柔軟構造物をもつ宇宙機の近似最短時間姿勢マヌーバに関する研究

抄録

This paper examines a method for approximating the minimum-time attitude maneuvers of spacecraft with flexible structures. For an attitude maneuver around a single axis, we considered a scenario in which a symmetric step-like torque input is applied with respect to the half-maneuver time. We propose a method for determining an input that achieves attitude change in nearly the minimum time. This input ensures that the spacecraft's angular velocity as well as the mode coordinates of the structural vibrations and their time derivatives reach zero at the final time. In addition, we propose a method to extend the robustness of the input to uncertainties in the frequency and damping ratio of vibration modes. Simulations of the proposed method were conducted using a spacecraft model. The results demonstrate that the spacecraft can change its attitude without any residual vibrations under the condition of no modeling errors and exhibit robustness against uncertainties in the vibration frequency and damping ratio.