Rate gyro calibration method and apparatus for a three-axis stab

Details Rate gyro calibration method and apparatus for a three-axis stab Rate gyro calibration method and apparatus for a three-axis stab

1994-04-20

1996-10-08

Barefoot, Galen L.

Aeronautics and astronautics

Spacecraft

With special crew accommodations

73 1D, 7350408, B64G 122

Patent

active

055622666

ABSTRACT:
Method and apparatus for calibration of a set of rate gyros on a three-axis stabilized satellite in orbit, the satellite including an attitude sensing system including the set of rate gyros, a set of actuators and control logic adapted to apply to the set of actuators control signals U derived from measurement signals M supplied by the attitude sensing system. From a time t.sub.0 satellite attitude errors (E1) relative to a reference frame of reference and constant drifts (E2) of the set of rate gyros about three axes (XYZ) of the satellite are estimated conjointly. The estimated values of the attitude errors and the difference between the measured speeds (.omega.) of the set of rate gyros and the estimated values of the constant drifts are applied in real time to the control logic and these estimated values of the constant drifts are stored when they become constant to within a first predetermined tolerance and the estimated values of the attitude errors become constant to within a second tolerance.

REFERENCES:
patent: 3599495 (1971-08-01), Brown
patent: 4393710 (1983-07-01), Bernard
patent: 4437047 (1984-03-01), Smay
patent: 4869092 (1989-09-01), Bernard et al.
patent: 5277385 (1994-01-01), Flamart
patent: 5279483 (1994-01-01), Blancke et al.
patent: 5421187 (1995-06-01), Morgan

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