飞行/推进综合系统集中控制技术及其分离方法研究
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摘要
飞行/推进综合控制是未来先进飞机和发动机控制的发展趋势。本文主要开展了飞行/推进综合系统集中控制技术及其分离方法的研究。
本文首先研究了建立飞机/推进综合系统状态空间模型的拟合法,拟合法所求取的状态空间模型具有很高的精度,为下一步控制系统设计奠定了基础。接着采用ALQR方法设计了基于矢量推力的飞行控制系统,验证了采用矢量推力控制飞机飞行的可行性。然后研究了飞行/推进综合系统集中控制技术,分别采用混合灵敏度H_∞方法和ALQR方法设计了飞行/推进综合系统集中控制器,非线性仿真结果表明均取得了很好的效果。集中控制器的优点是由于考虑了子系统耦合而性能最优,缺点是控制器阶次较高,难以在现有的控制结构上实现,且无法在目前的科研生产管理体制下进行管理。于是本文最后开展了飞行/推进综合系统控制器分离方法的研究,这里“分离”是指,求取几个具有特定交联结构的低阶子控制器来近似原高阶集中控制器,同时保证分离子控制器的闭环性能和集中控制器的闭环性能尽可能一致,这样通过分离,使得集中控制器的闭环性能基本得到保持,而分离子控制器阶次较低也非常便于实现,同时允许独立的子系统控制校验。本文研究了两种控制器分离方法,一种是解析的,另一种是优化的,优化方法以解析的分离子控制器为初始解,求取一组最优的分离子控制器,使其闭环性能更接近于集中控制器的闭环性能。
Integrated Flight/Propulsion Control (IFPC) is the development trend of control system design for advanced aircraft and aero-engine in the future. The centralized control techniques and controller partitioning methods of integrated flight/propulsion system are mainly researched in this paper.
Firstly, the data fitting method of building state space models for integrated aircraft/propulsion system is discussed. The state space models acquired using data fitting method are with high precision and will be appropriate for the control system design in the next step. Subsequently, a control system based on the vectoring thrust is designed using ALQR method and the feasibility of controlling air-craft by vectoring thrust is verified. Then the centralized techniques are studied and two centralized controllers are designed using mixed sensitivity H∞method and ALQR method, respectively. The non-linear simulation results demonstrate that both of them have good performance. The advantage of centralized controller is that it is with optimal performance by considering the coupling of subsystems, but the disadvantage of centralized controller is that it is difficult to implement it on present control structure because of its high-order and can not be managed under the crrent management system of research and production. So the controller partitioning methods are investigated at last in this paper. The meaning of partitioning is to approximate the high-order centralized controller with several lower order subcontrollers with a specified connecting structure, and the closed-loop performance of the centralized controller should be matched by the partitioned subcontrollers at the same time. Thus the closed-loop performance of the centralized controller is basically preserved by partitioning and the partitioned subcontrollers are easier to implement owing to their lower order and independent subsys-tem control validation is allowed. Two methods of controller partitioning are discussed in this paper. One is analytical method and the other is optimization method. A set of optimal partitioned subcon-trollers is obtained using the optimization method with the analytical partitioned subcontrollers as an initial solution and the closed-loop performance of the optimal partitioned subcontrollers is more close to that of the centralized controller.
本文首先研究了建立飞机/推进综合系统状态空间模型的拟合法,拟合法所求取的状态空间模型具有很高的精度,为下一步控制系统设计奠定了基础。接着采用ALQR方法设计了基于矢量推力的飞行控制系统,验证了采用矢量推力控制飞机飞行的可行性。然后研究了飞行/推进综合系统集中控制技术,分别采用混合灵敏度H_∞方法和ALQR方法设计了飞行/推进综合系统集中控制器,非线性仿真结果表明均取得了很好的效果。集中控制器的优点是由于考虑了子系统耦合而性能最优,缺点是控制器阶次较高,难以在现有的控制结构上实现,且无法在目前的科研生产管理体制下进行管理。于是本文最后开展了飞行/推进综合系统控制器分离方法的研究,这里“分离”是指,求取几个具有特定交联结构的低阶子控制器来近似原高阶集中控制器,同时保证分离子控制器的闭环性能和集中控制器的闭环性能尽可能一致,这样通过分离,使得集中控制器的闭环性能基本得到保持,而分离子控制器阶次较低也非常便于实现,同时允许独立的子系统控制校验。本文研究了两种控制器分离方法,一种是解析的,另一种是优化的,优化方法以解析的分离子控制器为初始解,求取一组最优的分离子控制器,使其闭环性能更接近于集中控制器的闭环性能。
Integrated Flight/Propulsion Control (IFPC) is the development trend of control system design for advanced aircraft and aero-engine in the future. The centralized control techniques and controller partitioning methods of integrated flight/propulsion system are mainly researched in this paper.
