An Integrated Control Method for Flexible Components and Spacecraft Body

This paper proposes an integrated control method that encompasses both the flexible components and the spacecraft body to address the challenge of high-precision attitude control for spacecraft utilizing the motion of flexible components connected to the spacecraft body. The design of a feedback control law is conducted without increasing the complexity of the spacecraft. This approach leverages the rotary motion at the root of the flexible component to achieve effective attitude control for the spacecraft body, thereby facilitating integrated control between these elements. The efficiency of the proposed method is validated through numerical simulations.