压气机静子叶片转角主备控制器 转换装置改进

李杰; 樊丁; 彭凯; 尹飞佳

压气机静子叶片转角主备控制器转换装置改进

西北工业大学动力与能源学院,西安 710072

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出版历程
- 收稿日期: 2010-04-09
- 修回日期: 2010-08-27
- 刊出日期: 2011-04-28

Improvement of switch devices of compressor stator blade angle main-backup controller

School of Power and Energy, Northwestern Polytechnical University,Xi'an 710072,China

摘要

摘要: 为了确保某型航空发动机高压压气机可调静子叶片转角控制系统主备控制器转换的可靠性,对系统原有的控制器转换装置进行了改进,加入了新的转换机构.仿真计算结果表明,若数字电子控制器故障后,未按照预定要求输出0脉冲占空比,而输出了固定的非0脉冲占空比信号或随机的不可预测的脉冲占空比信号,原系统的正常工作将受到较严重的影响;而采用改进的转换装置后,系统的正常工作不受影响且能够实现主备控制器安全、平稳、快速地转换.对转换装置所做的改进改善了该控制系统的转换性能并提高了发动机工作可靠性.
- 高压压气机可调静子叶片转角 /
- 航空发动机 /
- 控制系统 /
- 转换特性 /
- 转换装置
Abstract: In order to ensure the main-backup controller switch reliability of an aeroengine high-pressure compressor variable stator blade angle control system,the original switch devices were improved by adding a new switch component.Simulation results show that,if the fault of digital electronic controller (DEC) occurs,and then if DEC output does not meet the design requirements, i.e .,the output pulse duty cycle of DEC is not 0 but fixed or random,unpredictable signal,the normal work of the original system will be seriously affected,while the normal work of the system with improved switch devices will not be affected,and the switching of main-backup controller is safe,rapid and smooth.Control system's switch performance and aero-engine's functional reliability are improved by the switch devices improvement.
- high-pressure compressor variable stator blade angle /
- aero-engine /

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参考文献(12)

[1]	秦海波,张天宏,孙建国.面向FADEC系统BIT 验证的综合故障注入器研究[J].航空动力学报,2005,21(3):581-587. QIN Haibo,ZHANG Tianhong,SUN Jianguo.Study on comprehensive fault injector for BIT verification of the FADEC system [J].Journal of Aerospace Power,2005,21(3):581-587.(in Chinese)
[2]	李勇,樊丁,石斌.航空发动机FADEC系统双机时钟级同步技术研究[J].计算机测量与控制,2006,14(4):508-509. LI Yong,FAN Ding,SHI Bin.Investigation about synchronization of real time clock between the two computers in aeroengine FADEC system[J].Computer Measurement & Control,2006,14(4):508-509.(in Chinese)
[3]	Witezak M,Obuehowiez A,Korbiez J.Genetic programming based approaches to identification and fault diagnosis of nonlinear dynamic systems[J].Control,2002,75(13):1012-1031.
[4]	张绍基.航空发动机控制系统的研究与展望[J].航空动力学报,2004,19(3):375-382. ZHANG Shaoji.A review of aeroengine control system[J].Journal of Aerospace Power,2004,19(3):375-382.(in Chinese)
[5]	Reed J A,Afjeh A A.Interactive,secure web-enabled aircraft engine simulation using XML data binding integration .AIAA Paper 2002-4058,2002.
[6]	Reed J A,Follen G J,Afjeh A A.Improving the aircraft design process using web-based modeling and simulation[J].ACM Transactions on Modeling and Computer Simulation,2000,10(1):58-83.
[7]	Sexton W R A.New method to control turbofan engine starting by varying compressor surge valve bleed .Virginia,US:Virginia Polytechnic Institute and Atate University,2001.
[8]	Beldimna O,Bushnell L.Stability linearization and control of switched systems .California,US:American Control Conference,1999.
[9]	Roth B.A work potential perspective of engine component performance .AIAA Paper 2001-3300,2001.
[10]	Pettersson S,Lennartson B.Stability and robustness of hybrid systems .Kobe,Japan:35th IEEE Conference,Decision and Control,1996.
[11]	Svakin A V,Matveev A S.Cyclic linear differential automatic:a simple class of hybrid dynamical systems[J].Automata,2000,36(5):727-734.
[12]	Libeozrn D,Morse A S.Basic problems in stability and design of switched systems[J].IEEE Control System Magazine,1999,19(5):59-70.