A CMG (60, 140) according to Claim 1 wherein a first plane transects the gimbal bearing (68, 154) and the rotor (76, 164), the first plane being substantially orthogonal to the gimbal axis (102, 160), the average thickness of the IGA housing (72, 156) as taken along the first plane being at least twice the average thickness of the gimbal bearing.ġ0.
A CMG (60, 140) according to Claim 1 wherein the IGA housing (72, 156) comprises a substantially hemi-spherical body having first end portion coupled to the stator assembly (62, 142) and a second end portion coupled to the rotor (76, 164), the first end portion having a smaller outer diameter than does the second end portion.ĩ. A CMG (60, 140) according to Claim 6 wherein the torque module assembly (98, 152) is disposed between the signal module assembly (100, 150) and the IGA - (64, 144).Ĩ.
A CMG (60, 140) according to Claim 1 further comprising a signal module assembly (100, 150) coupled to the stator assembly housing (96, 146) substantially adjacent the torque module assembly (98, 152).ħ. A CMG (60, 140) according to Claim 4 wherein the IGA housing (72, 156) includes a sloped outer surface having an average outer diameter, and wherein the inner diameter of the substantially annular bearing is greater than the average outer diameter of the sloped outer surface.Ħ. A CMG (60, 140) according to Claim 1 wherein the gimbal bearing (68, 154) comprises a substantially annular bearing disposed around the IGA housing (72, 156).ĥ. A CMG (60, 140) according to Claim 2 wherein the spacecraft interface (118, 148) and the gimbal bearing (68, 154) at least partially overlap.Ĥ. A CMG (60, 140) according to Claim 1 further comprising a spacecraft interface (118, 148) located on the stator assembly housing (96, 146) substantially adjacent the gimbal bearing (68, 154).ģ. A control moment gyroscope (CMG) (60, 140) for deployment on a spacecraft, the CMG comprising:Īn inner gimbal assembly (IGA) (64, 144), comprising:Ī rotor (76, 164) rotatably coupled to the IGA housing andĪ spin motor (86) coupled to the IGA housing and configured to rotate the rotor about a spin axis (88, 170) andĪ stator assembly housing (96, 146) rotatably coupled to the IGA housing Ī torque module assembly (98, 152) coupled to the stator assembly housing and configured to rotate the IGA about a gimbal axis (102, 160) Ĭharacterised in that the CMG further comprises:Ī gimbal bearing (68, 154) disposed between the IGA housing and the stator assembly housing, the gimbal bearing residing between the spin axis and the torque module assembly, and the distance between the gimbal bearing and the spin axis being less than the distance between the gimbal bearing and the torque module assembly.Ģ.