並列タイトル等コントロール・モーメント・ジャイロの試作と振子装置による制御性能の測定
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-641
一般注記A control moment gyro(CMG) is one of the promising actuators for attitude control of spacecrafts. Attempts have been made to develop single-degree-of-freedom CMGs in our laboratory. The first one is a versional one of a senser gyro, rate-integrating gyro, which was used for the spin table of launching vehicle M. The angular momentum is very small and the linearity of torqer and pick-off becomes poor for the large offset of gimbal angle. The second one has been made, based on the investigations of the first one. The angular momentum has been increased up to 7.90×10(exp 6)gr-cm2-s-1, and the linearity has been improved for the wide range of ±60 degrees of gimbal angle. An operational test as an integrating gyro has been carried out on a servo table. Then, performance as a CMG has been investigated on a pendulum. Two kinds of experiments have been carried out through a coupling oscillation between the CMG and the pendulum. One is a stabilization, and the other is an excitation of the pendulum. Both of them have been carried out by a main control torque (H-cosθg term) and a coupling control torque (H-sinθg term) respectively.
資料番号: NALTR0641000
レポート番号: NAL TR-641
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