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.

中文翻译：

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具有高惯性旋转附件的刚柔耦合航天器的非奇异积分滑模姿态控制

这项研究解决了具有高惯性旋转附件的刚性-挠性航天器姿态跟踪控制的挑战。拉格朗日方法用于建立航天器的运动学和动力学模型。考虑了航天器的平移和旋转，太阳能电池板的振动以及由旋转附件引起的不平衡，这引起了复杂的控制问题。为了解决复杂的控制问题，提出了一种新颖的，快速的非奇异积分滑模控制方法来执行航天器的姿态跟踪功能。针对高惯性附件建立了滑模控制律，以在旋转过程中保持适当的角速度。最后，