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International Conference on Fluid Power and Mechatronics (FPM)

作者： Boya Zhang Zongxia Jiao Rongjie Kang Shuai Wu Pan Zhao Science and Technology on Aircraft Control Laboratory Beihang University Beijing China

The basic rotate-vector optimization method (BROM) is a direct optimization algorithm and is valuable to engineering application. Multipoint rotate-vector optimization method (MROM) is an improved algorithm based on BROM. In the On-line Identification based Optimal control (OIOC) scheme, the author apply MROM to optimize the PID controller, the simulation is done on the co-simulation platform and the result showed its effectiveness and convergence.

关键词： Optimization methods MATLAB Mathematical model Object recognition Servomotors Optimal control

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Compound control for electro-hydraulic positioning servo system based on dynamic inverse model

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Jixie Gongcheng Xuebao/Journal of Mechanical Engineering 2011年第10期47卷 145-151页

作者： Yao, Jianyong Jiao, Zongxia Huang, Cheng Science and Technology on Aircraft Control Laboratory Beihang University Beijing 100191 China School of Automation Science and Electrical Engineering Beihang University Beijing 100191 China

Electro-hydraulic positioning servo system is a typical nonlinear system, and usually suffers uncertain external disturbances which make the conventional controller fail to meet the high performance requirements. A compound controller based on the dynamic inverse model of system is proposed, which includes a feed-forward controller and a robust controller to improve system control accuracy and robustness respectively. The rules of robust controller are presented and online parameter estimation is given for the compound controller to adapt the system nonlinear characteristics. A case study is presented, and experimental results show that the system nonlinear parameters are estimated accurately and the proposed compound control can handle the external disturbances effectively and upgrade the tracking performance of the hydraulic system. © 2011 Journal of Mechanical Engineering.

关键词： Robust control

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Robust initial alignment for inertial navigation systems with multiple types of disturbances

Robust initial alignment for inertial navigation systems wit...

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作者： Guo, Lei Cao, Songyin National Key Laboratory on Science and Technology on Aircraft Control Beihang University Beijing 100191 China Department of Automation College of Information Engineering Yangzhou University Yangzhou 225009 China

In this paper, the robust initial alignment problem for inertial navigation systems (INSs) is investigated. Different from most previous works only focusing on Gaussian noises (or other single disturbance), the INS error equation with multiple types of disturbances is constructed. We consider two types of disturbances, where the first type is the sensor drifts described by an exosystem, and the second one includes the nonlinear modeling uncertainties and other measurement noises. A robust filter is constructed for the concerned INS with disturbance rejection and attenuation performance. In the proposed approach, the drift estimations are applied to reject the inertial sensor drifts, H∞ performance is applied to attenuate the norm bounded uncertain disturbances. The proposed multi-objective filter is with both disturbance rejection and attenuation performance. Finally, simulation for stationary base alignment of an INS is given to show the efficiency of the proposed approach. © 2011 Zhejiang University.

关键词： Inertial navigation systems

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Transition flight control for Canard Rotor/Wing rotorcraft

Transition flight control for Canard Rotor/Wing rotorcraft

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International Conference on Artificial Intelligence, Management science and Electronic Commerce (AIMSEC)

作者： Tengfei Guo Honglun Wang Wendong Gai Science and Technology on Aircraft Control Laboratory Beijing Aeronautics and Astronautics University Beijing China

Canard Rotor/Wing (CRW) Unmanned Aerial Vehicle (UAV) combines advantages of a helicopter for taking-off and hover, and a fixed-wing aircraft for high speed cruise. A key technology involved is control system design for transition flight. This paper describes flight characteristic of CRW UAV with achieving transition flight from helicopter mode to fixed-wing mode. Dynamic model is built and analyzed. control strategy is proposed for three flight modes, including helicopter mode, conversion mode and fixed-wing mode. Then, flight control law is designed by modified nonlinear dynamic inversion technique. In addition, we succeed to allocate redundant control inputs for the CRW with generalized multiple control effectors. Finally, simulation has been done with MATLAB /SIMULINK toolbox. The CRW UAV accelerates from helicopter mode to fixed-wing mode. Meanwhile, control loops are closed on airspeed and altitude. Simulation results show that the designed controller could meet the requirements for transition flight control.

关键词： Rotors Helicopters Aerodynamics Aerospace control Acceleration Atmospheric modeling Mathematical model

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Design of new predictive guidance algorithm via fuzzy techniques

Design of new predictive guidance algorithm via fuzzy techni...

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International Conference on Electrical and control Engineering (ICECE)

作者： Junbo Wang Zhang Ren Zixuan Liang Zihao Xiong Science and Technology on Aircraft Control Laboratory Beijing University of Aeronautics and Astronautics Beijing China

New predictive guidance (NPG) algorithm is proposed and the fuzzy techniques are adopted to improve the real-time capability of the predictive guidance. The simplified kinematical and dynamical equations of model for the entry vehicle are established. The nominal bank angel profile is established beforehand to implement numerical prediction. The predictive errors are used as input of fuzzy logic controller which is designed for generation of correct commands. The fuzzy logic controller avoids massive iterations of conventional predictive guidance (CPG) algorithm and improves the real-time capability. Numerical simulations for the proposed algorithm under the condition of perturbations are presented to demonstrate the capability and effectiveness.

关键词： Prediction algorithms Algorithm design and analysis Vehicles Trajectory Real time systems Atmospheric modeling Vehicle dynamics

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Profile-tracking entry guidance using adaptive global sliding mode control theory

Profile-tracking entry guidance using adaptive global slidin...

