航空发动机小偏差状态变量模型的建立方法  

Modeling of small perturbation state variable model for aeroengines

作　　者：冯正平[1] 孙健国[2] 

机构地区：[1]上海交通大学船舶与海洋工程学院,上海200030 [2]南京航空航天大学动力工程系,江苏南京210016

出　　处：《推进技术》2001年第1期54-57,共4页Journal of Propulsion Technology

基　　金：航空科学基金资助项目! (96C5 2 0 2 9)

摘　　要：采用最小二乘拟合法建立用于航空发动机鲁棒控制系统设计的小偏差状态变量模型 ,即根据发动机非线性模型的小偏差动态响应数据直接拟合出其小偏差状态变量模型。由于建模误差在最小二乘意义下最小 ,因而应用该方法可以保证所建模型具有较高精度。此外该方法亦不受模型阶次的限制。应用该方法建立某型涡扇发动机的小偏差状态变量模型 ,具有较高的精度 ,从而验证了该方法的有效性。Modeling of small perturbation State Variable Model (SVM) for the design of aeroengines' multivariable robust control system was studied. The small perturbation SVM of an aeroengine was derived directly by fitting its nonlinear simulation data under small perturbation about the steady operating point. The SVM established by this approach has high accuracy since the modeling error is minimized under the meaning of least square. Moreover the approach is not limited by the plant order. The application of the approach to establishing the small perturbation SVM for a turbofan engine shows its effectiveness.

关 键 词：航空发动机 状态变量模型 最小二乘法 鲁棒控制系统 小偏差 

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]