The real-time capability of integrated flight/propulsion optimal control （IFPOC） is studied. An appli- cation is proposed for IFPOC by combining the onboard hybrid aero-engine model with sequential quadratic pro- gr...The real-time capability of integrated flight/propulsion optimal control （IFPOC） is studied. An appli- cation is proposed for IFPOC by combining the onboard hybrid aero-engine model with sequential quadratic pro- gramming （SQP）. Firstly, a steady-state hybrid aero-engine model is designed in the whole flight envelope with a dramatic enhancement of real-time capability. Secondly, the aero-engine performance seeking control including the maximum thrust mode and the minimum fuel-consumption mode is performed by SQP. Finally, digital simu- lations for cruise and accelerating flight are carried out. Results show that the proposed method improves real- time capability considerably with satisfactory effectiveness of optimization.展开更多
The landing task of an aircraft under low aerodynamic pressure on carrier requires precise airplane control,A flight/thrust integrated control system(FTICS)with constant ad,actual angle of attack,is developed using LM...The landing task of an aircraft under low aerodynamic pressure on carrier requires precise airplane control,A flight/thrust integrated control system(FTICS)with constant ad,actual angle of attack,is developed using LMI-based H∞synthesis.The typical single input/outputspecifications are translated into the weighting functions of an H∞output-feedback synthesis problem.The motiva-tion of the work is to improve the key performance of dy-namic tracking and air disturbance attenuation.The FTICS can keep the attitude andgle and the path angle un-changeable as the airplane is passing through the ramp at which the tracking radar doesnot work and the guidance signal is terminated.For engineering application,an or-der-reduction method of the H∞controller is also pro-posed,Simulational results indicate that the system satis-fies the design requirements quite well.展开更多
In this paper, sensitivity approaches are taken to analyze and design an integrated flight propulsion control system where the interaction between subsystems direitly affects the stability property and handling perfor...In this paper, sensitivity approaches are taken to analyze and design an integrated flight propulsion control system where the interaction between subsystems direitly affects the stability property and handling performances of the aircraft. The eigenvalue sen sitivity approach is employed to study the effect of coupling parameters on system stability and gain sensitivity approach is used to direct the reduced states feedback suboptimal control system design. Simulation results show that the integrated flight propulsion control system designed by sensitivity approaches is of good performance.展开更多
Hypersonic vehicles(HSVs)exhibit significant advantages over other vehicles,including the wide range of velocity and large airspace types,and these features have contributed to the rapid development of HSVs in the las...Hypersonic vehicles(HSVs)exhibit significant advantages over other vehicles,including the wide range of velocity and large airspace types,and these features have contributed to the rapid development of HSVs in the last 20 years.Moreover,hypersonic technologies have become a multidisciplinary research topic in the fields of aerodynamics,propulsion,structure,material,and control.Different types of re-entry gliding,air-breathing cruise,and aerospace vehicles have been designed to realize ambitious tasks,which in turn influenced the technological advancements and process change in the military.This paper summarizes the control-oriented integrated design of HSVs.First,the status of current research on the distinct characteristics and technique issues of HSVs is introduced.Then,the progresses made on complex modeling,guidance and control,and trajectory optimization are elaborated to exhibit the significant research interest in hypersonic technologies.The control-integrated design of HSVs is emphasized to solve the multidisciplinary design problems associated with the model and its control and trajectory.Various strategies regarding the multidisciplinary optimization design are also proposed to solve the integrated design problem.Finally,suggestions are provided for the control-oriented integrated design of HSVs.展开更多
针对当前飞行训练模拟器中航电系统显控逻辑仿真软件开发困难、可维护性差的问题,提出一种将显控逻辑判断与显示画面仿真独立设计的模块化、松耦合的显控系统功能仿真思路。根据显控系统交互式、多输入多输出的时序逻辑决策特点,基于有...针对当前飞行训练模拟器中航电系统显控逻辑仿真软件开发困难、可维护性差的问题,提出一种将显控逻辑判断与显示画面仿真独立设计的模块化、松耦合的显控系统功能仿真思路。根据显控系统交互式、多输入多输出的时序逻辑决策特点,基于有限状态机(finite state machine,FSM)理论构建显控逻辑仿真模块,并应用Simulink/Stateflow进行实现。结果表明:该设计思路结构合理,开发过程直观,程序可维护性、可移植性强,有利于提高显控逻辑仿真度和开发效率。展开更多
基金Supported by the Aeronautical Science Foundation of China(2010ZB52011)the Funding of Jiangsu Innovation Program for Graduate Education(CXLX11-0213)the Nanjing University of Aeronautics and Astronautics Research Funding(NS2010055)~~
文摘The real-time capability of integrated flight/propulsion optimal control （IFPOC） is studied. An appli- cation is proposed for IFPOC by combining the onboard hybrid aero-engine model with sequential quadratic pro- gramming （SQP）. Firstly, a steady-state hybrid aero-engine model is designed in the whole flight envelope with a dramatic enhancement of real-time capability. Secondly, the aero-engine performance seeking control including the maximum thrust mode and the minimum fuel-consumption mode is performed by SQP. Finally, digital simu- lations for cruise and accelerating flight are carried out. Results show that the proposed method improves real- time capability considerably with satisfactory effectiveness of optimization.
