飞/推综合系统建模与控制研究
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摘要
飞/推综合控制技术是满足飞机先进性能要求的新一代战斗机关键技术。它把飞机和推进系统作为一个整体对象来研究,充分考虑飞机和推进系统之间的耦合作用,并通过性能优化提高推进系统潜力和协调飞行控制系统和推进控制系统等措施来改善飞机的飞行性能,从而使整个系统达到整体性能最优。
本文主要围绕着飞推综合控制器设计和飞推综合优化控制两个方面进行研究的,按其内容包括以下三部分:
首先建立飞推综合实时仿真模型。建立了飞机六自由度仿真模型,在原有发动机模型基础上,进行了风扇及压气机可调导叶建模工作,完善了航空发动机非线性部件级模型,然后将飞机模型和发动机模型按照飞机和发动机之间的耦合关系组合成飞/推综合模型,并对飞/推综合模型进行了稳态配平和动态仿真计算验证。
其次设计飞/推综合控制规律。按照飞/推综合控制系统设计思路分别采用ADRC解耦方法和ALQR方法进行设计飞/推综合控制规律,并进行了仿真验证;其中在发动机控制系统设计时,提出了应用最小二乘方法对控制规律进行包线分区的方法解决按控制计划燃油低选问题。
最后分别应用LP与SQP两种实时优化算法进行飞推综合优化控制研究。阐述了最南推力优化模式、最小油耗优化模式的优化机理及算法实现,结合飞推综合优化控制的整体设计方案,采用LP与SQP算法对以上两种优化模式进行了数字仿真,并进行了两者的性能与优化结果等方面的对比,结果表明,SQP优化方案在实时性、优化效果方面具有明显的优势。然后基于SQP实时在线优化方案,进行了飞机爬升和平飞加速任务下最南推力优化模式和飞机巡航任务下最小油耗优化模式的数学仿真验证。
Integrated Flight/Propulsion control technology which used to meet the performance requirements for advanced aircraft design is one of the key technologies of a new generation fighter.It takes the aircraft and propulsion system as a whole object to study and deal with coupling effects between them. The aircraft’s closed-loop control system would turn out to be an much better integrated flight system by improving the performance of propulsion system or taking other measures to coordinate the flight control system and propulsion control system.
In this paper, Integrated Flight/Propulsion System’s Controller design and optimization control are studied; According to this dissertation’s contents, three parts are as follows:
First of all, the real-time model of aircraft is established for Integrated Flight/Propulsion system’s simulation. the aircraft model with six degrees of freedom is established; based on the original engine nonlinear component level model, the fan and compressor model are constructed of which the guiding vane can be adjusted, then the nonlinear component level model are better realized; according to the coupling relationship between the two models, the Plane model and the engine model are combined into the Integrated Flight/Propulsion model,and then Steady-state trimming and dynamic simulated calculation verifications are carried out for the Integrated Flight/Propulsion system’s model .
Secondly,An Integrated Flight/Propulsion Controller is designed. As the design thread of Flight/Propulsion control system, ADRC decoupling method and ALQR method are respectively applied to design the Integrated Flight/Propulsion Controller, and simulation verifications are also carried out; In addition, a least square method to divide the flight envelope for some engine’s intermediate state control is proposed to solve low fuel selection principle.
Finally Integrated Flight/Propulsion optimization control is studied in the use of SQP optimization algorithm and LP optimization algorithm. Mechanism and algorithm realization of maximum thrust optimization mode and minimum fuel consumption optimization mode are elaborated; simulation verifications are carried out in consideration of the design scheme of flight/propulsion optimization control of maximum thrust optimization mode in accelerating and climbing mission and minimum fuel consumption optimization mode in cruise mission.
