用于控制器分区设计的发动机飞行包线区域最优划分

李述清; 张胜修; 胡卫红

用于控制器分区设计的发动机飞行包线区域最优划分

1.
中国人民解放军第二炮兵工程学院 303教研室, 西安 710025
2.
中国人民解放军 96111部队, 陕西韩城 715400
3.
中国人民解放军第二炮兵驻第31研究所军代室, 北京 100074

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出版历程
- 收稿日期: 2011-01-12
- 修回日期: 2011-07-08
- 刊出日期: 2012-02-28

Partition optimization in the flight envelope for control design of aero-engines

1.
Staff-Room 303, The Second Artillery Engineering College, People’s Liberation Army, Xi’an 710025, China
2.
The United 96111, People’s Liberation Army, Hancheng Shaanxi 715400, China
3.
The Second Artillery Military Delegation in the 31st Research Institute, People’s Liberation Army, Beijing 100074, China

摘要

摘要: 结合最优化理论和线性系统理论,对控制问题中航空发动机飞行包线区域划分方法展开了研究.首先基于小偏离线性动态模型,根据线性系统理论,将发动机动态特性的摄动归为线性模型的状态矩阵特征值和稳态增益的摄动来表征.然后在此基础上,定义了一种广义距离以表征发动机动态特性的摄动程度,并以定义了区域的划分原则.继而提出将飞行包线区域划分问题转化为一个基于该广义距离的最优化问题.最后就某型涡扇发动机情形,对其飞行包线区域进行了划分计算,并对划分区域内发动机线性模型摄动进行了比较,结果表明该区域划分和标称点选择方法的有效性.
- 航空发动机 /
- 飞行包线 /
- 标称点 /
- 最大覆盖 /
- 优化
Abstract: According to the optimization theory and linear system theory,the method of flight-envelop optimization partition for aero-engines is researched.First,linear state variable mode (LSVM) was used to describe aero-engine’s dynamic characteristic of small perturbation on steady operating point,and the perturbation between LSVMs was denoted by the perturbation of coefficient matrix eigenvalues and low-frequency gains of the LSVMs.Then,a general distance based on the perturbation of eigenvalues and low-frequency gains of the LSVMs was put forward.And the problem of dividing the flight envelope and selecting the nominal points in a flight envelope was translated into a most overlay problem.Thus,based on the general distance,a set of least number of nominal points could be found to divide the flight envelope by using optimizing method.Last,a flight envelope area of a turbofan engine was divided by using this method,and the results indicated that this method was proper.
- aero-engine /
- flight envelop /
- nominal point /
- most overlay /
- optimize

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参考文献(12)

[1]	樊思齐,徐芸华.航空推进系统控制[M].西安:西北工业大学出版社,1995.
[2]	Frederick D,Garg S,Adibhatla S.Turbofan engine control design using robust multivariable control technology.AIAA-96-2587,1996.
[3]	SUN Jianguo,Vasilyev V,Hyasov B.现代航空发动机多变量控制系统[M].北京:北京航空航天大学出版社, 2005.
[4]	李中建.大包线飞行控制系统鲁棒设计研究.西安:西北工业大学,2000.
[5]	陶涛.航空发动机鲁棒控制研究.西安:西北工业大学,1997.
[6]	李剑,谢寿生,丁康乐.航空发动机全飞行包线小偏差动态数学模型[J].空军工程大学学报,2002,3(5):12-16. LI Jian,XIE Shousheng,DING Kangle.Research on small perturabation dynamics mathematical model in whole flight envelope for aeroengine[J].Journal of Airforce Engineering University,2002,3(5):12-16.(in Chinese)
[7]	王进,李剑,谢寿生.航空发动机控制问题研究中飞行包线区域的划分方法[J].航空动力学报,2003,18(3):436-439. WANG Jing,LI Jian,XIE Shousheng.Flight envelope division method in aeroengine control study[J].Journal of Aerospace Power,2003,18(3):436-439.(in Chinese)
[8]	赵延渝.航空发动机数学模型[J].电子科技大学,2005,34(4):545-547. ZHAO Tingyu.Aeroengine’s mathematical model[J].Journal of UEST of China,2005,34(4):545-547.(in Chinese)
[9]	王海泉,郭迎清,李睿,等.航空发动机全飞行包线鲁棒控制器设计研究[J].测控技术,2009,28(5):48-51. WANG Haiquan,GUO Yingqing,LI Rui,et al.Design of full flight envelop controller for aero-engine[J].Measure and Control Technique,2009,28(5):48-51.(in Chinese)
[10]	王小平,曹立明.遗传算法:理论、应用与软件实现[M].西安:西安交通大学出版社,2001.
[11]	LI Songlin,SUN Jianguo.Application of genetic algorithm to solving nonlinear model of aeroengine[J].Chinese Journal of Aeronautics,2003,16(2):69-72.
[12]	廉筱纯,吴虎.航空发动机原理[M].西安:西北工业大学出版社,2005.