数不大于2.
- 涡轴发动机 /
- 控制系统 /
- 故障诊断与容错控制 /
- 未知输入观测器 /
- 干扰矩阵估算
Abstract: Focusing on the research of unknown input observer of good performance to deal with the problem of control system's sensors fault, a method using a full-order state observer to estimate the disturbance matrix of turboshaft engine system model was proposed based on the analysis of relationship between the disturbance matrix reflecting modeling uncertainty and the accuracy of states observed by UIO. This method contributed to an accurate disturbance matrix so that the results of UIO had no combination of modeling uncertainty when the operating state of turboshaft was fixed. Furthermore, this method was developed to meet the requirements of variable operating states of the engine so that the modeling uncertainty had no influence on the design of UIO in this situation. Finally, some simulations were made to verify the proposed methods, which contribute to obtain a better matrix to ensure that the observed output residual of UIO is less than 2.
- turboshaft /
- control system /
- fault diagnosis and fault tolerant control /
- unknown input observer /
- estimation of disturbance matrix

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参考文献(20)

[1]	陈毅.航空发动机控制系统传感器故障诊断研究[D].南京:南京航空航天大学,2007. CHEN Yi.Fault diagnosis on sensors of control system for aeroengines[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2007.(in Chinese)
[2]	Garg S.NASA Glenn research in controls and diagnostics for intelligent aerospace propulsion systems[R].NASA/TM-2005-214036,2005.
[3]	颜秋英,时瑞军,张秋贵,等.涡轴发动机健康管理跟踪滤波器技术[J].航空发动机,2011,37(2):16-19. YAN Qiuying,SHI Ruijun,ZHANG Qiugui,et al.Tracking filter technology of health management for turboshaft engine[J].Aeroengine,2011,37(2):16-19.(in Chinese)
[4]	张征.军用涡轴发动机发展研究[J].航空发动机,2011,37(6):58-62. ZHANG Zheng.Development of military turboshaft engine[J].Aeroengine,2011,37(6):58-62.(in Chinese)
[5]	姜彩虹,孙志岩,王曦.航空发动机预测健康管理系统设计的关键技术[J].航空动力学报,2009,24(11):2589-2594. JIANG Caihong,SUN Zhiyan,WANG Xi.Critical technologies for aero-engine prognostics and health management systems development[J].Journal of Aerospace Power,2009,24(11):2589-2594.(in Chinese)
[6]	Kobayashi T,Simon D L.Application of a bank of Kalman filters for aircraft engine fault diagnostics[R].ASME Paper GT2003-38550,2003.
[7]	孔祥兴.民用涡扇发动机故障诊断仿真平台关键技术研究[D].北京:北京航空航天大学,2013. KONG Xiangxing.A research on the pivotal technique of civil turbofan engine fault diagnosis simulation platform[D].Beijing:Beijing University of Aeronautics and Astronautics,2013.(in Chinese)
[8]	王曦,程茵.国外航空推进控制技术的发展[J].航空发动机,2009,35(3):5-7. WANG Xi,CHENG Yin.Development of thrust control technology for foreign aeroengine[J].Aeroengine,2009,35(3):5-7.(in Chinese)
[9]	Chen J,Patton R J.Robust model-based fault diagnosis for dynamic systems[M].Boston,MA:Kluwer Academic Publishers,1999.
[10]	覃道亮,何皑,孔祥兴,等.基于UIO的航空发动机控制系统传感器故障诊断[J].航空动力学报,2011,26(6):1396-1404. TAN Daoliang,HE Ai,KONG Xiangxing,et al.UIO-base sensor fault diagnosis for aero-engine control systems[J].Journal of Aerospace Power,2011,26(6):1396-1404.(in Chinese)
[11]	何皑,覃道亮,孔祥兴,等.基于UIO的航空发动机执行机构故障诊断[J].推进技术,2012,33(1):98-104. HE Ai,TAN Daoliang,KONG Xiangxing,et al.UIO-based diagnosis of aeroengine actuator faults[J].Journal of Propulsion Technology,2012,33(1):98-104.(in Chinese)
[12]	何皑.基于LMI的航空发动机智能容错控制技术研究[D].北京:北京航空航天大学,2011. HE Ai.The LMI-based intelligent fault-tolerant control for aircraft engine[D].Beijing:Beijing University of Aeronautics and Astronautics,2011.(in Chinese)
[13]	时瑞军,周剑波,张秋贵,等.涡轴发动机性能退化数学建模研究[J].航空发动机,2010,36(4):26-28. SHI Ruijun,ZHOU Jianbo,ZHANG Qiugui,et al.Mathematical model study on performance deterioration of turboshaft engine[J].Aeroengine,2010,36(4):26-28.(in Chinese)
[14]	Tufts D W,Kumaresan R,Kirsteins I.Data adaptive signal estimation by singular value decomposition of a data matrix[J].Proc.IEEE,1982,70(6):684-685.
[15]	Eckart C,Young G.The approximation of one matrix by another of lower rank[J].Psychometrika,1936,1(3):211-218.
[16]	Ballin M G.A high fidelity real-time simulation of a small turboshaft engine[R].NASA-TM-100991,1988.
[17]	Spack J M.Linear parameter varying controller for a small turboshaft engine[D].Boston,Massachusetts:Northeastern University,2011.
[18]	杨超,王曦.涡轴发动机双回路结构PI控制器设计[J].航空发动机,2014,40(增刊1):51-56. YANG Chao,WANG Xi.Design of PI controller with double-loop structure for a turboshaft[J].Aeroengine,2014,40(suppl.1):51-56.(in Chinese)
[19]	YANG Chao,WANG Xi,LIU Mengni,et al.Design of PI controller with three-loop structure for power balance of turboshaft[R].ASME Paper GT2014-27338,2014.
[20]	Grant M C,Boyd S P.Matlab software for disciplined convex programming[R/OL].[2013-8-15].http://cvxr.com/cvx/.