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Chinese Journal of Aeronautics 2021年第2期34卷 490-503页

作者： Yang LIU Chaoyang DONG Wenqiang ZHANG Qing WANG School of Aeronautic Science and Engineering Beihang UniversityBeijing 100083China School of Automation Science and Electrical Engineering Beihang UniversityBeijing 100083China

In this paper, fast setpoint altitude tracking control for hypersonic flight vehicle(HFV)satisfying Angle of Attack(AOA) constraint is studied with a two-loop structure controller, in the presence of parameter uncertainties and disturbances. For the outer loop, phase plane design is adopted for the simplified model under Bang-Bang controller to generate AOA command guaranteeing fast tracking performance. Modifications based on Feedback-Linearization(FL) technique are adopted to transform the phase trajectory into a sliding curve. Moreover, to resist mismatch between design model and actual model, Fast Exponential Reaching Law(FERL) is augmented with the baseline controller to maintain state on the sliding curve. The inner-loop controller is based on backstepping technique to track the AOA command generated by outer-loop controller. Barrier Lyapunov Function(BLF) design is employed to satisfy AOA requirement. Moreover, a novel auxiliary state is introduced to remove the restriction of BLF design on initial tracking errors. Dynamic Surface Control(DSC) is utilized to ease the computation burden. Rigorous stability proof is then given, and AOA is guaranteed to stay in predefined region theoretically. Simulations are conducted to verify the efficiency and superior performance of the proposed method.

关键词： Adaptive control Angle of attack constraints Barrier Lyapunov function hypersonic flight vehicle Phase plane design Reaching law design

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Robust adaptive control of hypersonic flight vehicle with asymmetric AOA constraint

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Science China(Information Sciences) 2020年第11期63卷 195-207页

作者： Yuyan GUO Bin XU Weixin HAN Shuai LI Yueping WANG Yu ZHANG School of Automation Northwestern Polytechnical University Department of Computing The Hong Kong Polytechnic University flight Automatic Control Research Institute State Key Laboratory of Industrial Control Technology College of Control Science and EngineeringZhejiang University

This paper investigates the state-constrained controller design of a hypersonic flight vehicle(HFV) based on an asymmetric barrier Lyapunov function(ABLF). The robust adaptive back-stepping controller with integral terms is applied for the HFV longitudinal dynamics. Considering the asymmetric angle of attack(AOA) constraint caused by the unique structure and scramjet, the controller is modified by constructing an ABLF, where the asymmetric constraint on AOA tracking error is introduced. Combined with the constraint on virtual control, the AOA is restricted to a predefined asymmetric interval. The system stability and the AOA constraint are guaranteed via Lyapunov analysis. Simulation results verify that the AOA can be kept in the given asymmetric interval while the altitude reference signal is tracked.

关键词： hypersonic flight vehicle HFV integral back-stepping control adaptive control asymmetric barrier Lyapunov function ABLF angle of attack (AOA) constraint

Sliding mode controller design based on reaching law for hypersonic flight vehicle

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International Journal of Modeling, Simulation, and Scientific Computing 2014年第4期5卷 19-35页

作者： Jianmin Wang Yunjie Wu Xiaodong Liu Science and Technology on Aircraft Control Laboratory Department of Automation Science and Electrical Engineering Beihang University Beijing 100191P.R.China

or a hypersonic flight vehicle with highly coupling nonlinear,a sliding mode controller based on reaching law is designed for its longitudinal motion *** proposals of reaching law are *** of which is a variable exponential reaching law,the other one is compound reaching law which consists of a conventional exponential reaching law and a power rate reaching *** reaching law controller can speed up the system states arriving at the sliding mode condition,at the same time,it can guarantee better *** analysis is conducted for trimmed cruise condition of 110,000 ft and Mach 15,in which the responses of the vehicle to a step change of altitude and velocity respectively are *** results show that the controller based on variable exponential reaching law enables the system to faster tracking speed than the conventional reaching *** the compound reaching law controller has shorter tracking time and strong robustness against parameters uncertainties.

