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DESIGNING REDUCED-ORDER controlLERS OF MIXEDSENSITIVITY PROBLEM FOR flight control systems

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Chinese Journal of Aeronautics 2000年第2期13卷 91-94页

作者：曾建平程鹏北京航空航天大学北京 1 0 0 0 83

Based on linear matrix inequalities (LMI), the design method of reduced order controllers of mixed sensitivity problem is studied for flight control systems. It is shown that there exists a controller with order not greater than the difference between the generalized plant order and the number of independent control variables, if the mixed sensitivity problem is solvable for strict regular flight control plants. The proof is constructive, and an approach to design such a controller can be obtained in terms of a pair of feasible solution to the well known 3 LMI. Finally, an example of mixed sensitivity problem for a flight control system is given to demonstrate practice of the approach.

关键词： flight control systems H ∞ control LMI reduced order controller

Fault diagnosis and accommodation for linear parameter-varying in flight control systems

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Fault diagnosis and accommodation for linear parameter-varyi...

Multi-Model Based Adaptive Reconfiguration control for flight control systems with Actuator Faults

2009年中国智能自动化会议

作者：陈伟姜斌张柯 College of Automation Engineering Nanjing University of Aeronautics and Astronautics

The fault diagnosis and accommodation strategy for a class of linear parameter-varying(LPV) systems were investigated. A fast adaptive fault estimation(FAFE) algorithm for LPV systems module,based on an adaptive observer,proposed to enhance the performance of fault estimation including rapidity and ***,the obtained fault estimate was used to construct the fault tolerant control(FTC) *** design method was formulated as a convex linear matrix inequalities(LMIs) optimization problem. Once the faults are estimated,the fault tolerant controller is implemented as a dynamic output feedback *** controller can compensate for the effect of the faults by stabilizing the closed-loop ***,a helicopter model in a vertical flight with actuator fault was used to the effectiveness of the proposed approach.

关键词： active FTC flight control systems polytopic LPV adaptive observer LMIs

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Multi-Model Based Adaptive Reconfiguration Control for Fligh...

Finite-time sliding mode attitude control for a reentry vehicle with blended aerodynamic surfaces and a reaction control system

2011 Chinese control and Decision Conference（CCDC）

作者： Yuying Guo,Zhengwei Zhu are with the School of Information Engineering,Southwest University of Science and Technology,Mianyang 621010,P.R.China.Youmin Zhang is Department of Mechanical and Industrial Engineering,Concordia University,Montreal,Quebec H3G 2W1,Canada.Peng Shi is with the Department of Computing and Mathematical Sciences,University of Glamorgan,Pontypridd,CF37 1DL,United Kingdom and the School of Engineering and Science,Victoria University Melbourne,Vic 8001,Australia.Bin Jiang is with the College of Automation Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,P.R.China.

This paper concerns the application of multimodel based adaptive control approach to accommodate actuator fault for fiight control *** approach does not require the exact information about the controlled system and persistent input *** method can increase robustness and provides stable adaptation of unknown *** model following conditions and adaptive rules are derived and system stability is guaranteed,while appropriate switching of the multiple models ensures asymptotic tracking for system *** aircraft model is given to illustrate the efficiency of the proposed method.

关键词： Actuator fault Direct adaptive reconfiguration control Multiple model flight control systems

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Chinese Journal of Aeronautics 2014年第4期27卷 964-976页

作者： Geng Jie Sheng Yongzhi Liu Xiangdong Key Laboratory for Intelligent control&Decision of Complex systems Beijing Institute of Technology School of Automation Beijing Institute of Technology

This paper proposes a finite-time robust flight controller, targeting for a reentry vehicle with blended aerodynamic surfaces and a reaction control system（RCS）. Firstly, a novel finite-time attitude controller is pointed out with the introduction of a nonsingular finite-time sliding mode manifold. The attitude tracking errors are mathematically proved to converge to zero within finite time which can be estimated. In order to improve the performance, a second-order finite-time sliding mode controller is further developed to effectively alleviate chattering without any deterioration of robustness and accuracy. Moreover, an optimization control allocation algorithm, using linear programming and a pulse-width pulse-frequency（PWPF） modulator, is designed to allocate torque commands for all the aerodynamic surface deflections and on–off switching-states of RCS *** are provided for the reentry vehicle considering uncertain parameters and external disturbances for practical purposes, and the results demonstrate the effectiveness and robustness of the attitude control system.

关键词： Chattering alleviation control allocation Finite-time convergence flight control systems Second-order sliding mode Singularity elimination Sliding mode control

Observer-based backstepping longitudinal control for carrier-based UAV with actuator faults

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Journal of systems Engineering and Electronics 2017年第2期28卷 322-337页

作者： Fengying Zheng Ziyang Zhen Huajun Gong College of Astronautics Nanjing University of Aeronautics and Astronautics Nanjing 210016 China College of Automation Engineering Nanjing University of Aeronautics and Astronautics Nanjing 210016 China

The paper presents the longitudinal control for the carrier-based unmanned aerial vehicle (UAV) system with unmeasured states, actuator faults, control input constraints, and external disturbances. By combining output state observer, adaptive fuzzy control, and constraint backstepping technology, a robust fault tolerant control approach is proposed. An output state observer with fuzzy logic systems is developed to estimate unmeasured states, and command filters rather than differentiations of virtual control law are used to solve the computational complexity problem in traditional backstepping. Additionally, a robust term is introduced to offset the fuzzy adaptive estimation error and external disturbance, and an appropriate fault controller structure with matching conditions obtained from fault compensation is proposed. Based on the Lyapunov theory, the designed control program is illustrated to guarantee that all the closed-loop signals of the given system are bounded, and the output errors converge to a small neighborhood of zero. A carrier-based UAV nonlinear longitudinal model is employed to testify the feasibility and validity of the control scheme. The simulation results show that all the controllers can perform at a satisfactory level of reference tracking despite the existence of unknown aerodynamic parameters and actuator faults. © 2017 Beijing Institute of Aerospace Information.

