| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a control moment gyroscope (CMG) achieving an efficient rotor-to-spacecraft load path in a relatively compact and lightweight envelope. <P>SOLUTION: The CMG 60 includes an inner gimbal assembly (IGA) 64 including an IGA housing 72, a rotor 76 rotatably coupled to the IGA housing, and a spin motor 86 coupled to the IGA housing and configured to rotate the rotor about a spin axis 88. The CMG further includes a stator assembly 62 including a stator assembly housing 96 rotatably coupled to the IGA housing, and a torque module assembly 98 coupled to the stator assembly housing and configured to rotate the IGA about a gimbal axis 102. A gimbal bearing 68 is located between the spin axis and the torque module assembly so that a distance between the gimbal bearing and the spin axis is less than a distance between the gimbal bearing and the torque module assembly. <P>COPYRIGHT: (C)2009,JPO&INPIT</p> |