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International Conference on Electrical and control Engineering (ICECE)

作者： Yu Hu Zhang Ren Zhen Shen Xin Qu Peng Jiang Science and Technology on Aircraft Control Laboratory Beijing University of Aeronautics and Astronautics Beijing China

Profile-tracking guidance of Reusable Launch Vehicle (RLV) is a challenging task due to dramatic aerodynamic data perturbations. A novel adaptive global sliding mode control (AGSMC) scheme is developed so that the closed-loop system shows invariance property to parameter uncertainties all the time. The approach designs a global sliding mode surface based on optimization theory and uses adaptive technology to estimate the uncertain items of the system so as to alleviate the chattering. Numerical simulations for profile-tracking under the condition of aerodynamic data perturbations are presented to demonstrate the capability and effectiveness of the proposed algorithm.

关键词： Aerodynamics Adaptive systems Uncertainty Robustness Sliding mode control Uncertain systems Vehicle dynamics

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A new piecewise predictive guidance for the long-range reentry vehicles

A new piecewise predictive guidance for the long-range reent...

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International Conference on Electrical and control Engineering (ICECE)

作者： Junbo Wang Zhang Ren Science and Technology on Aircraft Control Laboratory Beijing University of Aeronautics and Astronautics Beijing China

A new predictive guidance algorithm was presented for the long-range reentry vehicles to improve the real-time capability of the conventional predictive guidance. The equation of constraints in reentry flight was established. The bank angle curve of the reference trajectory was generated beforehand to supply the reference states for piecewise predictive guidance. The absolute value of the bank angle viewed as the control variable was designed to be a piecewise linear function of the energy parameter which consists of the velocity and the altitude. The reversal condition of the bank angle was gotten using the method of the azimuth error boundary. The predictive points were chosen according to the predictive time step and the predictive guidance equation which was used to generate the control corrections of the bank angel was designed. This approach avoids massive iterations of the conventional predictive guidance. Simulation results indicate that the method can decrease the time cost of the predictive guidance to a satisfying level and improve the guidance accuracy at the Terminal Area Energy Management (TAEM) interface.

关键词： Vehicles Trajectory Mathematical model Prediction algorithms Equations Algorithm design and analysis Real time systems

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Application of a feedforward controller with a disturbance observer for UAV during missile launch

Application of a feedforward controller with a disturbance o...

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International Conference on Artificial Intelligence, Management science and Electronic Commerce (AIMSEC)

作者： Dawei Li Honglun Wang Wendong Gai Science and Technology on Aircraft Control Laboratory Beijing Aeronautics and Astronautics University Beijing China

This paper presents a feedforward controller with disturbance observer for UAV (unmanned aerial vehicle), which is able to reduce the disturbance produced by launching missile from UAV. The focus of this work was in two areas. First, according to the layout characteristics of UAV platform, the aerodynamic interference between UAV and external stores was analyzed, and the flight stability and control performance during two ways of external separation were simulated by establishing six degree-of-freedom dynamics and kinematics equations of UAV. Second, the control law was designed by blending the feedforward controller and disturbance observer into the flight control system. The simulation results show that the stability and anti-interference ability of UAV are improved during the missile launch.

关键词： Missiles Feedforward neural networks Observers Interference Resistance Aerodynamics

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Modeling and LPV flight control of the Canard Rotor/ Wing unmanned aerial vehicle

Modeling and LPV flight control of the Canard Rotor/ Wing un...

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International Conference on Artificial Intelligence, Management science and Electronic Commerce (AIMSEC)

作者： Wendong Gai Honglun Wang Tengfei Guo Dawei Li Science and Technology on Aircraft Control Laboratory Beijing Aeronautics and Astronautics University Beijing China

ISBN: (纸本)9781457705359

The concept, known as the Canard Rotor/Wing (CRW) unmanned aerial vehicle (UAV) combines the hover flight characteristic of a helicopter with high subsonic cruise of a fixed-wing aircraft. The longitudinal flight dynamic model of CRW was developed, and the trim result was derived in the full flight envelope. The linear model of CRW was derived by the Jacobian linear method, and it was nonlinearly dependent on the time-varying flight speed and altitude. The tensor-product (TP) model transformation was adopted to transform the model to a convex polytopic model form. Hence, a linear parameter-varying (LPV) synthesis method was used to design the flight control system of CRW in the rotary mode. The simulation results show that the desired performance objectives are achieved in the rotary flight stage.

关键词： Rotors Aerodynamics Atmospheric modeling Aerospace control aircraft Vehicle dynamics Force

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Onboard generation of reentry drag profile using fuzzy logic

Onboard generation of reentry drag profile using fuzzy logic

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International Conference on Electrical and control Engineering (ICECE)

作者： Zhen Shen Zhang Ren Jingjing Li Science and Technology on Aircraft Control Laboratory Beijing University of Aeronautics and Astronautics Beijing China

A novel method for fast design of reentry drag profile for reusable launch vehicle (RLV) is developed. A reference drag profile as a function of velocity is designed as a two-segment piecewise line subjects to given initial conditions, path constraints, and terminal conditions. The secant method is utilized to search for the turning point of the profile rapidly until the gliding range and the terminal velocity meet the desired values simultaneously. To ensure the convergence of the search, a fuzzy controller is designed to determine the initial value of the turning point in accordance with a specified gliding range. Numerical simulations for various reentry missions are implemented to demonstrate the effectiveness of the method. The results show that the proposed method could generate a drag profile within 1 second and is applicable to reentry cases with gliding range varying from 3000~15000 km.

关键词： Aerodynamics Vehicle dynamics Vehicles Trajectory Upper bound Acceleration Numerical simulation

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