本文主要围绕着飞推综合控制器设计和飞推综合优化控制两个方面进行研究的,按其内容包括以下三部分:
首先建立飞推综合实时仿真模型。建立了飞机六自由度仿真模型,在原有发动机模型基础上,进行了风扇及压气机可调导叶建模工作,完善了航空发动机非线性部件级模型,然后将飞机模型和发动机模型按照飞机和发动机之间的耦合关系组合成飞/推综合模型,并对飞/推综合模型进行了稳态配平和动态仿真计算验证。
其次设计飞/推综合控制规律。按照飞/推综合控制系统设计思路分别采用ADRC解耦方法和ALQR方法进行设计飞/推综合控制规律,并进行了仿真验证;其中在发动机控制系统设计时,提出了应用最小二乘方法对控制规律进行包线分区的方法解决按控制计划燃油低选问题。
最后分别应用LP与SQP两种实时优化算法进行飞推综合优化控制研究。阐述了最南推力优化模式、最小油耗优化模式的优化机理及算法实现,结合飞推综合优化控制的整体设计方案,采用LP与SQP算法对以上两种优化模式进行了数字仿真,并进行了两者的性能与优化结果等方面的对比,结果表明,SQP优化方案在实时性、优化效果方面具有明显的优势。然后基于SQP实时在线优化方案,进行了飞机爬升和平飞加速任务下最南推力优化模式和飞机巡航任务下最小油耗优化模式的数学仿真验证。
Integrated Flight/Propulsion control technology which used to meet the performance requirements for advanced aircraft design is one of the key technologies of a new generation fighter.It takes the aircraft and propulsion system as a whole object to study and deal with coupling effects between them. The aircraft’s closed-loop control system would turn out to be an much better integrated flight system by improving the performance of propulsion system or taking other measures to coordinate the flight control system and propulsion control system.
In this paper, Integrated Flight/Propulsion System’s Controller design and optimization control are studied; According to this dissertation’s contents, three parts are as follows:
First of all, the real-time model of aircraft is established for Integrated Flight/Propulsion system’s simulation. the aircraft model with six degrees of freedom is established; based on the original engine nonlinear component level model, the fan and compressor model are constructed of which the guiding vane can be adjusted, then the nonlinear component level model are better realized; according to the coupling relationship between the two models, the Plane model and the engine model are combined into the Integrated Flight/Propulsion model,and then Steady-state trimming and dynamic simulated calculation verifications are carried out for the Integrated Flight/Propulsion system’s model .
Secondly,An Integrated Flight/Propulsion Controller is designed. As the design thread of Flight/Propulsion control system, ADRC decoupling method and ALQR method are respectively applied to design the Integrated Flight/Propulsion Controller, and simulation verifications are also carried out; In addition, a least square method to divide the flight envelope for some engine’s intermediate state control is proposed to solve low fuel selection principle.
Finally Integrated Flight/Propulsion optimization control is studied in the use of SQP optimization algorithm and LP optimization algorithm. Mechanism and algorithm realization of maximum thrust optimization mode and minimum fuel consumption optimization mode are elaborated; simulation verifications are carried out in consideration of the design scheme of flight/propulsion optimization control of maximum thrust optimization mode in accelerating and climbing mission and minimum fuel consumption optimization mode in cruise mission.
引文
[1]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],北南,北南航空航南南学出版社,2005
[2]樊思齐,徐芸华,航空推进系统控制[M],西安,西北工业南学出版社,1995.12
[3]申安玉,申学仁,李云保,自动飞行控制系统[M],北南,国防工业出版社,2003.1
[4]郭锁凤,申功璋,吴成富,先进飞行控制系统[M],北南,国防工业出版社,2003.3
[5]吴森堂,费玉华,飞行控制系统[M],北南,北南航空航南南学出版社,2005.9
[6] Sun Jianguo;V.Vasilyev;B.Ilyasov.Advanced multivariable control systems of aeroengines.北南:北南航空航南南学出版社,2005
[7]黄春风.航空智能发动机的研究发展.中国航空学会,南型飞机关键技术高层论坛暨中国航空学会2007年学术年会论文集,北南:中国航空学会, 2007: 1-14.
