Escaping singularities in a satellite attitude control

Details Escaping singularities in a satellite attitude control Escaping singularities in a satellite attitude control

1998-03-16

2000-04-11

Cuchlinski, Jr., William A.

Aeronautics and astronautics

Spacecraft

Attitude control

244169, 244176, 701 13, 701 4, 701 8, B64G 128

Patent

active

060479272

ABSTRACT:
Control moment gyros in an array are rotated to reorient a satellite by an attitude signal. If the signal causes a gyro to have position that will produce a singularity in attitude control, a disturbance is introduced into the signal to avoid the singularity.

REFERENCES:
patent: 5100084 (1992-03-01), Rahn et al.
patent: 5248118 (1993-09-01), Cohen et al.
patent: 5269483 (1993-12-01), Flament
patent: 5354016 (1994-10-01), Goodzeit et al.
patent: 5875676 (1999-03-01), Bailey et al.

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