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Sliding mode control based guidance law with impact angle constraint

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Chinese Journal of Aeronautics 2014年第1期27卷 145-152页

作者： Zhao Yao sheng yongzhi Liu Xiangdong School of Automation Beijing Institute of Technology Key Laboratory for Intelligent Control & Decision of Complex Systems Beijing Institute of Technology

The terminal guidance problem for an unpowered lifting reentry vehicle against a sta- tionary target is considered. In addition to attacking the target with high accuracy, the vehicle is also expected to achieve a desired impact angle. In this paper, a sliding mode control （SMC）-based guidance law is developed to satisfy the terminal angle constraint. Firstly, a specific sliding mode function is designed, and the terminal requirements can be achieved by enforcing both the sliding mode function and its derivative to zero at the end of the flight. Then, a backstepping approach is used to ensure the finite-time reaching phase of the sliding mode and the analytic expression of the control effort can be obtained. The trajectories generated by this method only depend on the initial and terminal conditions of the terminal phase and the instantaneous states of the vehicle. In order to test the performance of the proposed guidance law in practical application, numerical simulations are carried out by taking all the aerodynamic parameters into consideration. The effec- tiveness of the proposed guidance law is verified by the simulation results in various scenarios.

关键词： Backstepping Impact angle Sliding mode control Terminal guidance Unpowered lifting reentryvehicle

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

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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

Trajectory reshaping based guidance with impact time and angle constraints

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Chinese Journal of Aeronautics 2016年第4期29卷 984-994页

作者： Zhao Yao sheng yongzhi Liu Xiangdong School of Automation Beijing Institute of Technology Key Laboratory for Intelligent Control and Decision of Complex Systems Beijing Institute of Technology

This study presents a novel impact time and angle constrained guidance law for homing missiles. The guidance law is first developed with the prior-assumption of a stationary target, which is followed by the practical extension to a maneuvering target scenario. To derive the closed-form guidance law, the trajectory reshaping technique is utilized and it results in defining a specific polynomial function with two unknown coefficients. These coefficients are determined to satisfy the impact time and angle constraints as well as the zero miss distance. Furthermore, the proposed guidance law has three additional guidance gains as design parameters which make it possible to adjust the guided trajectory according to the operational conditions and missile's capability. Numerical simulations are presented to validate the effectiveness of the proposed guidance law. (C) 2016 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license.

关键词： Guidance Homing missiles Impact angle Impact time Trajectory reshaping

Observer-based finite-time sliding mode control for reentry vehicle

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International Journal of Intelligent Computing and Cybernetics 2015年第4期8卷 345-362页

作者： Xiangdong Liu Xiaohuan Ren yongzhi sheng School of Automation Beijing Institute of TechnologyKey Laboratory of Complex System Intelligent Control and DecisionMinistry of EducationBeijingPeople’s Republic of China

Purpose–The purpose of this paper is to design a disturbance observer-based finite-time global sliding mode control scheme for the attitude tracking control problem of the reentry vehicle with parameter uncertainties and ***/methodology/approach–Feedback linearization is first introduced to transform vehicle model into three independent second order uncertain *** a finite-time controller(FTC)is proposed for the nominal system on the basis of the homogeneity *** the integral sliding mode method is introduced for the vehicle with *** finite time convergence is achieved and global robustness is also assured by the combination of finite time control method and integral sliding mode ***,to improve the attitude angle tracking accuracy a novel finite time disturbance observer(DO)is ***–Simulation is made for the reentry vehicle with disturbances *** the results show the finite-time convergence,tracking accuracy and robustness of the proposed ***/value–The proposed control strategy has three *** of all it can achieve finite time convergence and avoid ***,it can also realize global ***,a new kind of DO is introduced to improve the tracking accuracy.

关键词： Nonlinear control Robust control Variable structure control

Second-order time-varying sliding mode control for reentry vehicle

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International Journal of Intelligent Computing and Cybernetics 2013年第3期6卷 272-295页

作者： Jie Geng yongzhi sheng Xiangdong Liu Key Laboratory of Complex System Intelligent Control and Decision School of AutomationBeijing Institute of TechnologyMinistry of EducationBeijingPeople’s Republic of China