文摘The landing task of an aircraft under low aerodynamic pressure on carrier requires precise airplane control,A flight/thrust integrated control system(FTICS)with constant ad,actual angle of attack,is developed using LMI-based H∞synthesis.The typical single input/outputspecifications are translated into the weighting functions of an H∞output-feedback synthesis problem.The motiva-tion of the work is to improve the key performance of dy-namic tracking and air disturbance attenuation.The FTICS can keep the attitude andgle and the path angle un-changeable as the airplane is passing through the ramp at which the tracking radar doesnot work and the guidance signal is terminated.For engineering application,an or-der-reduction method of the H∞controller is also pro-posed,Simulational results indicate that the system satis-fies the design requirements quite well.
文摘In this paper, sensitivity approaches are taken to analyze and design an integrated flight propulsion control system where the interaction between subsystems direitly affects the stability property and handling performances of the aircraft. The eigenvalue sen sitivity approach is employed to study the effect of coupling parameters on system stability and gain sensitivity approach is used to direct the reduced states feedback suboptimal control system design. Simulation results show that the integrated flight propulsion control system designed by sensitivity approaches is of good performance.
基金Aerospace Science and Technology Innovation Fund(CASC2016)Six Talent Peaks Project in Jiangsu Province(KTHY-025).
文摘Hypersonic vehicles(HSVs)exhibit significant advantages over other vehicles,including the wide range of velocity and large airspace types,and these features have contributed to the rapid development of HSVs in the last 20 years.Moreover,hypersonic technologies have become a multidisciplinary research topic in the fields of aerodynamics,propulsion,structure,material,and control.Different types of re-entry gliding,air-breathing cruise,and aerospace vehicles have been designed to realize ambitious tasks,which in turn influenced the technological advancements and process change in the military.This paper summarizes the control-oriented integrated design of HSVs.First,the status of current research on the distinct characteristics and technique issues of HSVs is introduced.Then,the progresses made on complex modeling,guidance and control,and trajectory optimization are elaborated to exhibit the significant research interest in hypersonic technologies.The control-integrated design of HSVs is emphasized to solve the multidisciplinary design problems associated with the model and its control and trajectory.Various strategies regarding the multidisciplinary optimization design are also proposed to solve the integrated design problem.Finally,suggestions are provided for the control-oriented integrated design of HSVs.
文摘针对当前飞行训练模拟器中航电系统显控逻辑仿真软件开发困难、可维护性差的问题,提出一种将显控逻辑判断与显示画面仿真独立设计的模块化、松耦合的显控系统功能仿真思路。根据显控系统交互式、多输入多输出的时序逻辑决策特点,基于有限状态机(finite state machine,FSM)理论构建显控逻辑仿真模块,并应用Simulink/Stateflow进行实现。结果表明:该设计思路结构合理,开发过程直观,程序可维护性、可移植性强,有利于提高显控逻辑仿真度和开发效率。