关键词： Actuators Aircraft control Backstepping control system analysis control theory controllers Error compensation Fault tolerance flight control systems Fuzzy control Fuzzy filters Fuzzy logic State estimation Three term control systems Unmanned aerial vehicles (UAV)

Closed-loop dynamic control allocation for aircraft with multiple actuators

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Chinese Journal of Aeronautics 2013年第3期26卷 676-686页

作者： Gai Wendong Wang Honglun Science and Technology on Aircraft control Laboratory Beihang University

A closed-loop control allocation method is proposed for a class of aircraft with multiple actuators. Nonlinear dynamic inversion is used to design the baseline attitude controller and derive the desired moment increment. And a feedback loop for the moment increment produced by the deflections of actuators is added to the angular rate loop, then the error between the desired and actual moment increment is the input of the dynamic control allocation. Subsequently, the stability of the closed-loop dynamic control allocation system is analyzed in detail. Especially, the closedloop system stability is also analyzed in the presence of two types of actuator failures： loss of effectiveness and lock-in-place actuator failures, where a fault detection subsystem to identify the actuator failures is absent. Finally, the proposed method is applied to a canard rotor/wing （CRW） aircraft model in fixed-wing mode, which has multiple actuators for flight control. The nonlinear simulation demonstrates that this method can guarantee the stability and tracking performance whether the actuators are healthy or fail.

关键词： Canard rotor/wing aircraft Closed-loop control allocation Dynamic inversion flight control systems Redundant actuators

Flying qualities based time-varying stability augmentation system design for tiltrotor conversion control

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Chinese Journal of Aeronautics 2024年第11期37卷 366-385页

作者： Chen WANG Wenqian TAN Liguo SUN Junkai JIAO flight Dynamics Department Beihang UniversityBeijing 100191China Chinese Aeronautical Establishment Beijing 100012China Jiangxi Research Institute Beihang UniversityNanchang 330096China

Tiltrotors have three flight modes that pose control problems and quality defects during the conversion *** address this,a novel flying qualities-based time-varying stability augmentation system is designed to achieve multi-mode,nonlinear,and time-varying *** system integrates a nonlinear time-varying control law with the flying qualities requirements for all three flight *** consists of an inner and outer loop control framework,where the control law in the inner loop is designed based on the Lyapunov theorem of *** reference models in the outer loop are derived from the flying qualities criteria to meet level one flying qualities *** evaluate the conversion process,a time-varying flying qualities evaluation method is developed,which includes the conversion path,pilot model,and time-varying flying qualities *** proposed time-varying stability augmentation control system is then tested through simulation during the conversion process.A pilot-aircraft closed-loop system is established for conducting *** between simulation results and pilot-in-loop experiment results demonstrates the effectiveness of the proposed control ***,it proves that the evaluation method is suitable for analyzing time-varying *** research can be valuable in designing and evaluating stability augmentation controls for strongly time-varying systems.

关键词： Tiltrotor Time varying control system flight control systems Flying qualities flight simulators

control-oriented modeling of a high-aspect-ratio flying wing with coupled flight dynamics

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Chinese Journal of Aeronautics 2023年第4期36卷 409-422页

作者： Cong NIU Xiutian YAN Boyi CHEN Department of Design Manufacturing&Engineering ManagementUniversity of StrathclydeGlasgow G11XQUK College of Astronautics Nanjing University of Aeronautics and AstronauticsNanjing 210016China

The flight-structural dynamics of a high-aspect-ratio wing challenge the flight control *** paper develops a reduced model of coupled dynamics with stability *** structural dynamics are formulated with dihedrals,and the central loads drive the *** control-oriented model with essential coupled dynamics is *** sensitivity anal-ysis and input–output pairing are performed to identify the control ***,an example of flight control design is provided to discuss the necessity of considering structural dynamics in controller *** coupled flight dynamics provide a system-theoretic approach for sta-bility and facilitate model-based control *** results reveal the characteristics of flight-structural coupled dynamics and demonstrate that the influence of flexible modes should be considered in control design,especially in lateral dynamics.

关键词： Flexible couplings Flexible wings flight control systems flight dynamics Sensitivity analysis

Nonlinear adaptive flight control system:Performance enhancement and validation

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Chinese Journal of Aeronautics 2023年第4期36卷 354-365页

作者： Yue FENG Zonghua SUN Liaoni WU Yongshun WANG Bin XI Weng Khuen HO Yancheng YOU School of Aerospace Engineering Xiamen UniversityXiamen 361102China Department of Electrical and Computer Engineering National University of SingaporeSingapore 117576Singapore

The problem of decreasing stability margins in L1 adaptive control systems is discussed and an out-of-loop L1 adaptive control scheme based on Lyapunov’s stability theorem is *** scheme enhances the effectiveness of the adaptation,which ensures that the system has suffi-cient stability margins to achieve the desired performance under parametric uncertainty,additional delays,and actuator *** stability of the developed control system is demonstrated through a series of *** with an existing control scheme,the constant adjustment of the sta-bility margins by the proposed adaptive scheme allows their range to be extended by a factor of 4–5,bringing the stability margin close to that of variable gain PD control with adaptively scheduled *** engineered practicability of adaptive technology is verified.A series of flight tests verify the practicability of the designed adaptive *** results of these tests demonstrate the enhanced performance of the proposed control scheme with nonlinear parameter estimations under insufficient stability margins and validate its robustness in the event of actuator failures.

关键词： Adaptive control systems control engineering flight control systems Nonlinear control systems Robustness stability