某型发动机压气机叶片调节控制系统设计技术研究
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摘要
随着航空发动机技术的提高,各种发动机普遍采用可调叶片控制器调节压气机静子叶片的位置,以改善发动机非设计点的性能,扩大压气机稳定工作范围。目前,发动机广泛使用的可调叶片控制器的控制方案,多数是按照压气机进口温度及其转速来调节叶片角度的,通过按设计的控制规律调节压气机导向叶片角度,保证压气机稳定工作,不发生喘振。
本文介绍了压气机叶片调节控制系统的总体方案设计,提出了采用FADEC控制,具有修改控制规律方便,调节精度高,动态响应快,系统工作稳定可靠等优点。本方案以TMS32OF2812为CPU,构建整个控制系统的硬件电路,用C语言进行软件设计,实现控制算法计算程序,并对控制软件的结构、控制流程进行了分析。另外,为了评估控制系统的性能,对电液转换元件进行计算和选择,然后利用Matlab软件中的Simulink建立了数学模型,采用PID控制算法,对控制系统进行了仿真,并对仿真结果进行了分析。
Along with aeroengine technology development , it is general to make use of blade adjustment controller adjusting blade position of compressor in order to improve engine off-design point; performance , expand stable operation range of compressor and anti-surge.Now, the compressor inlet temperature and rotating speed is mostly used to regulate aero engine vane. In order to make compressor operate stably and prevent the surge ,make use of the control law designed to regulate aero engine vane.
The paper introduces the global scheme design of blade adjustment control system of compressor with FADEC control. It is very convenient to modify control law ,adjust precision and improve dynamic response and system stabilization. The scheme includes hardware electric circuit which CPU is TMS32OF2812 , control software structure and control flow . Use Matlab to simulate control system with PID based on count and selection of electro-hydraulic conversion element ,in order to know control system performance.
本文介绍了压气机叶片调节控制系统的总体方案设计,提出了采用FADEC控制,具有修改控制规律方便,调节精度高,动态响应快,系统工作稳定可靠等优点。本方案以TMS32OF2812为CPU,构建整个控制系统的硬件电路,用C语言进行软件设计,实现控制算法计算程序,并对控制软件的结构、控制流程进行了分析。另外,为了评估控制系统的性能,对电液转换元件进行计算和选择,然后利用Matlab软件中的Simulink建立了数学模型,采用PID控制算法,对控制系统进行了仿真,并对仿真结果进行了分析。
Along with aeroengine technology development , it is general to make use of blade adjustment controller adjusting blade position of compressor in order to improve engine off-design point; performance , expand stable operation range of compressor and anti-surge.Now, the compressor inlet temperature and rotating speed is mostly used to regulate aero engine vane. In order to make compressor operate stably and prevent the surge ,make use of the control law designed to regulate aero engine vane.
The paper introduces the global scheme design of blade adjustment control system of compressor with FADEC control. It is very convenient to modify control law ,adjust precision and improve dynamic response and system stabilization. The scheme includes hardware electric circuit which CPU is TMS32OF2812 , control software structure and control flow . Use Matlab to simulate control system with PID based on count and selection of electro-hydraulic conversion element ,in order to know control system performance.
引文
[1]廉筱纯,吴虎.航空发动机原理,西北工业大学出版社[M],94-102.
[2]姚伟,对我国研制大飞机动力控制的展望与看法[D],中国航空学会第十四届发动机自动控制专业学术交流会论文集2008.10,120-125.
[3]赵顺利等.某型机械液压式航空发动机导叶调节器方案设计,航空动力控制系统重点实验室学术论文选编,中国一航动力控制系统研究所,2005~2007,246-257.
[4]航空发动机设计手册(第15册)[M],航空工业出版社,2002.1,410-726.
[5]熊静琪.计算机控制技术[M],电子工业出版社,2005.7,230-268.
[6]胡寿松.自动控制原理(第四版)[M],科学出版社,2002.3,128-150.
[7]刑志强.推力矢量喷管控制系统设计与仿真研究[D],北京航空航天大学,2002.2,40-44.
[8]童万军.WF1静叶调节修改方案(第2版),中国燃气涡轮研究院,2005.9,2-9.
[9]苏奎峰等.TMS320F2812原理与开发[M],电子工业出版社,2005.4,10-48.
[10]王念旭等.DSP基础与应用系统设计[M],北京航空航天大学出版社,2001.8,68-102.
[11] TMS320F2812 Digital Signal Processors Data Manua[M]l,2006.5,55-87.
[12]付家才.DSP控制工程实践技术[M],化学工业出版社,2005.6,32-65.
[13]高毅军.发动机用转速和位移信号调理规范,中国燃气涡轮研究院,2005.9,1-9.
[14]周霖.DSP系统设计与实现[M],国防工业出版社,2003.10,67-98.
[15].Sun Jianguo,Vasilyev,B.Hyasov.Advanced MulKivariable Control Systems of Aeroengines.Beijing:Beijing University of AeronauKics and AstronauKics,2005,102-118.
