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Adaptive spacecraft attitude tracking Controller Design Based on Similar Skew-symmetric Structure

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Chinese Journal of Aeronautics 2010年第2期23卷 227-234页

作者：刘宜成张涛宋靖雁梁斌清华大学自动化系

This article presents an adaptive attitude tracking controller with external disturbances and unknown inertia parameters. The similar skew-symmetric structure is extended from the autonomous case to the non-autonomous case. The non-autonomous similar skew-symmetric is chosen as the desired structure of the closed loop system for attitude controller design. Based on this structure, a novel adaptive backstepping scheme is proposed to design the attitude controller by taking full advantage of the symmetry and the positive definiteness of the inertia matrix. The attitude tracking precision is enhanced by employing the linear parameterized form of the external disturbance torques. Simulation results demonstrate the effectiveness of the proposed attitude controller.

关键词： spacecraft attitude tracking similar skew-symmetric structure backstepping adaptive non-autonomous

Fuzzy Sliding Mode Controller Design for spacecraft attitude tracking in Terms of Quaternion

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Fuzzy Sliding Mode Controller Design for Spacecraft Attitude...

Sliding-Mode-Based attitude tracking Control of spacecraft Under Reaction Wheel Uncertainties

第二十七届中国控制会议

作者： Ataei Mohammad Shafiei S.Ehsan Electronic Department Engineering FacultyUniversity of Isfahan Electrical and Robotic Engineering Faculty Shahrood University of Technology

In this paper a fuzzy sliding mode control（FSMC） for spacecraft attitude tracking in terms of quaternion is designed. For this purpose,at first,the spacecraft dynamic and kinematic equations based on quaternion are ***,the design procedure of related variable structure controller is *** prove the system stability in sliding mode and also to guarantee the convergence of quaternion vectors to desired state,a lemma is presented which is proved by using Lyapunov direct *** continuation,in order to improve the controller performance,tuning of the sliding mode gain is accomplished by using fuzzy logic ***,the proposed controller design is simulated on an assumed case study with uncertain parameters and external *** simulation results are provided to show the effectiveness of the method and its robustness to parameter uncertainties and disturbances.

关键词： Sliding mode control Fuzzy logic Lyapunov stability spacecraft attitude tracking Quaternion

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IEEE/CAA Journal of Automatica Sinica 2023年第6期10卷 1475-1487页

作者： Wei Chen Qinglei Hu the School of Automation Science and Electrical Engineering Beihang UniversityBeijing 100191China. The Beihang Hangzhou Innovation Institute Yuhang Hangzhou 310023China

The attitude tracking operations of an on-orbit spacecraft with degraded performance exhibited by potential actuator uncertainties(including failures and misalignments) can be extraordinarily challenging. Thus, the control law development for the attitude tracking task of spacecraft subject to actuator(namely reaction wheel) uncertainties is addressed in this paper. More specially, the attitude dynamics model of the spacecraft is firstly established under actuator failures and misalignment(without a small angle approximation operation). Then, a new non-singular sliding manifold with fixed time convergence and anti-unwinding properties is proposed, and an adaptive sliding mode control(SMC) strategy is introduced to handle actuator uncertainties, model uncertainties and external disturbances simultaneously. Among this, an explicit misalignment angles range that could be treated herein is offered. Lyapunov-based stability analyses are employed to verify that the reaching phase of the sliding manifold is completed in finite time, and the attitude tracking errors are ensured to converge to a small region of the closest equilibrium point in fixed time once the sliding manifold enters the reaching phase. Finally, the beneficial features of the designed controller are manifested via detailed numerical simulation tests.

关键词： Actuator failures actuator misalignment angles finite time sliding mode control(SMC) spacecraft attitude tracking

Fully-Actuated System Approach Based Optimal attitude tracking Control of Rigid spacecraft with Actuator Saturation

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Journal of Systems Science & Complexity 2022年第2期35卷 688-702页

作者： LIU Gaoqi ZHANG Kai LI Bin School of Aeronautics and Astronautics Sichuan UniversityChengdu 610065China

In this paper,a fully-actuated system approach(FASA)based control method is proposed for rigid spacecraft attitude tracking with actuator ***,a second-order fully-actuated form of spacecraft attitude error model is established by modified Rodrigues parameters(MRPs).The unknown total disturbance caused by inertial uncertainty and external disturbance is estimated by using extended state observer,then an FASA based controller is ***,a control parameterization method is adopted to optimize the parameter matrices of FASA based controller with the actuator ***,a numerical example is carried out to validate the effectiveness of the proposed scheme.

关键词： Full-actuated system approach modified Rodrigues parameters parameter optimization spacecraft attitude tracking

Disturbance-Observer-Based attitude tracking Control for Rigid spacecraft with Unmeasurable Angular Velocity

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Disturbance-Observer-Based Attitude Tracking Control for Rig...

Reinforcement⁃Learning⁃Based Appointed⁃Time Prescribed Performance attitude Control for Rigid spacecraft

2021中国智能自动化大会(CIAC2021)

作者： Jintao Hu Yingmin Jia The Seventh Research Division and the Center for Information and Control School of Automation Science and Electrical EngineeringBeihang University (BUAA)

This paper addresses the rigid spacecraft attitude tracking control problem in the presence of input saturation, unmeasurable angular velocity and external disturbance. First, an angular velocity observer is proposed to estimate the unavailable angular velocity. Further, another disturbance observer is provided to obtain the estimation of the external disturbance. Based on the second order sliding mode surface, the compensation of input saturation, and these two observers, a continuous attitude control strategy with only attitude measurement is *** utilizing the Lyapunov theory, it is demonstrated that the proposed controller can realize attitude tracking control of spacecraft and keep all variables of the rigid spacecraft attitude system are uniformly ***, numerous simulations illustrate the feasibility of the proposed control law.

关键词： spacecraft attitude tracking State observer Disturbance observer Input saturation Sliding mode control

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Journal of Harbin Institute of Technology(New Series) 2023年第1期30卷 13-23页

作者： Xiaoning Shi Di Zhou Zhigang Zhou School of Electronic Information Jiangsu University of Science and TechnologyZhenjiang 212003JiangsuChina Fujian(Quanzhou)-HIT Research Institute of Engineering and Technology Quanzhou 362000FujianChina School of Astronautics Harbin Institute of TechnologyHarbin 150001China

This paper addresses a geometric control algorithm for the attitude tracking problem of the rigid spacecraft modeled on SO(3).Considering the topological and geometric properties of SO(3),we introduced a smooth positive attitude error function to convert the attitude tracking issue on SO(3)into the stabilization counterpart on its Lie *** error transformation technique was further utilized to ensure the assigned transient and steady state performance of the attitude tracking error with the aid of a well⁃designed assigned⁃time performance ***,using the actor⁃critic(AC)neural architecture,an adaptive reinforcement learning approximator was constructed,in which the actor neural network(NN)was utilized to approximate the unknown nonlinearity online.A critic function was introduced to tune the next phase of the actor neural network operation for performance improvement via supervising the system performance.A rigorous stability analysis was presented to show that the assigned system performance can be ***,the effectiveness and feasibility of the constructed control strategy was verified by the numerical simulation.

关键词： spacecraft attitude tracking appointed⁃time control performance constraints actor⁃critic NNs