航空发动机组件化建模及性能参数估计
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摘要
本文是为飞/推综合控制系统仿真平台提供航空发动机组件化模型。旨在利用软件组件化的思想,将COM组件技术应用到航空发动机建模中,建立一个可重用、通用性强以及精度高的组件化模型,并在此模型基础之上,研究航空发动机性能参数估计的方法。
首先将航空发动机按照结构划分为10个主要部件,分别建立各部件的数学模型并将其封装成COM组件。各组件之间以及与模型与仿真平台之间的数据传递通过接口实现。此外,还创建了航空发动机的一些功能组件,用于封装功能函数等。
其次,进行航空发动机仿真平台的设计,包括界面设计和内部运行管理系统设计。仿真平台的界面是在MFC单文档框架的基础上创建的,利用树形控件和绘图技术等设计了组件栏和模型仿真区;在内部运行管理系统中,提供了牛顿-拉夫森法和Broyden秩1拟牛顿法解模型动态方程。
本文还提出了将支持向量回归机与遗传算法相结合进行航空发动机参数估计的方法。针对简约最小二乘支持向量回归机的简约集确定问题,利用遗传算法具有很好的全局寻优能力来选择支持向量,构成简约集,以实现对航空发动机参数的准确估计。为了验证此估计方法的实用性,论文还设计了ALQR推力控制器,以推力估计器的推力估计值为反馈量,形成闭环控制系统。仿真结果表明,所设计的推力估计器能准确对推力进行估计,将其作为反馈用于直接推力控制系统,实现了发动机在飞行包线内的快速响应和平稳过渡。
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.
首先将航空发动机按照结构划分为10个主要部件,分别建立各部件的数学模型并将其封装成COM组件。各组件之间以及与模型与仿真平台之间的数据传递通过接口实现。此外,还创建了航空发动机的一些功能组件,用于封装功能函数等。
其次,进行航空发动机仿真平台的设计,包括界面设计和内部运行管理系统设计。仿真平台的界面是在MFC单文档框架的基础上创建的,利用树形控件和绘图技术等设计了组件栏和模型仿真区;在内部运行管理系统中,提供了牛顿-拉夫森法和Broyden秩1拟牛顿法解模型动态方程。
本文还提出了将支持向量回归机与遗传算法相结合进行航空发动机参数估计的方法。针对简约最小二乘支持向量回归机的简约集确定问题,利用遗传算法具有很好的全局寻优能力来选择支持向量,构成简约集,以实现对航空发动机参数的准确估计。为了验证此估计方法的实用性,论文还设计了ALQR推力控制器,以推力估计器的推力估计值为反馈量,形成闭环控制系统。仿真结果表明,所设计的推力估计器能准确对推力进行估计,将其作为反馈用于直接推力控制系统,实现了发动机在飞行包线内的快速响应和平稳过渡。
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.
引文
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[2]周文祥.航空发动机及控制系统建模与面向对象的仿真研究. [博士学位论文].南京:南京航空航天大学2006年9月.
[3] C. A. Skira, M. Agnello. Control system for the next century’s fighter engines. Transactions of the ASME Journal of Engineering for Gas Turbines and Power, 1992, 114(4): 749-754.
[4] Koop W. The integrated high performance turbine engine technology program. ISABE 97-7175, 1997.
[5] W. Troha, K. Kerner, G. Butler. Development status of the U.S. army small heavy fuel engine (SHFE) VAATE program. AHS International 63rd Annual Forum - Proceedings - Riding the Wave of New Vertical Flight Technology, United States: American Helicopter Society.
[6]方昌德.航空发动机的发展前景.航空发动机, 2004, 30(1): 1-5.
[7] John Lytle, Greg Follen, Cynthia Naiman, et al. NPSS: Numerical Propulsion System Simulation, 1999 Industry Review. NASA TM-2000-209795. October 6-7, 1999.
[8] John Lytle, Greg Follen, Cynthia Naiman, et al. NPSS: Numerical Propulsion System Simulation Review. NASA CP-2001-210673. October 4-5, 2000.
[9] John Lytle, Greg Follen, Cynthia Naiman, et al. 2001 Numerical Propulsion System Simulation Review. NASA TM-2002-211197. November 7-8, 2001.
[10] Evans A L, Follen G, Naiman C, et al. Numerical Propulsion System Simulation's National Cycle Program. AIAA-98-3113.
[11] Scott M. Jones. An Introduction to Thermodynamic Performance Analysis of Aircraft Gas Turbine Engine Cycles Using the Numerical Propulsion System Simulation Code. NASA/TM-2007-214690, March 2007.
