Control motion gyro with vibration isolation

Details Control motion gyro with vibration isolation Control motion gyro with vibration isolation

1996-09-27

1998-10-13

Barefoot, Galen L.

Aeronautics and astronautics

Spacecraft

Attitude control

74 5F, 74 55, B64G 128

Patent

active

058200789

ABSTRACT:
A control moment gyro having a housing enclosing a spinning momentum wheel. A rocking plate circumscribes the housing and is compliantly connected thereto by a set of isolator struts and non-contacting actuators which isolate the rocking plate from the inherent vibrations and oscillations of the momentum wheel. The rocking plate is pivotably connected to a gimbal ring about a first pivot axis normal to the spin axis of the momentum wheel. The gimbal ring is pivotably connected to the structure of the spacecraft about a second axis orthogonal to the spin axis and the first pivot axis. Actuators are provided to control the attitude of the housing relative to the rocking plate, the rocking plate relative to the gimbal ring, and the gimbal ring relative to the spacecraft.

REFERENCES:
patent: 3550395 (1970-12-01), Herzog et al.
patent: 3765631 (1973-10-01), Herbst et al.
patent: 4270393 (1981-06-01), Osborne et al.
patent: 4332365 (1982-06-01), Berk
patent: 4352481 (1982-10-01), Forward
patent: 4735296 (1988-04-01), Pinson
patent: 5368271 (1994-11-01), Kiunke et al.
patent: 5441222 (1995-08-01), Rosen

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