Control moment gyroscope
AssigneeHoneywell International Inc.
InventorsCarlos J. Stevens, Stephen E. Fiske
Life of this patent
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Abstract
A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes a stator housing, an inner gimbal assembly disposed in the stator housing, and a torque motor coupled to the stator housing and at least partially disposed around an intermediate portion of the inner gimbal assembly. The torque motor is configured to rotate the inner gimbal assembly about a gimbal axis.
Claims17
A control moment gyroscope (CMG) for deployment on a spacecraft, the CMG comprising:
- a stator housing;
- an inner gimbal assembly disposed in the stator housing, the inner gimbal assembly comprising:
- an inner gimbal assembly housing rotatably coupled to the stator housing;
- a rotor rotatably coupled to the inner gimbal assembly housing;
- and
- a spin motor coupled to the inner gimbal assembly housing and configured to rotate the rotor about a spin axis;
- and
- a torque motor coupled to the stator housing and surrounding an intermediate portion of the inner gimbal assembly, the torque motor configured to rotate the inner gimbal assembly about a gimbal axis.
A control moment gyroscope (CMG) for deployment on a spacecraft, the CMG comprising:
- a stator housing;
- an inner gimbal assembly, comprising:
- an inner gimbal assembly housing rotatably mounted in the stator housing;
- a rotor rotatably coupled to the inner gimbal assembly housing;
- and
- a spin motor coupled to the inner gimbal assembly housing and configured to rotate the rotor about a spin axis;
- and
- a torque motor residing between the stator housing and the inner gimbal assembly housing, the torque motor circumferentially disposed around a central portion of the inner gimbal assembly housing and configured to rotate the inner gimbal assembly about a gimbal axis;
- and
- a rotation sensor coupled to a surface of the stator housing and to an external surface of the inner gimbal assembly housing, the rotation sensor configured to monitor at least one rotational characteristic of the inner gimbal assembly.
A control moment gyroscope (CMG) for deployment on a spacecraft, the CMG comprising:
- a stator housing, comprising:
- a first end portion;
- a second end portion substantially opposite the first end portion;
- and
- an intermediate portion between the first end portion and the second end portion;
- an inner gimbal assembly disposed in the stator housing;
- a torque motor coupled to the intermediate portion of the stator housing, the torque motor disposed at least partially around the inner gimbal assembly;
- a signal module assembly coupled to the second end portion of the stator housing;
- and
- a rotation sensor mounted within the first end portion of the stator housing proximate the inner gimbal assembly, the rotation sensor configured to monitor a rotational characteristic of the inner gimbal assembly.
Dependencies are inferred from the claim text.