@techreport{oai:jaxa.repo.nii.ac.jp:00044896,
 author = {吉村, 庄市 and 上村, 平八郎 and 山中, 龍夫 and YOSHIMURA, Shoichi and KAMIMURA, Heihachiro and YAMANAKA, Tatsuo},
 month = {Nov},
 note = {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},
 title = {An Experimental Investigation of a Single-Degree-of-Freedom Control Moment Gyro on a Pendulum},
 year = {1980}
}