Closed loop roll/yaw control system for satellites

Details Closed loop roll/yaw control system for satellites Closed loop roll/yaw control system for satellites

1975-12-12

1977-12-13

Kunin, Stephen G.

Aeronautics and astronautics

Spacecraft

Attitude control

364434, 244 32, B64G 110

Patent

active

040625095

ABSTRACT:
Attitude of a pitch momentum biased satellite in a low inclination orbit is controlled by a closed loop magnetic torquing control system. A magnetic dipole oriented perpendicular to the satellite's pitch axis in the roll/yaw plane and at a predetermined azimuth angle relative to the roll axis minimizes roll and yaw errors by interaction with the earth's magnetic field. Signals from an on-board roll attitude sensor are used by satellite mounted detection and driver circuits to control the compensating torques. Magnetic torquing is initiated whenever the roll error as measured by the roll attitude sensor exceeds a predetermined threshold.

REFERENCES:
patent: 3232561 (1966-02-01), Adams
patent: 3429524 (1969-02-01), Buckingham et al.
patent: 3575362 (1971-04-01), Hammond et al.
patent: 3765621 (1973-10-01), Shigehara
patent: 3834653 (1974-09-01), Perkel
patent: 3866025 (1975-02-01), Cavanagh

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