Componentization Modeling And Performance Parameters Estimation Of Aero-engine

This paper is designed to provide componentization model of aero-engine for integrated flight/propulsion control system simulation platform. In this paper, the software componentization ideology is adopted and the COM technology is applied to aero-engine modeling in order to establish a reusable, universal, and high accuracy aero-engine model. On the basis of this model, the aero-engine performance parameter estimation method is researched.Firstly, the aero-engine is divided into ten main components from the perspective of its structure. Mathematics model of every component is established and then every mathematics model is packaged as a COM component. Data transfer among all components, as well as between model and simulation platform, is realized by way of the interfaces. In addition, some components are built to package the important functions.Secondly, the design of the aero-engine simulation platform is carried out, which includes the design of interface and inner function. The interface of the simulation platform is established on the basis of MFC single-document framework. The tree control and drawing technique is adopted to design the component column and the model simulation area. In the inner working system, both Newton-Raphsion method and Broyden quasi-Newton method are introduced for the purpose of solving the dynamic balance equations of the model.In this paper, a method is proposed for aero-engine performance parameters estimation, based on the combination of support vector regression (SVR) and genetic algorithm (GA). As for confirming the reduced set of reduced least squares support vector regression (RLSSVR), genetic algorithm (GA) is used because of its global performance seeking capability to select support vector and compromise the reduced set in order to realize accurate parameters estimation of the aero-engine performance. To verify the practicality of this aero-engine performance parameters estimation method, the ALQR thrust controller is designed and the estimate thrust is used as feedback signal to form a close loop control system. The simulations demonstrate that the thrust estimator can estimate thrust accurately and that the estimate thrust as feedback is applied to the thrust control system, so that the engine can get rapid response and realize smooth transition in the fly envelope.