[16] Aeron J. Ostroff, Keith D. Hoffler , High Alpha Research Vehicle(HARV) Longitudinal Controller: Design Analyses and SimulaKion Results NASA-TP 3446,34-41.
[17]黄宗霖,控制系统MATLAB计算及仿真[M],国防工业出版社,2004.9,88-110.
[18]张国良等,模糊控制及其MATLAB应用[M],西安交通大学出版社,2002.11,82-89.
[19] SanJay Garg,Duane L.Mattern,Integrated Flight/Propulsion Control System Design Based on a Centralized Approach, Journal of Guidance Dynamic &Control VOL 14 NO1,JAN-FEB,1991,113-125.
[20] Garson , George T. and Capone, Francis J, StaKic internal Performance of an Aximmetric Nozzle with MulKiaxis Thrust Vectoring Capability,NASA TM-4237 1991.2,5-9.
[21] Smith K L,Kerr W B,et al.Aircraft Control IntegraKion Methodology and Performance Impact.AIAA-85-1424,18-23.
[22] Smith R H Chisholm J D,et al.OpKimizaKion Aircraft Performance with AdapKive Integrated Flight/Propulsion Control.Journal of Engineering for Gas Turbine and Power,Jan.1991,43-49.
[23]杨印堂等.DSP应用开发从实践到提高[M],中国电力出版社,2007.7,139-173.
[24]苏奎峰等.TMS320X281X DSP原理及C程序开发[M],北京航空航天大学出版社,2008.2,128-139.
[25] Katsuhiko Ogata.现代控制工程[M],电子工业出版社,2000.5,128-139,625-634.
[2]姚伟,对我国研制大飞机动力控制的展望与看法[D],中国航空学会第十四届发动机自动控制专业学术交流会论文集2008.10,120-125.
[3]赵顺利等.某型机械液压式航空发动机导叶调节器方案设计,航空动力控制系统重点实验室学术论文选编,中国一航动力控制系统研究所,2005~2007,246-257.
[4]航空发动机设计手册(第15册)[M],航空工业出版社,2002.1,410-726.
[5]熊静琪.计算机控制技术[M],电子工业出版社,2005.7,230-268.
[6]胡寿松.自动控制原理(第四版)[M],科学出版社,2002.3,128-150.
[7]刑志强.推力矢量喷管控制系统设计与仿真研究[D],北京航空航天大学,2002.2,40-44.
[8]童万军.WF1静叶调节修改方案(第2版),中国燃气涡轮研究院,2005.9,2-9.
[9]苏奎峰等.TMS320F2812原理与开发[M],电子工业出版社,2005.4,10-48.
[10]王念旭等.DSP基础与应用系统设计[M],北京航空航天大学出版社,2001.8,68-102.
[11] TMS320F2812 Digital Signal Processors Data Manua[M]l,2006.5,55-87.
[12]付家才.DSP控制工程实践技术[M],化学工业出版社,2005.6,32-65.
[13]高毅军.发动机用转速和位移信号调理规范,中国燃气涡轮研究院,2005.9,1-9.
[14]周霖.DSP系统设计与实现[M],国防工业出版社,2003.10,67-98.
[15].Sun Jianguo,Vasilyev,B.Hyasov.Advanced MulKivariable Control Systems of Aeroengines.Beijing:Beijing University of AeronauKics and AstronauKics,2005,102-118.
[16] Aeron J. Ostroff, Keith D. Hoffler , High Alpha Research Vehicle(HARV) Longitudinal Controller: Design Analyses and SimulaKion Results NASA-TP 3446,34-41.
[17]黄宗霖,控制系统MATLAB计算及仿真[M],国防工业出版社,2004.9,88-110.
[18]张国良等,模糊控制及其MATLAB应用[M],西安交通大学出版社,2002.11,82-89.
[19] SanJay Garg,Duane L.Mattern,Integrated Flight/Propulsion Control System Design Based on a Centralized Approach, Journal of Guidance Dynamic &Control VOL 14 NO1,JAN-FEB,1991,113-125.
[20] Garson , George T. and Capone, Francis J, StaKic internal Performance of an Aximmetric Nozzle with MulKiaxis Thrust Vectoring Capability,NASA TM-4237 1991.2,5-9.
[21] Smith K L,Kerr W B,et al.Aircraft Control IntegraKion Methodology and Performance Impact.AIAA-85-1424,18-23.
[22] Smith R H Chisholm J D,et al.OpKimizaKion Aircraft Performance with AdapKive Integrated Flight/Propulsion Control.Journal of Engineering for Gas Turbine and Power,Jan.1991,43-49.
[23]杨印堂等.DSP应用开发从实践到提高[M],中国电力出版社,2007.7,139-173.
[24]苏奎峰等.TMS320X281X DSP原理及C程序开发[M],北京航空航天大学出版社,2008.2,128-139.
[25] Katsuhiko Ogata.现代控制工程[M],电子工业出版社,2000.5,128-139,625-634.