直升机/发动机系统综合控制半物理仿真

张海波; 叶飞; 李永进; 陈国强

直升机/发动机系统综合控制半物理仿真

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国人民解放军总参谋部陆航部驻株洲地区军事代表室, 湖南株洲 412002

基金项目: 南京航空航天大学基本科研业务费(NS2013021)

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出版历程
- 收稿日期: 2012-07-15
- 刊出日期: 2013-07-28

Semi-physical simulation on integrated helicopter/engine control system

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Military Representatives' Office in Zhuzhou District of Army Airmen Branch of the Headquarters of General Staff, The Chinese People's Liberation Army, Zhuzhou Hunan 412002, China

摘要

摘要: 基于直升机/发动机系统综合控制半物理仿真试验平台,针对直升机/发动机系统综合模型和综合控制算法进行数字与半物理仿真试验研究.提出了一种串级PID(proportional integration differential)+扭矩前馈+总距补偿的系统抗扰控制算法,并提出了基于机载简化发动机模型的多模式综合实时优化控制算法.试验结果表明:所建立的直升机/发动机系统综合开闭环模型能够模拟发动机从起动到慢车再到直升机飞行的整个过程,自由涡轮转速超调量和下垂量均在4%以内,在不同飞行条件下,动静态品质均满足设计要求.本文还进行了综合系统多模式优化技术的半物理仿真,结果表明所设计综合控制律的良好工程应用前景.
- 直升机/发动机系统综合控制 /
- 半物理仿真试验 /
- 串级PID控制 /
- 扭矩前馈 /
- 总距补偿 /
- 综合系统多模式优化
Abstract: Based on the simulation platform of integrated helicopter/engine system control,semi-physical simulations were carried out for integrated helicopter/engine model and integrated control algorithm.The core part of anti-disturbance control of the integrated system adopted a novel algorithm of cascade proportional integration differential(PID)+torque feed forward+collective compensation,and the optimization control was multi-mode real-time optimization based on the simplified engine adaptive system model.The simulation tests show that the established integrated helicopter/engine model can simulate the engine's total process from start to idling,then to helicopter flying,and the droop and overshoot of the power turbine is within 4% in the whole process.The engine's dynamic and static quality meets the requirements of helicopter flight control in different flight conditions.The semi-physical simulation results of the integrated system multi-mode optimization were validated.The established semi-physical simulation platform of integrated helicopter/engine control system is valuable for engineering applications.
- integrated helicopter/engine system controlx /
- semi-physical simulation test /
- cascade proportional integration differential(PID) control /
- torque feed forward /

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参考文献(15)

[1]	Shanthakumaran P,Harding J,Thompson T,et al.Flight simulation model application for AH-64A Apache engine integration[C]//49th Annual Forum proceedings of AHS.St Louis,US:AHS,1993:261-282.
[2]	Killion S.Flight tests of adaptive fuel control and decoupled rotor speed control systems[C]//49th Annual Forum proceedings of ASH.St Louis,US:ASH,1993:413-419.
[3]	Sturisky S H,Lewis W D,Schrage D P,et al,Development and validation of a comprehensive real time AH-64 Apache simulation model[C]//48th Annual Forum proceeding of AHS.Washington,US:AHS,1992:1267-1280.
[4]	James R M,Mark G B,Ruttledge D C G.Rotorcraft flight-propulsion control integration [R].NASA-TP-2815,1988.
[5]	WEI Guo.Flight control design for rotorcraft with variable rotorspeed [D].Pennsylvania,US:The Pennsylvania State University,2009.
[6]	Stevens M A,Handschuh R F,Lewicki D G.Concepts for variable/multi-speed rotorcraft drive system [R].NASA/TM-215276,2008.
[7]	Smith B J,Zagranski R D.Next generation control syetem for helicopter engines[C]//57th Annual Forum Proceedings of AHS.Washington,US:ASH,2001:401-409.
[8]	Smith B J,Zagranski R D.Closed loop bench testing of the next generation control system for helicopter engines[C]//58th Annual Forum Proceedings of AHS.Montreal,Canada:ASH,2002:1041-1050.
[9]	孙立国.基于直升机/发动机综合仿真的发动机性能优化及控制 [D].南京:南京航空航天大学,2010. SUN Liguo.Optimization and control for a turbo-shaft engine via integrated helicopter and engine system simulation [D].Nanjing:Nanjing University of Aeronautics and Astronautics,2010.(in Chinese)
[10]	张海波,姚文荣,陈国强.涡轴发动机/直升机综合控制仿真平台设计[J].推进技术,2011,6(3):383-390. ZHANG Haibo,YAO Wenrong,CHEN Guoqiang.Design of an integrated turbo-shaft engine/helicopter control simulation platform[J].Journal of Propulsion Technology,2011,6(3):383-390.(in Chinese)
[11]	Howlett J J.UH- 60A Black Hawk engineering simulation program:Volume 1 mathematical model [R].NASA 166309,1981.
[12]	Hilbert K B.A mathematical model of UH-60 helicopter.NASA-TM-85890,1984.
[13]	张海波,孙健国.自抗扰控制算法在发动机加力过渡态控制中的应用[J].推进技术,2010,31(2):219-225. ZHANG Haibo,SUN Jianguo.Application of active disturbance rejection control method in aero-engines afterburning transition state control[J].Journal of Propulsion Technology,2010,31(2):219-225.(in Chinese)
[14]	Lawrence C T,Tits A L.A computational efficient feasible seaquential quadratic programming algorithm[J].Journal on Optimization,2001,11(4):1092-1118.
[15]	张海波,孙健国,王健康.信赖域滤子算法在航空发动机在线优化中的应用[J].航空动力学报,2010,25(3):659-666. ZHANG Haibo,SUN Jianguo,WANG Jiankang.Application of trust region filter algorithm to aero-engine online optimization[J].Journal of Aerospace Power,2010,25(3):659-666.(in Chinese)