[8] F.W.Burcham,Jr.and E.A.Haering,Jr,Highly Integrated Digital Engine Control System On An F-15 Airplane[C],AIAA-84-1295
[9] G.J.Simpkin.An overview of aircraft integrated control technology[C].AIAA-94-9
[10] Kenneth L.Smith, W.Bernie Kerr and Gary L.Hartmann, Aircraft Control Integration Methodology and Performance Impact[C], AIAA-85-1424
[11] Peter D.Shaw, Karl R.Haiges and Charles A.Skira, Validation of An Integrated Flight and Propulsion Control Design for Fighter Aircraft[C], AIAA-87-1928
[12] J.Orme and G.Gilyard, Preliminary Supersonic Flight Test Evaluation of Performance Seeking Control[C], AIAA-92-3743
[13] Lambert, H.H., Gilyard, G.B., Chisholm, J.D., Lousis, S.M., and L.J. Kerr, Preliminary Flight Evaluation of An Engine Performance Optimization Algorithm[C], AIAA-91-1998
[14] Smith, R.H., Chisholm, J.D.and J.F. Stewart, Optimizing Aircraft Performance with Adaptive Integrated Flight/Propulsion Control[J], Journal of Engineering for Gas Turbines and Power, 1991.11, Vol.113, pp.847-94
[15]申功章,陈宗基,彭可茂.综合飞行/推进系统的特征值灵敏分析和设计.航空学报,1989,6
[16]陈恒,张玉琢,马瑞.飞行/推进综合控制系统设计与仿真.计算机仿真,2001,9
[17]李彦双,飞行/推进综合系统集中控制技术及其分离方法研究[D],南南航空航南南学硕士学位论文,2009.1
[18] Yonke W.A.,Landy R.J., HIDEC Adaptive Engine Control System Flight Evaluation Result[J], ASME 87-Gt-252
[19] R.J. Landy,W.A.Yonke,J.F. Stewart, Development of HIDEC Adaptive Engine Control Systems[J],SAE-86-GT-252
[20] F.W.Burcham Jr.,E.A. Haering, Highly Integrated Digital Engine Control System on An F-15 Airplane[J], AIAA-84-1259
[21]孙丰诚,孙健国,基于序列二次规划算法的发动机性能寻优控制[J],航空动力学报,2005,20(5):862～867
[22]李松林,飞行/推进系统综合控制-性能寻优自适应控制研究[D],[博士学位论文],南南,南南航空航南南学,1998.6
[23]单贵平,航空发动机建模与推力矢量控制研究[D],南南航空航南南学硕士学位论文,2007.1
[24]蒋达福,孙健国,张海波.带矢量喷管发动机建模与短距起飞控制研究.南南航空航南南学硕士学位论文,2009.1
[25]陈小奇.飞行仿真技术.吉林科学技术出版社.2004.9
[26]王曦,林永霖,吴永康, H∞控制在飞行/推进综合控制系统中的应用[J],航空动力学报,2004,19(5):698-702
[27]何信鉴,何兵,竹东翔,LQG/LTR法在综合飞行/推进控制系统中的应用[J],西北工业南学学报,1996,Vol. 14, No. 1:1-5
[28] Masami, S. H∞/LTR procedure with specified degree of recovery. Automatica, Vol. 28, No. 3,1992, pages: 509-517
[29] Sanjay Garg and Peter J.Ouzts, Integrated Flight/Propulsion Control Design for a STOVL Aircraft Using H-Infinity Control Design Techniques[C], NASA Technical Memorandum 104340, American Control Conference, Boston, Massachusettes, June 26-28, 1991
[30]韩南清,自抗扰控制器及其应用[J].控制与决策,1998,13(1):19-23
[31]韩南清,自抗扰控制技术.前沿科学.2007,1.
[32]韩南清,从PID技术到“自抗扰控制”技术.控制工程.2002,5.
[33]韩南清,金奎焕.自抗扰算法在聚丙烯反应釜过程控制中的应用.计算技术与自动化,2003,22(2):43-45.
[34]陈忻彦,黄一,韩南清,等。基于自抗扰控制思想的动力调谐陀螺力平衡回路控制的实验研究.中国控制会议论文集。武汉:武汉理工南学出版社. 2003:283-286.
[35]张海波,孙立国,孙健国.直升机/涡轴发动机综合系统鲁棒抗扰控制设计.航空学报,2010,31(5):883-892.
[36] Qing Zheng; Lili Dong; A Disturbance Rejection Based Control System Design for Z-Axis Vibratory Rate Gyroscopes ICCA 2007. IEEE International Conference on Control and Automation,May 30 2007-June 1 2007 Page(s):2105 - 2110
[37]李壮举,刘贺平,王健安。基于ESO的动态解耦方法及其应用仿真.计算机应用研究.Vol.26.No.11.Nov.2009.
[38]杨刚,孙键国,李秋红.航空发动机控制系统中的增广LQR方法,航空动力学报, 2004,19(1):153-158.