Firstly, the data fitting method of building state space models for integrated aircraft/propulsion system is discussed. The state space models acquired using data fitting method are with high precision and will be appropriate for the control system design in the next step. Subsequently, a control system based on the vectoring thrust is designed using ALQR method and the feasibility of controlling air-craft by vectoring thrust is verified. Then the centralized techniques are studied and two centralized controllers are designed using mixed sensitivity H∞method and ALQR method, respectively. The non-linear simulation results demonstrate that both of them have good performance. The advantage of centralized controller is that it is with optimal performance by considering the coupling of subsystems, but the disadvantage of centralized controller is that it is difficult to implement it on present control structure because of its high-order and can not be managed under the crrent management system of research and production. So the controller partitioning methods are investigated at last in this paper. The meaning of partitioning is to approximate the high-order centralized controller with several lower order subcontrollers with a specified connecting structure, and the closed-loop performance of the centralized controller should be matched by the partitioned subcontrollers at the same time. Thus the closed-loop performance of the centralized controller is basically preserved by partitioning and the partitioned subcontrollers are easier to implement owing to their lower order and independent subsys-tem control validation is allowed. Two methods of controller partitioning are discussed in this paper. One is analytical method and the other is optimization method. A set of optimal partitioned subcon-trollers is obtained using the optimization method with the analytical partitioned subcontrollers as an initial solution and the closed-loop performance of the optimal partitioned subcontrollers is more close to that of the centralized controller.
引文
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[4]孙健国,V. Vasilyev, B. Hyasov, Advanced Multivariable Control System of Aeroengines(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
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[6]吴森堂,费玉华,飞行控制系统[M],北京,北京航空航天大学出版社,2005.9:358～361
[7]申安玉,申学仁,李云保,自动飞行控制系统[M],北京,国防工业出版社,2003.1:150～161
[8]王玉新,喷气发动机轴对称推力矢量喷管[M],北京,国防工业出版社,2006.3:1～9
[9] F.W. Burcham, Jr. and E.A. Haering, Jr, Highly Integrated Digital Engine Control System On An F-15 Airplane[C], AIAA-84-1295
[10] Yonke, W.A., Terrell, L.A. and Meyer, L.P., Integrated Flight/Propulsion Control[C], AIAA-85-1425
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[24] D.L. Mattern, S. Garg, and R.E. Bullard, Integrated Flight/Propulsion Control System Design Based on a Decentralized, Hierarchical Approach[C], AIAA Paper 89-3519, presented at the AIAA Guidance, Navigation and Control Conference, Boston, MA, August 1989
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[27] S. Garg, Partitioning of Centralized Integrated Flight/Propulsion Control Design for Decentra-lized Implementation[J], IEEE Trans. on Control Systems Technology, Vol. 1, No. 2, pp. 93-100, 1993
[28] S. Garg, and D.L. Mattern, Application of an Integrated Flight/Propulsion Control Design Me-thodology to a STOVL Aircraft[C], presented at the AIAA Guidance Navigation Control Confe-rence, New Orleans, LA, Aug. 1991, AIAA Paper 91-2792
[29] P.H. Schmidt, S. Garg, and B. Holowecky, A Parameter Optimization Approach to Controller Partitioning for Integrated Flight/Propulsion Control Application[J], IEEE Transactions on Con-trol Systems Technology, Vol. 1, No. 1, pp. 21-36,1993
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