[12]刘大响.对加快发展我国航空动力的思考.航空动力学报,2001,16(1):1-7.
[13]金捷.美国推进系统数值仿真(NPSS)计划综述.燃气涡轮试验与研究,2003,16(1),57-62.
[14]曹源,金先龙,孟光.航空发动机系统级仿真研究的回顾与展望.航空动力学报,2004,4(19),562-571.
[15] McKinney John S. Simulation of Turbofan Engine Part I: Description of Method and Balancing Technique. AFAPL-TR-67-125-pt.-1, Air Force Aero Propulsion Lab, 1967.
[16] Koeig R W, Fisbbacb L H. GENENG-A Program for Calculating Design and Off-Design Performance for Turbojet and Turbofan Engines. NASA TN D-6552, Feb.1972.
[17] Fisbbacb L H, Koenig R W. GENENG II-A Program for Calculating Design and Off-Design Performance of Two and Three-Spool Turbofans with as many as Three Nozzles. NASA TN D-6553, Feb. 1972.
[18] Reed J.A. and Afjeh A A. Development of an Interactive Graphical Propulsion System Simulator. AIAA paper 94-3216, 30th AIAA/ASE/SAE/ASEE Joint Propulsion Conference, Indianapolis IN, June, 1994.
[19] Reed J A and Afjeh A A. An Interactive Graphical Simulation Environment for the Study of Gas Turbine Operation. AIAA paper 96-0119, 32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Lake Buena Vista, FL, July 1996.
[20] Reed J A and Afjeh A A. Computational simulation of gas turbine: Part I-foundation of component-based models. ASME 99-GT-346, June 1999.
[21] Reed J A and Afjeh A A. Computational simulation of gas turbine: Part II-Extensible domain framework. AMSE 99-GT-347, June 1999.
[22] Reed J A , Follen G J and Afjeh A A. Improving the Aircraft Design Process using Web-based Modeling and simulation. ACM Transactions an Modeling and Computer Simulation, Vol. 10,No. 1, 2000:58~83.
[23] N. D. Semkin, A. V. Piyakov, K. E. Voronov, et al. A linear accelerator for simulating micrometeorites. Instruments and Experimental Techniques, March-April 2007: 75-81.
[24] Goryunov. Automation of design and production of aeronautical equipment: Calculation of moisture content influence on parameters of working bodies and processes in the DVIGwT system. Russian Aeronautics. 2006(v49): 83-88.
[25] Kurzke J. GasTurb9: A Program to Calculate Design and Off-Design Performance of Gas Turbines. User’s Manual. Avaluable from Http://www.gasturb.de. 2001.
[26] Peter Jeschke, Joachim Kurzke, Preliminary Gas Turbine Design Using the Multidisciplinary Design System Mopeds. Journal of Engineering for Gas Turbines and Power, 2002,124(3): 465~479.
[27] Visser W P J and Broomhead M J. GSP: A generic object-oriented gas turbine simulation environment. NLR-TP-2000-267. July 2000.
[28] Visser W P J, Broomhead M J and Vorst J V D. TERTS, a generic real-time gas turbine simulation environment. NLR-TP-2002-069.Feb.2002.
[29] Antonio Alejandro. Modeling of a Gas Turbine with Modelica TM. [Master thesis]. Department of Automatic Control, Lund Institute of Technology, Sweden, May 2001.
[30] Ailer P, Santa I, Szederkenyi G et al. Nonlinear Model-Building of a Low-Power Gas Turbine. Periodica Polytechnica Ser. Transp. Eng. 2001,v(29):117-135.
[31]华清.某型涡扇发动机全包线实时仿真模型.航空发动机,2002,vol:47-52.
[32]曹源,金先龙,孟光.航空发动机的非线性模块化建模与仿真.计算机辅助设计与图形学学报,Vol.17 No.3,Mar.2005:507～510.
[33]徐鲁兵,潘宏亮,周鹏.基于面向对象技术的航空发动机性能仿真框架设计.测控技术,2007年第26卷第4期:83～86.
[34]周文祥,黄金泉,窦建平等.面向对象的涡扇发动机及控制系统仿真平台.航空动力学报,Vol.22 No.1, Jan.2007:119～125.
[35]刘永文.模块化建模与半物理仿真研究及其在舰船动力装置中的应用. [博士学位论文],上海:上海交通大学,2002.
[36]李中群.系统仿真及其在航空发动机仿真平台设计中的应用研究. [硕士学位论文],西安:西北工业大学,2004.
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