[39] S. Garg, D.L. Mattern, and R.E. Bullard, Integrated Flight/Propulsion Control System Design Based on a Centralized Approach[C], AIAA Paper 89-3520, presented at the AIAA Guidance, Navigation and Control Conference, Boston, MA, August 1989.
[40] K.L. Smith, Design Methods for Integrated Control Systems[J], Wright Patterson AFB, OH, Rep. AFWAL-TR-86-2103, Dec. 1986.
[41] 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.
[42] Ian Postlethwaite and Declan G. Bates, Integrated Flight and Propulsion Control System Design, via H∞Loop Shaping and Partitioning[C], AIAA Paper, AIAA-98-4295
[43] Sarah L. Gately, Declan G. Bates and Ian Postlethwaite, Partitioning and Re-design of H∞Loopshaping Integrated Flight and Propulsion Control Systems[C], AIAA Paper AIAA 2001-4384, AIAA Guidance, Navigation, and Control Conference and Exhibit, 6-9 August 2001, Montreal, Canada
[44]王前宇,孙健国,基于控制结构优化的航空发动机多变量鲁棒控制研究.南南航空航南南学硕士学位论文,20010.1
[45]杨刚.多变量鲁棒控制在涡扇发动机中的应用研究与实验验证, [博士学位论文].南南:南南航空航南南学, 2004.
[46] S.G. Nobbs,S.W.Jacobs, D.J. Donahue, Development of the Full-Envelope Performance Seeking Control Algorithm,AIAA-92-3748
[47] Martin D. Eapana, On the Estimation Algorithm for Adaptive Performance Optimization of Turbofan Engines, AIAA-93-1823
[48] T. Conners, Thrust Stand Evaluation of Engine Performance Improvement Algorithms in an F-15 Airplane, AIAA-92-3747
[49]姚文荣,涡轴发动机/旋翼综合建模、控制及优化研究[D],南南:南南航空航南南学博士论文,2008
[50]王健康,孙健国.基于机载复合模型及SQP的发动机性能寻优控制研究.南南航空航南南学硕士学位论文,20010.1
[51]孙丰诚,航空发动机性能寻优控制控制技术研究[D],[博士学位论文],南南,南南航空航南南学,2007.6
[2]樊思齐,徐芸华,航空推进系统控制[M],西安,西北工业南学出版社,1995.12
[3]申安玉,申学仁,李云保,自动飞行控制系统[M],北南,国防工业出版社,2003.1
[4]郭锁凤,申功璋,吴成富,先进飞行控制系统[M],北南,国防工业出版社,2003.3
[5]吴森堂,费玉华,飞行控制系统[M],北南,北南航空航南南学出版社,2005.9
[6] Sun Jianguo;V.Vasilyev;B.Ilyasov.Advanced multivariable control systems of aeroengines.北南:北南航空航南南学出版社,2005
[7]黄春风.航空智能发动机的研究发展.中国航空学会,南型飞机关键技术高层论坛暨中国航空学会2007年学术年会论文集,北南:中国航空学会, 2007: 1-14.
