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attitude tracking control of flexible spacecraft with large amplitude slosh

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Acta Mechanica Sinica 2017年第6期33卷 1095-1102页

作者： Mingle Deng Baozeng Yue School of Aerospace Engineering Beijing Institute of Technology Beijing 100081 China

This paper is focused on attitude tracking control of a spacecraft that is equipped with flexible appendage and partially filled liquid propellant tank. The large amplitude liquid slosh is included by using a moving pulsating ball model that is further improved to estimate the settling location of liquid in microgravity or a zero-g environment. The flexible appendage is modelled as a three-dimensional Bernoulli–Euler beam, and the assumed modal method is employed.A hybrid controller that combines sliding mode control with an adaptive algorithm is designed for spacecraft to perform attitude tracking. The proposed controller has proved to be asymptotically stable. A nonlinear model for the overall coupled system including spacecraft attitude dynamics,liquid slosh, structural vibration and control action is established. Numerical simulation results are presented to show the dynamic behaviors of the coupled system and to verify the effectiveness of the control approach when the spacecraft undergoes the disturbance produced by large amplitude slosh and appendage vibration. Lastly, the designed adaptive algorithm is found to be effective to improve the precision of attitude tracking.

关键词： attitude tracking Large amplitude liquid slosh Flexible spacecraft Dynamic coupling Adaptive sliding mode control

Event-triggered attitude tracking for rigid spacecraft

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Science China(Information Sciences) 2019年第12期62卷 178-193页

作者： Deheng CAI Hengguang ZOU Junzheng WANG Yuan HUANG Dawei SHI State Key Laboratory of Intelligent Control and Decision of Complex Systems School of AutomationBeijing Institute of Technology China Academy of Space Technology

This study aims to investigate the problem of attitude control for a spacecraft with inertial uncertainties, external disturbances, and communication restrictions. An event-triggered active disturbance rejection control approach is proposed for attitude tracking of the spacecraft. An event-triggered mechanism is introduced together with an extended state observer to jointly monitor the system states and total disturbances. The observation error is proved to be uniformly bounded. Based on the proposed control scheme,the integrated tracking system is shown to be asymptotically stable, implying successful attitude tracking of the spacecraft for the desired motion. Numerical results illustrate the effectiveness of the control strategy in achieving satisfactory tracking performance with a reduced data-transmission cost.

关键词： spacecraft attitude tracking active disturbance rejection control event-triggered control extended state observer

Fixed-time attitude tracking control for spacecraft based on a fixed-time extended state observer

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Science China(Information Sciences) 2021年第11期64卷 154-170页

作者： Lijun ZHANG Yuanqing XIA Ganghui SHEN Bing CUI School of Automation Beijing Institute of Technology

This paper deals with the problem of fixed-time attitude tracking control for spacecraft subject to model uncertainties and external disturbances. Firstly, by using a fixed-time extended state observer(Fx TESO), the synthetic uncertainties generated by external disturbances and model deviations can be estimated and compensated accordingly. We propose a novel Fx TESO aimed to improve previous *** with the existing extended state observer(ESO), the proposed Fx TESO provides faster convergence and higher accuracy. Then, we design a fixed-time adaptive attitude tracking controller based on the strategy combining the Fx TESO and fast non-singular terminal sliding mode control(FNTSMC), such that a desired attitude can be achieved accurately, which does not only allow providing fast and accurate responses,and acceptable chattering suppression, but also avoid singularity. Finally, the numerical simulation results are discussed to verify the efficiency and merits of the proposed control strategy.

关键词： spacecraft fixed time attitude tracking FxTESO FNTSMC

attitude tracking control for autogyro based on derivative-free adaptive NDI and dynamic control allocation 36

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Attitude tracking control for autogyro based on derivative-f...

Finite-Time attitude tracking Control of Spacecraft with Actuator Saturation

第36届中国控制会议

作者： Lin Qing

ISBN: (纸本)9781538629185

This paper presents a new attitude tracking control scheme for *** example unmanned autogyro is built and modeled based on explicit blade element method（EBEM）.To tackle the strong coupling and fast time-varying periodic disturbances,a new attitude control scheme is *** scheme employs nonlinear dynamic inversion augmented with derivative-free adaptive neural network to achieve decoupling and fast *** coordinate the aerodynamic control surfaces and non-affine rotor cyclic pitch controls,a rotor-surface control allocator is designed based on dynamic control allocation *** simulations illustrate the superior performance of the proposed scheme comparing to conventional PID and derivative-based adaptive controllers in the presence of fast time-varying disturbances.