Purpose-The purpose of this paper is to design a global robust and continuous control scheme for the attitude tracking control problem of the reentry vehicle with parameter uncertainties and ***/methodology/approach-First,feedback linearization is applied to the model of reentry vehicle,resulting in three independent uncertain *** a new second-order time-varying sliding function is proposed,based on which a continuous second-order time-varying sliding mode control(SOTVSMC)law is proposed for each *** global robustness and convergence performance of the closed-loop reentry vehicle control system under the proposed control law are ***-Simulation is made for a reentry vehicle through the assumption that there is external disturbance to aerodynamic moment and the aerodynamic parameters as well as the atmospheric density are *** results verify the validity and robustness of the proposed ***/value-The SOTVSMC attitude controller based on feedback linearization is proposed for the reentry *** advantages of the proposed SOTVSMC are ***,the global second order sliding mode is established,which implies that the closed-loop system is global robust against matched parameter uncertainties and disturbances in ***,the chattering problem is significantly alleviated.

关键词： Flight control Nonlinear control Real-time systems Robust control Variable structure control

Near minimum-time feedback attitude control with multiple saturation constraints for agile satellites

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Chinese Journal of Aeronautics 2016年第3期29卷 722-737页

作者： Liu Xiangdong Xin Xing Li Zhen Chen Zhen sheng yongzhi School of Automation Beijing Institute of Technology National Key Laboratory of Complex System Intelligent Control and Decision Beijing Institute of Technology

Agile satellites are of importance in modern aerospace applications, but high mobility of the satellites may cause them vulnerable to saturation during attitude maneuvers due to limited rating of actuators, This paper proposes a near minimum-time feedback control law for the agile satellite attitude control system. The feedback controller is formed by specially designed cascaded sub-units. The rapid dynamic response of the modified Bang Bang control logic achieves the near optimal property and ensures the non-saturation properties on three-axis. To improve the dynamic performance, a model reference control strategy is proposed, in which the oniline near optimal attitude maneuver path is generated by the cascade controller and is then tracked by a nonlinear back-stepping controller. Furthermore, the accuracy and the robustness of the control system are achieved by momentum-based on-line inertial identification. The rapid attitude maneuvering can be applied for tasks including the move to move case. Numerical simulations are conducted to verify the effectiveness of the proposed control strategy in terms of the saturation-free property and rapidness.

关键词： Actuator saturation Attitude control Identification Momentum transfer Satellites

Second-Order Time-Varying Sliding Mode Control for Uncertain Systems

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Second-Order Time-Varying Sliding Mode Control for Uncertain...

SDRE based Optimal Time-Varying Sliding Mode Control for Re-entry Vehicle

第25届中国控制与决策会议

作者： Jie Geng yongzhi sheng Xiangdong Liu Bing Liu School of Automation Beijing Institute of Technology Key Laboratory of Complex System Intelligent Control and Decision Ministry of Education

ISBN: (纸本)9781467355339

A novel second-order time-varying sliding mode control（SOTVSMC） law is proposed for the robust tracking control problem of nonlinear smooth single-input single-output（SISO） system with disturbance. The advantages of the proposed SOTVSMC are twofold. The global second order sliding mode is established, which implies that the closed-loop system is global robust against matched parameter uncertainties and disturbances. Meanwhile, the chattering problem is significantly alleviated. Then the parameter of the sliding mode is obtained by solving an optimal problem. Finally, the effectiveness and robustness of the control strategy is demonstrated by simulation results.

关键词： Sliding Mode Control Nonlinear Systems Global Second Order Sliding Phase Chattering Alleviation

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SDRE based Optimal Time-Varying Sliding Mode Control for Re-...

Finite-Time Control Based On The Time-Varying Sliding Mode For Spacecraft Body-Fixed Hovering Over an Asteroid 36

第25届中国控制与决策会议

作者： Liang Wang yongzhi sheng Xiangdong Liu Jie Geng School of Automation Beijing Institute of Technology Key laboratory for Intelligent Control & Decision of Complex Systems Beijing Institute of Technology

ISBN: (纸本)9781467355339

An optimal time-varying sliding mode controller based on SDRE approach is proposed in this paper for re-entry vehicle attitude control in the presence of parametric uncertainties and external disturbances. Firstly, an optimal time-varying sliding surface is obtained through the minimization of a given performance index function and the philosophy of time-varying sliding mode control. Subsequently, a discontinuous control law is designed for guaranteeing the existence of the sliding mode throughout the entire response of the system. Therefore, the global robustness can be ensured. Simulation example is finally given to illustrate the effectiveness of the proposed controller.

关键词： Re-entry vehicle Attitude control SDRE Optimal time-varying sliding mode control

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Finite-Time Control Based On The Time-Varying Sliding Mode F...