This study addresses the challenge of attitude tracking control for a rigid-flexible spacecraft with high-inertia rotating appendages. The Lagrange method was used to establish the kinematic and dynamic models of the spacecraft. The translation and rotation of the spacecraft, vibrations of solar panels, and imbalance caused by the rotating appendages, which cause a complex control problem, were considered. To address the complex control problem, a novel, fast nonsingular integral sliding mode control method is proposed to perform the attitude tracking function of spacecraft. A sliding mode control law was established for the high-inertia appendages to maintain an appropriate angular velocity during rotation. Finally, the effectiveness of the proposed attitude control law was verified by numerical simulations for a spacecraft with high-inertia rotating appendages and symmetrical flexible solar panels.
This paper focuses on the attitude control problems of spacecraft with external interference and platform actuator failure. The Lagrange method is used to establish dynamic models of complex spacecraft composed of rotating appendages and platform, and the quaternion is used to describe spacecraft attitude kinematics. Second, a fault-tolerant control algorithm that combined adaptive fuzzy control with finite time sliding mode is proposed for the spacecraft platform, and fixed-time control schemes are proposed for rotating parts to achieve stable rotation of the spacecraft components relative to the platform. Finally, a numerical simulation is performed to verify the superiority and effectiveness of the proposed control laws, and comparisons with other control methods are presented.
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