关键词： unmanned autogyro control-oriented rotor model attitude tracking derivative-free adaptive nonlinear inversion control dynamic control allocation

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Journal of Shanghai Jiaotong university(Science) 2018年第5期23卷 650-656页

作者： LIU Yueyang HU Qinglei GUO Lei School of Automation Science and Electrical Engineering Beihang UniversityBeijing 100191China

The attitude tracking control problem of a rigid spacecraft with actuator saturation is investigated in this paper. A finite-time attitude tracking control scheme is presented by incorporating sliding mode control(SMC) and adaptive technique. Specifically, a novel time-varying sliding mode manifold is first developed that aims at regulating the attitude tracking error to equilibrium point within a certain finite time. Moreover, it can be specified a priori by the designer according to the mission requirement. Subsequently, an adaptive controller is derived by using the SMC in conjunction with adaptive technique. The designed controller is capable of ensuring that the state trajectories reach to sliding regime within a finite time, and hence that attitude tracking error can converge to zero in a finite time with the aid of the developed sliding dynamics, despite the presence of exogenous disturbances, unknown inertia properties and saturation nonlinearities. Finally, the simulation experiments are carried out to demonstrate the effectiveness of the proposed control scheme.

关键词： time-varying sliding mode finite-time convergence input saturation attitude tracking spacecraft

Semitensor product based adaptive control for attitude tracking of spacecraft with unknown external disturbances

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控制理论与应用（英文版） 2012年第3期10卷 292-296页

作者： Xuxi ZHANG Control and Simulation Center Harbin Institute of TechnologyHarbin Heilongjiang 150001China College of Science Harbin Engineering UniversityHarbin Heilongjiang 150001China

This paper investigates the attitude tracking and disturbance rejection problem of rigid spacecraft. Using a new matrix product, i.e., the semitensor product of matrices, the parameter uncertainties in the inertia matrix is isolated. Both the parameter uncertainties and the external disturbance are handled by robust adaptive control method. By combining the semitensor product of matrices, backstepping control methodology, and adaptive control technique, a new adaptive control law is designed. Simulation result is also presented to demonstrate the proposed design method.

关键词： Semitensor product Adaptive control attitude tracking Disturbance rejection

Neural adaptive attitude tracking controller for flexible spacecraft

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Journal of Harbin Institute of Technology(New Series) 2010年第5期17卷 716-720页

作者：肖冰胡庆雷马广富 Dept.of Control Science and Engineering Harbin Institute of Technology

In this paper,a neural network adaptive controller is proposed for attitude tracking of flexible spacecraft in presence of unknown inertial matrix and external *** this approach,neural network technique is employed to approximate the unknown system dynamics with finite combinations of some basis functions,and a robust controller is also designed to attenuate the effect of approximation error,more specially,the knowledge of angular velocity is not *** the closed-loop system,Lyapunov stability analysis shows that the attitude trajectories asymptotically follow the reference output ***,simulation results are presented for the attitude tracking of a flexible spacecraft to show the excellent performance of the proposed controller and illustrate its robustness in face of external disturbances and unknown dynamics.

关键词： Adaptive control flexible spacecraft attitude tracking neural network

Adaptive Spacecraft attitude tracking Control with Guaranteed Transient Performance 36

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Adaptive Spacecraft Attitude Tracking Control with Guarantee...

Optimal Relative attitude tracking Control for Spacecraft Proximity Operation

第36届中国控制会议

作者： Xiaodong Shao Qinglei Hu Lei Guo School of Automation Science and Electrical Engineering Beihang University

ISBN: (纸本)9781538629185

In this paper,we concentrate on the problem of attitude tracking control with guaranteed transient performance for a rigid spacecraft subject to unknown inertia properties and exogenous disturbances.A promising solution to the problem under consideration is ***,certain performance functions specified a priori by the designer are first introduced to impose desired transient and steady state performance specifications on the attitude tracking ***,by using an error transformation,the original attitude tracking dynamics with performance constraints are transformed into an equivalent unconstrained one whose robust stabilization is shown to be sufficient to achieve prescribed performance ***,based on the transformed system,an adaptive controller is designed by incorporating the backstepping control and the adaptive *** is proven that the control algorithm developed can guarantee the stabilization of the transformed errors,and hence the achievement of the desired performance metrics,as well as the boundedness of all other closed-loop signals,without resorting to an exact knowledge of the inertia matrix and despite the presence of external *** detailed control design and rigorous closed-loop stability analysis,numerical simulations are finally performed on a microsatellite to testify the effectiveness of the proposed control scheme.

关键词： Prescribed performance robust adaptive control attitude tracking spacecraft

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Optimal Relative Attitude Tracking Control for Spacecraft Pr...