控制问题中航空发动机飞行包线区域最优划分  

Flight-envelope optimization partition for aeroengines control

作　　者：胡卫红[1,2] 李述清[3] 孙健国[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]第二炮兵驻第31研究所军事代表室,北京100074 [3]第二炮兵工程学院,陕西西安710025

出　　处：《推进技术》2011年第3期391-395,共5页Journal of Propulsion Technology

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。分析了发动机线性状态空间模型与进气道出口气流总温总压参数有关特性。在此基础上定义了飞行包线内任意两飞行点间的广义距离,提出将飞行包线区域划分与标称点设计问题转化为一个基于该广义距离的最大覆盖优化问题,即选择尽量少的标称点实现对飞行包线区域的覆盖。以涡扇发动机及其进气道为例,采用文中方法对其包线区域进行了划分计算,并对标称点与其覆盖区域内最远点处发动机线性化模型进行了比较。结果表明,该区域划分和标称点选择的优化方法的有效性。According to the aeroengine principle,the aeroengine efficiency of engine model are related with the total temperature and total pressure at the outlet of the inlet.And based on this trait,a general distance between two points in flight envelope was put forward.Then,the problem of dividing the flight envelope and selecting the nominal points in a flight envelope were translated into a most overlay problem as a mathematical 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.Lastly,a flight envelope area of an inlet-aeroengine system was divided by using this optimizing method,and the coefficients,gains and singular values of aeroengine linear models at one normal point and the farmost point in its overlay area were compared.These results above indicate that this method of dividing flight envelope and selecting nominal points is proper.

关 键 词：航空发动机 飞行包线 标称点 最大覆盖 优化 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]