Spacecraft control with skewed control moment gyros

Details Spacecraft control with skewed control moment gyros Spacecraft control with skewed control moment gyros

1995-01-05

1997-10-28

Barefoot, Galen L.

Aeronautics and astronautics

Spacecraft

Attitude control

B64G 128

Patent

active

056810121

ABSTRACT:
A method of and system for applying single gimbal control moment gyros to spacecraft attitude control employing two control moment gyros with nominal spin axes anti-parallel and gimbal axes displaced at a fixed angle in the plane normal to the nominal spin axes to achieve two orthogonal body fixed control torques using two wheels. If the gimbal axis displacement of each of three wheels is 120 degrees, two wheels provide independent uncoupled orthogonal two-axis control, and the third can substitute, in the event of failure, for either of the two requiring no change in control law or performance.

REFERENCES:
patent: 3471105 (1969-10-01), Yarber et al.
patent: 3741500 (1973-06-01), Liden
patent: 5012992 (1991-05-01), Salvatore
patent: 5279483 (1994-01-01), Blancke et al.
Cummings et al "Skewed Versus Orthogonal Reaction Wheels for Outer Planet Exploration" AAS Conf 1971.
Ramos, "Air Bearing Testing of a Skewed Reaction Wheel System for Attitude Control", CCMSAT Tech Rev vol. 9 No. 1 Spring 1979 pp. 157-202.

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