关键词： Sliding mode control reaching law hypersonic flight vehicle robustness

Output Feedback Dynamic Surface Controller Design for Airbreathing hypersonic flight vehicle

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IEEE/CAA Journal of Automatica Sinica 2015年第2期2卷 186-197页

作者： Delong Hou Qing Wang Chaoyang Dong School of Automation Science and Electrical Engineering Beihang University Beijing Institute of Electronic System Engineering

This paper addresses issues related to nonlinear robust output feedback controller design for a nonlinear model of airbreathing hypersonic vehicle. The control objective is to realize robust tracking of velocity and altitude in the presence of immeasurable states, uncertainties and varying flight conditions.A novel reduced order fuzzy observer is proposed to estimate the immeasurable states. Based on the information of observer and the measured states, a new robust output feedback controller combining dynamic surface theory and fuzzy logic system is proposed for airbreathing hypersonic vehicle. The closedloop system is proved to be semi-globally uniformly ultimately bounded(SUUB), and the tracking error can be made small enough by choosing proper gains of the controller, filter and observer. Simulation results from the full nonlinear vehicle model illustrate the effectiveness and good performance of the proposed control scheme.

关键词： hypersonic flight vehicle immeasurable states output feedback control model uncertainties fuzzy logic system dynamic surface control

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Neural Network Modeling-Based Anti-Disturbance Tracking Control for hypersonic flight vehicle Models

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Neural Network Modeling-Based Anti-Disturbance Tracking Cont...

第36届中国控制会议

作者： XU Lubing YI Yang SHAO Liren ZHENG Weixing College of Information Engineering Yangzhou University School of Computing Engineering and MathematicsUniversity of Western Sydney

ISBN: (纸本)9781538629185

This paper discusses the novel anti-disturbance control algorithm for hypersonic flight vehicle（HFV） models by using neural network（NN） identifier. Different from those existed anti-disturbance results, the unknown exogenous disturbances in HFV models are assumed to be described by the designed NNs with adjustable parameters. Furthermore, the disturbanceobserver-based-control（DOBC） algorithm with adaptive regulation laws is thus presented to estimate the nonlinear *** integrating the estimated value of disturbances with the PI feedback control input, a composite controller based on convex optimization theory is generated to ensure the satisfactory stability and dynamical tacking convergence of HFV models. Finally,a numerical example for HFV models is included to illustrate the effectiveness of the theoretical results.

关键词： anti-disturbance control hypersonic flight vehicle tracking control neural network identifier disturbance observer

Switching Control Design for A hypersonic flight vehicle

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Switching Control Design for A Hypersonic Flight Vehicle

2010 Chinese Control and Decision Conference

作者： Shuping Tan~(1,2),Zhibin Li~(1,2) 1.National Laboratory of Space Intelligent Control,Beijing 100190 2.Beijing Institute of Control Engineering,Beijing 100190

An adaptive switching controller is designed and analyzed for the longitudinal dynamics of a generic hypersonic air vehicle in the whole cruise phase rather than a trimmed working *** model is nonlinear, multivariable and *** adaptive controller presented in this paper consists of a local linearization method,an adaptive switching law and a nonlinear feedback control ***,a theorem is obtained that the closed-loop system under the adaptive switching control is stable.

关键词： hypersonic flight vehicle Switching Control Adaptive Switching Law Stability

Nonlinear Tracking Control of hypersonic flight vehicle Subjected to Hyperbolic Zero Dynamics via output regulation Theorem

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Nonlinear Tracking Control of Hypersonic Flight Vehicle Subj...

