柔軟衛星のモデリングと姿勢制御 : 1軸エアテーブルを用いた実験的検討

概要

論文の詳細を見る
This paper experimentally studies modeling and control of a class of flexible spacecraft having elastic appendages. First. an equation of motion of the flexible spacecraft is derived from experimental data of flexible appendages. and modal analysis using unconstrained modes is applied to the equation in order to obtain the reduced order model. Subsequently, the characteristic transfer function method based on the design freedom is adopted to design the controller. The effectiveness of the controller derived by this method is demonstrated in control experiments by using a flexible spacecraft model on a single-axis air-table. The evaluation for the results of the control experiments is made concerning with vibration control, suppression of spillover instability, and step response of attitude angle.
社団法人日本機械学会の論文
1988-11-25