[8] F.W.Burcham,Jr.and E.A.Haering,Jr,Highly Integrated Digital Engine Control System On An F-15 Airplane[C],AIAA-84-1295
[9] G.J.Simpkin.An overview of aircraft integrated control technology[C].AIAA-94-9
[10] Kenneth L.Smith, W.Bernie Kerr and Gary L.Hartmann, Aircraft Control Integration Methodology and Performance Impact[C], AIAA-85-1424
[11] Peter D.Shaw, Karl R.Haiges and Charles A.Skira, Validation of An Integrated Flight and Propulsion Control Design for Fighter Aircraft[C], AIAA-87-1928
[12] J.Orme and G.Gilyard, Preliminary Supersonic Flight Test Evaluation of Performance Seeking Control[C], AIAA-92-3743
[13] Lambert, H.H., Gilyard, G.B., Chisholm, J.D., Lousis, S.M., and L.J. Kerr, Preliminary Flight Evaluation of An Engine Performance Optimization Algorithm[C], AIAA-91-1998
[14] Smith, R.H., Chisholm, J.D.and J.F. Stewart, Optimizing Aircraft Performance with Adaptive Integrated Flight/Propulsion Control[J], Journal of Engineering for Gas Turbines and Power, 1991.11, Vol.113, pp.847-94
[15]申功章,陈宗基,彭可茂.综合飞行/推进系统的特征值灵敏分析和设计.航空学报,1989,6
[16]陈恒,张玉琢,马瑞.飞行/推进综合控制系统设计与仿真.计算机仿真,2001,9
[17]李彦双,飞行/推进综合系统集中控制技术及其分离方法研究[D],南南航空航南南学硕士学位论文,2009.1
[18] Yonke W.A.,Landy R.J., HIDEC Adaptive Engine Control System Flight Evaluation Result[J], ASME 87-Gt-252
[19] R.J. Landy,W.A.Yonke,J.F. Stewart, Development of HIDEC Adaptive Engine Control Systems[J],SAE-86-GT-252
[20] F.W.Burcham Jr.,E.A. Haering, Highly Integrated Digital Engine Control System on An F-15 Airplane[J], AIAA-84-1259
[21]孙丰诚,孙健国,基于序列二次规划算法的发动机性能寻优控制[J],航空动力学报,2005,20(5):862～867
[22]李松林,飞行/推进系统综合控制-性能寻优自适应控制研究[D],[博士学位论文],南南,南南航空航南南学,1998.6
[23]单贵平,航空发动机建模与推力矢量控制研究[D],南南航空航南南学硕士学位论文,2007.1
[24]蒋达福,孙健国,张海波.带矢量喷管发动机建模与短距起飞控制研究.南南航空航南南学硕士学位论文,2009.1
[25]陈小奇.飞行仿真技术.吉林科学技术出版社.2004.9
[26]王曦,林永霖,吴永康, H∞控制在飞行/推进综合控制系统中的应用[J],航空动力学报,2004,19(5):698-702
[27]何信鉴,何兵,竹东翔,LQG/LTR法在综合飞行/推进控制系统中的应用[J],西北工业南学学报,1996,Vol. 14, No. 1:1-5
[28] Masami, S. H∞/LTR procedure with specified degree of recovery. Automatica, Vol. 28, No. 3,1992, pages: 509-517
[29] Sanjay Garg and Peter J.Ouzts, Integrated Flight/Propulsion Control Design for a STOVL Aircraft Using H-Infinity Control Design Techniques[C], NASA Technical Memorandum 104340, American Control Conference, Boston, Massachusettes, June 26-28, 1991
[30]韩南清,自抗扰控制器及其应用[J].控制与决策,1998,13(1):19-23
[31]韩南清,自抗扰控制技术.前沿科学.2007,1.
[32]韩南清,从PID技术到“自抗扰控制”技术.控制工程.2002,5.
[33]韩南清,金奎焕.自抗扰算法在聚丙烯反应釜过程控制中的应用.计算技术与自动化,2003,22(2):43-45.
[34]陈忻彦,黄一,韩南清,等。基于自抗扰控制思想的动力调谐陀螺力平衡回路控制的实验研究.中国控制会议论文集。武汉:武汉理工南学出版社. 2003:283-286.
[35]张海波,孙立国,孙健国.直升机/涡轴发动机综合系统鲁棒抗扰控制设计.航空学报,2010,31(5):883-892.
[36] Qing Zheng; Lili Dong; A Disturbance Rejection Based Control System Design for Z-Axis Vibratory Rate Gyroscopes ICCA 2007. IEEE International Conference on Control and Automation,May 30 2007-June 1 2007 Page(s):2105 - 2110
[37]李壮举,刘贺平,王健安。基于ESO的动态解耦方法及其应用仿真.计算机应用研究.Vol.26.No.11.Nov.2009.
[38]杨刚,孙键国,李秋红.航空发动机控制系统中的增广LQR方法,航空动力学报, 2004,19(1):153-158.
[39] S. Garg, D.L. Mattern, and R.E. Bullard, Integrated Flight/Propulsion Control System Design Based on a Centralized Approach[C], AIAA Paper 89-3520, presented at the AIAA Guidance, Navigation and Control Conference, Boston, MA, August 1989.
[40] K.L. Smith, Design Methods for Integrated Control Systems[J], Wright Patterson AFB, OH, Rep. AFWAL-TR-86-2103, Dec. 1986.
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