第36届中国控制会议

作者： Yuehui Ji Hailiang Zhou School of Electrical Engineering Tianjin University of Technology Tianjin Institute of Metrological Supervision and Testing(TIMST)

ISBN: (纸本)9781538629185

The standard output regulation theorem is utilized to construct a nonlinear flight tracking controller for a hypersonic vehicle in presence of non-minimum phase dynamic in the *** the elevator is chosen as the only control surface,the hypersonic vehicle model exhibits unstable hyperbolic zero-dynamics,preventing the application of standard inversion-based control *** standard nonlinear output regulation theory is introduced to design a flight controller,achieving asymptotic tracking of velocity and altitude in a climbing maneuver ***,a Taylor-expansion-based approximation method is presented to solve the center manifold equation for the output regulation ***,Numerical simulations in Matlab/Simulation Environment validate the effectiveness of the proposed controller in resisting unstable zero dynamics and providing favorable tracking performance.

关键词： flight tracking Control hypersonic flight vehicle Hyperbolic Zero Dynamics Nonlinear Output Regulation

Robust Model Predictive Controller Design for a hypersonic flight vehicle

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Robust Model Predictive Controller Design for a Hypersonic F...

4th International Conference on Modelling,Identification and Control(ICMIC 2012)

作者： Xiangyuan Tao,Ning Li and Shaoyuan Li are with the department of Automation,Shanghai Jiao Tong University, and key laboratory of systemcontrol and information processing,ministry of education,Shanghai,200240,China

This paper considers the control problem of cruising flight of hypersonic flight vehicle (HFV). The dynamic characteristics of HFV can be addressed as a strong nonlinear, and parameter uncertain multivariable system with hard constraints, which is extremely difficult to design the controller. In this paper, the longitudinal dynamic model of HFV is studied. Subsequently, we propose a robust model predictive control (RMPC) strategy to handle constraints in a systematic manner and overcome the impact of parameter uncertainty on the control effect, and a robust model predictive controller is designed for cruising flight of HFV. Simulation results show that this method can provide sufficient robustness and handle constraints effectively.

关键词： hypersonic flight vehicle longitudinal flight control robust predictive control.

Disturbance Rejection Control Based on Linear Quadratic for Nonminimum-phase hypersonic flight vehicle System

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Disturbance Rejection Control Based on Linear Quadratic for ...

作者： Yu-qing LI Fu-yang CHEN Li WANG College of Automation Engineering Nanjing University of Aeronautics and Astronautics NORINCO Group North Information Control Research Academy Group CO. LTD

This paper proposed a disturbance rejection control method based on linear quadratic（LQ） for nonminimum-phase discrete-time systems with unmatched *** introducing a new cost function that considers the influences of disturbance on the input signal,we apply the novel control method to hypersonic flight vehicle（HFV） system to solve the problem of turbulence compensation.A two-component control input is generated through systematic derivation of finite-time LQ optimal control law,improving the stability,output regulation capability,and robustness of the HFV *** analysis under different control schemes in simulation study shows the effectiveness of the proposed method.

关键词： Linear quadratic Disturbance rejection Nonminimum-phase system hypersonic flight vehicle

Disturbance observer-based backstepping control for hypersonic flight vehicles without use of measured flight path angle

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Chinese Journal of Aeronautics 2021年第2期34卷 396-406页

作者： Yao Lu Beijing Aerospace Automatic Control Institute Beijing 100854China National Key Laboratory of Science and Technology on Aerospace Intelligence Control Beijing 100854China

In this paper a nonlinear control method is proposed for the tracking control of hypersonic flight vehicles. The designed control laws do not utilize the measured flight path angle due to its inferior accuracy in practical engineering. For this, an estimated flight path angle is designed via the measurements of the altitude and velocity. A tracking differentiator is designed for constructing nonlinear disturbance observer which is used to estimate the model uncertainties including the parameter indeterminacies and external disturbances in the channels of velocity and pitch rate. A robust high-order differentiator is introduced to avoid the employment of the measured flight path angle and estimate the lumped disturbance in dynamics of flight path angle. Meanwhile, the possible saturation of the control inputs is considered and compensated by the auxiliary states. The boundness of closed-loop signals is proved through the Lyapunov theory. Comparative simulations are carried out and the results demonstrate the effectiveness of the proposed method.

关键词： Anti-saturation Backstepping Disturbance observer flight control hypersonic flight vehicle State estimation

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