Gyroless yaw control system for a three axis stabilized, zero-mo

Details Gyroless yaw control system for a three axis stabilized, zero-mo Gyroless yaw control system for a three axis stabilized, zero-mo

1991-11-25

1993-04-27

Peters, Jr., Joseph F.

Aeronautics and astronautics

Spacecraft

Attitude control

244171, 364434, B64G 128, B64G 136

Patent

active

052055183

ABSTRACT:
A satellite attitude control system is usable in the absence of any inertial yaw attitude reference, such as a gyroscope, and in the absence of a pitch bias momentum. Both the roll-yaw rigid body dynamics and the roll-yaw orbit kinematics are modelled. Pitch and roll attitude control are conventional. The model receives inputs from a roll sensor, and roll and yaw torques from reaction wheel monitors. The model produces estimated yaw which controls the spacecraft yaw attitude.

REFERENCES:
patent: 3998409 (1976-12-01), Pistiner
patent: 4021716 (1977-03-01), Rue
patent: 4038527 (1977-07-01), Brodie et al.
patent: 4084772 (1978-04-01), Muhlfelder
patent: 4437047 (1984-03-01), Smay
patent: 4537375 (1985-08-01), Chan
patent: 4723735 (1988-02-01), Eisenhaure et al.
patent: 5025381 (1991-06-01), Goodzeit et al.
patent: 5098041 (1992-03-01), Uetrecht

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