Method for reducing bias error in a vibrating structure gyroscope

• US 7,240,533 B2
• Filed: 02/01/2005
• Issued: 07/10/2007
• Est. Priority Date: 02/04/2004
• Status: Active Grant

• Current Assignee: Atlantic Inertial Systems Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: BAE Systems Plc
• Inventors: Fell, Christopher Paul, Kazer, Andrew
• Primary Examiner(s): NOLAND, THOMAS
• Application Number:
  US10/527,454
• Publication Number:
  US 20060260382A1
• Time in Patent Office: 889 Days
• Field of Search: 7350412-50413, 73 137- 138, 73/17.7, 734/97, 735/142.9, 74/56.D, 702/106, 333/18
• US Class Current: 73/1.38
• CPC Class Codes: G01C 19/5677 of essentially two-dimensional vibrators, e.g. ring-shaped vibrators

Abstract

A method for reducing bias error in a Vibrating Structure Gyroscope having a vibrating structure, a primary drive for putting the vibrating structure into carrier mode resonance, a primary pick-off device for sensing carrier mode motion, a secondary pick-off for sensing response mode vibration of the vibrating structure in response to applied rotation rate, a secondary drive for applying a force to control the response mode motion, closed loop primary control loops for maintaining a fixed amplitude of motion at the primary pick-off device, for maintaining the drive frequency at the resonance maximum, and secondary control loops for maintaining a null at the secondary pick-off device. In the method the ratio SF_QUAD over SF_IN-PHASE is measured from the secondary control loop to provide a direct measurement of Sin (φ_SD+φ_PPO), according to the relationship SF_QUAD=SF_IN-PHASE×Sin (φ_SD+_PPO) where SF_QUAD is the quadrature scalefactor SF_IN-PHASE is the in-phase scalefactor, φ_SD is the phase error in the secondary drive and φ_PPO is the phase error in the primary pick-off device. The total phase error φ_E is obtained directly from the measured Sin (φ_SD+φ_PPO) according to the relationship; φ_E=φ_SD+φ_PPO and phase corrections applied to the secondary drive and/or primary pick-off device to reduce the phase error φ_E, and hence the quadrature bias error, to enhance the performance of the gyroscope.

Claims

1. A method for reducing bias error in a Vibrating Structure Gyroscope having a vibrating structure, primary drive means for putting the vibrating structure into carrier mode resonance, primary pick-off means for sensing carrier mode motion, secondary pick-off means for sensing response mode vibration of the vibrating structure in response to applied rotation rate, secondary drive means for applying a force to control the response mode motion, closed loop primary control loops for maintaining a fixed amplitude of motion at the primary pick-off means and for maintaining the drive frequency at the resonance maximum, and secondary control loops for maintaining a null at the secondary pick-off means, in which the ratio SF_QUAD divided by SF_IN-PHASE is measured from the secondary control loop to provide a direct measurement of Sin (φ

_SD+φ

_PPO), according to the relationship;

SF_QUAD=SF_IN-PHASE×

Sin (φ

_SD+φ

_PPO)

where SF_QUAD is the quadrature scalefactor, SF_IN-PHASE is the in-phase scalefactor, φ

_SD is the phase error in the secondary drive means and φ

_PPO is the phase error in the primary pick-off means, the total phase error φ

_E is obtained directly from the measured Sin (φ

_SD+φ

_PPO) according to the relationship;

φ

_E=φ

_SD+φ

_PPO

and phase corrections are applied to one of the secondary drive means and the primary pick-off means to reduce the phase error φ

_E and hence the quadrature bias error to enhance the performance of the gyroscope.

2. A method according to claim 1, when used with a gyroscope having a silicon vibrating structure.

3. A method according to claim 2, when used with a gyroscope having a substantially planar, substantially ring shaped vibrating structure.

4. A method according to claim 1, when used with a gyroscope having analogue primary and secondary control loops with variable value capacitors, in which the phase corrections are applied by varying the values of the variable value capacitors in the secondary control loop relating to the secondary drive means and/or the values of the variable value capacitors in the primary control loop relating to the primary pick-off means to adjust φ

_SD and/or φ

_PPO such that φ

_E is minimised in value.

5. A method according to claim 4, in which in-phase and quadrature signal components are each multiplied by Sin φ

_C0RR and Cos φ

_CORR, where φ

_CORR, is the phase correction, and the effective phase of each in-phase and quadrature channel adjusted according to the summations;

Quadrature_CORR=Quadrature×

Cos φ

_CORR+In-phase×

Sin φ

_CORR

and

In-phase_CORR=In-phase×

Cos φ

_CORR−

Quadrature×

Sin φ

_CORR.

6. A method according to claim 1, when used with a gyroscope having digital primary and secondary control loops, in which the phase corrections equal to φ

_E are applied to the secondary drive means via the secondary control loop in a manner such as to cross-couple in-phase and quadrature drive channels by an amount equal and opposite to the combined effect of the phase errors in the vibrating structure control system.

7. A method according to claim 1, when used with a gyroscope having digital primary and secondary control loops, in which the phase corrections equal to φ

_E are applied to the primary pick-off means by the primary control loop in a manner such as to cross-couple in-phase and quadrature drive channels by an amount equal and opposite to the combined effect of the phase errors in the vibrating structure control system.

8. A method according to claim 7, in which φ

_CORR is adjusted in accordance with operating temperature of the gyroscope to maintain φ

_E at a minimised value.

9. A Vibrating Structure Gyroscope having a vibrating structure, primary drive means for putting the vibrating structure into carrier mode resonance, primary pick-off means for sensing carrier mode motion, secondary pick-off means for sensing response mode vibration of the vibrating structure in response to applied rotation rate, secondary drive means for applying a force to control the response mode motion, closed loon primary control loops for maintaining a fixed amplitude of motion at the primary pick-off means and for maintaining the drive frequency at the resonance maximum, and secondary control loops for maintaining a null at the secondary pick-off means, in which the ratio SF_QUAD divided by SF_IN-PHASE is measured from the secondary control loon to provide a direct measurement of Sin (φ

_SD+φ

_PPO), according to the relationship;

SF_QUAD=SF_IN-PHASE×

Sin (φ

_SD×

φ

_PPO)

where SF_QUAD is the quadrature scalefactor, SF_IN-PHASE is the in-phase scalefactor, φ

_SD is the phase error in the secondary drive means and φ

_PPO is the phase error in the primary pick-off means, the total phase error φ

_E is obtained directly from the measured Sin (φ

_SD+φ

_PPO) according to the relationship;

φ

_E=φ

_SD+φ

_PPO

and phase corrections are applied to one of the secondary drive means and the primary pick-off means to reduce the phase error φ

_E and hence the quadrature bias error to enhance the performance of the gyroscope.