High torque double gimbal control moment gyro

Details High torque double gimbal control moment gyro High torque double gimbal control moment gyro

1993-07-16

1995-08-01

Barefoot, Galen L.

Aeronautics and astronautics

Spacecraft

Attitude control

74 54, B65G 128

Patent

active

054374200

ABSTRACT:
A system and related method is provided for rapidly repointing spacecraft through the application of a high torque, of a gyroscope in which braking means (20, 22) provided on a gimbal (16, 18) is actuated simultaneously with the actuation of the torque motor (24, 26) to achieve amplification of the control moment imparted to the gyroscope (10). Because only one brake (20, 22) may be actuated at a time in a double gimbal gyroscope system having a single spin wheel (12), actuation of the brake ( 20, 22) for each of the two axes is sequential. However in a system having redundant torque motors (24, 26), re-pointing of the spacecraft may be achieved using the simultaneous braking and torque application method of the present invention without increasing the repointing time by applying torque to a gimbal (16) rotating about one axis of the first spin wheel (12) at the same time that torque is applied to a gimbal (18) rotating around the orthogonal axis of the redundant spin wheel (12).

REFERENCES:
patent: 3424401 (1969-01-01), Maurer
patent: 3795150 (1974-03-01), Eckhardt
patent: 3813067 (1974-05-01), Mork
patent: 4911385 (1990-03-01), Agrawal et al.
patent: 5259577 (1993-11-01), Achkar et al.

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