Dual Bridge Angular Accelerometer

• US 20050000284A1
• Filed: 07/02/2003
• Published: 01/06/2005
• Est. Priority Date: 07/02/2003
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Gunther, Thomas J., Campell, Ray F., Wada, Joan D.
• Granted Patent: US 6,895,817 B2
• Time in Patent Office: Days
• US Class Current: 73/488
• CPC Class Codes: G01P 15/0888 for indicating angular acceleration
• CPC Class Codes: G01P 15/125 by capacitive pick-up
• CPC Class Codes: G01P 15/18 in two or more dimensions

Abstract

An accelerometer includes an inertial platform maintaining an attitude in response to a platform stabilizing controller signal and defining a spin axis and a reference plane. An accelerometer, coupled to the inertial platform a distance from the spin axis, defines a flex axis, which is perpendicular to the stability axis. The accelerometer generates an accelerometer signal in response to acceleration of the accelerometer. A second accelerometer defines a second flex axis also perpendicular to the stability axis, and is also coupled to the inertial platform a distance from the spin axis. The second accelerometer generates a second accelerometer signal in response to acceleration of the second accelerometer. A controller, including an angular acceleration signal generator, receives the first accelerometer signal and the second accelerometer signal and generates an angular acceleration signal from a difference in amplitudes between the first accelerometer signal and the second accelerometer signal. The controller further generates the platform stabilizing controller signal in response to the first acceleration signal and the second acceleration signal.

Claims

1. An accelerometer system comprising:

an inertial platform defining a reference plane, a spin axis, and a stability axis, wherein said spin axis is within said reference plane and said stability axis is perpendicular to said reference plane, said inertial platform maintaining a minimized rotation in response to a platform stabilizing controller signal;

a first accelerometer defining a first flex axis perpendicular to said stability axis, said first accelerometer coupled to said inertial platform a first distance from said spin axis, said first accelerometer generating a first accelerometer signal in response to acceleration of said first accelerometer;

a second accelerometer defining a second flex axis perpendicular to said stability axis, said second accelerometer coupled to said inertial platform a second distance from said spin axis, said second accelerometer generating a second accelerometer signal in response to acceleration of said second accelerometer; and

a controller comprising an angular acceleration signal generator, said controller receiving said first accelerometer signal and said second accelerometer signal, said angular acceleration signal generator generating an angular acceleration signal from a difference in amplitudes of said first accelerometer signal and said second accelerometer signal, said controller further generating said platform stabilizing controller signal in response to said first acceleration signal and said second acceleration signal.

2. The system of claim 1 wherein said first accelerometer generates a first linearized digital output signal in response to acceleration of said first accelerometer, and said second accelerometer generates a second linearized digital output signal in response to acceleration of said second accelerometer.

3. The system of claim 1, wherein said controller comprises a first compensator compensating for a non-linearity within said angular acceleration signal and generating a first digital word proportional to an angular acceleration about said spin axis.

4. The system of claim 3 wherein said controller controls a missile system in response to said first digital word.

5. The system of claim 1, wherein said first accelerometer is a first bridge accelerometer and said second accelerometer is a second bridge accelerometer.

6. The system of claim 1, wherein said first accelerometer and said second accelerometer are equidistant from said spin axis.

7. The system of claim 1, wherein said inertial platform comprises a gimbal or plurality of gimbals.

8. A method for operating a dual bridge accelerometer system defining a z spin axis comprising:

generating a first accelerometer signal from a first bridge accelerometer;

generating a second accelerometer signal from a second bridge accelerometer;

controlling said first bridge accelerometer and said second accelerometer such that said first bridge accelerometer and said second bridge accelerometer remain in an xz-plane;

generating a first output word from said first bridge accelerometer equivalent to a sum of a first linear acceleration and a first tangential acceleration acting on said first bridge accelerometer;

generating a second output word from said second bridge accelerometer equivalent to a sum of said first linear acceleration and said first tangential acceleration acting on said second bridge accelerometer;

averaging said first output word and a negative value of said second output word; and

generating an angular acceleration signal.

9. The method of claim 8 further comprising compensating for non-linearities within said angular acceleration signal.

10. The method of claim 8 further comprising generating a digital word proportional to an angular acceleration around said spin axis.

11. The method of claim 8 further comprising activating an object control device in response to said digital word.

12. The method of claim 8 averaging said first output word and a negative value of said second output word further comprises generating a difference of amplitudes of said first output word and said second output word.

13. An accelerometer system comprising:

an inertial platform defining a reference plane, a spin axis, and a stability axis, wherein said spin axis is within said reference plane and said stability axis is perpendicular to said reference plane, said inertial platform maintaining a minimized rotation in response to a platform stabilizing controller signal;

a first bridge accelerometer defining a first flex axis perpendicular to said stability axis, said first accelerometer coupled to said inertial platform a first distance from said spin axis, said first accelerometer generating a first linearized digital output signal in response to acceleration of said first accelerometer;

a second bridge accelerometer defining a second flex axis perpendicular to said stability axis, said second bridge accelerometer coupled to said inertial platform a second distance from said spin axis, said second bridge accelerometer generating a second linearized digital output signal in response to acceleration of said second bridge accelerometer; and

a controller comprising a first compensator, said controller receiving said first linearized digital output signal and said second linearized digital output signal,

said controller generating an angular acceleration signal from a difference in amplitudes of said first linearized digital output signal and said second linearized digital output signal,

said first compensator compensating for a non-linearity within said angular acceleration signal and generating a first digital word proportional to a rotational acceleration about said spin axis,

said controller further generating said platform stabilizing controller signal in response to said first linearized digital output signal and said second linearized digital output signal, and

said controller controlling a missile system in response to said first digital word.

14. The system of claim 13, wherein said controller is a missile computer.

15. The system of claim 13, wherein said first compensator is a linear lookup table providing compensation information to said controller.

16. The system of claim 13, wherein said first bridge accelerometer and said second bridge accelerometer are equidistant from said spin axis.

17. The system of claim 13, wherein said first bridge accelerometer is on a first plate, and said second bridge accelerometer is on a second plate.

18. The system of claim 17, wherein said first plate faces a yz, xz, or yx plane.