AIR DATA AIDED INERTIAL MEASUREMENT UNIT

• US 20180052006A1
• Filed: 08/22/2016
• Published: 02/22/2018
• Est. Priority Date: 08/22/2016
• Status: Active Grant

• Current Assignee: Rosemount Aerospace, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Rosemount Aerospace, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Ell, Todd
• Granted Patent: US 10,101,174 B2
• Time in Patent Office: Days
• CPC Class Codes: G01C 21/185 for gravity
• CPC Class Codes: G01C 25/00 Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass testing, calibrating or compensating compasses G01C17/38
• CPC Class Codes: G01P 21/00 Testing or calibrating of apparatus or devices covered by the preceding groups
• CPC Class Codes: G01P 5/00 Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft application of speed-measuring devices for measuring volume of fluid G01F

Abstract

An inertial measurement unit (IMU) includes an inertial sensor assembly including a plurality of accelerometers and a plurality of rate gyroscopes, an inertial sensor compensation and correction module, and a Kalman estimator module. The inertial sensor compensation and correction module is configured to apply a set of error compensation values to sensed acceleration and rotational rate to produce a compensated acceleration and a compensated rotational rate of the IMU. The Kalman estimator module is configured to determine a set of error correction values based on a difference between a change in integrated acceleration of the IMU and a change in true airspeed of the IMU. The inertial sensor compensation and correction module is further configured to apply the set of error correction values to each of the compensated acceleration and the compensated rotational rate to output an error-corrected acceleration and an error-corrected rotation rate.

Claims

1. An inertial measurement unit (IMU) comprising:

an inertial sensor assembly comprising;

a plurality of accelerometers, each of the plurality of accelerometers configured to sense acceleration of the IMU along one of a plurality of axes; and

a plurality of rate gyroscopes, each of the plurality of rate gyroscopes configured to sense rotational rate of the IMU along one of the plurality of axes;

an inertial sensor compensation and correction module configured to apply a set of error compensation values to acceleration sensed by the plurality of accelerometers and to rotational rate sensed by the plurality of rate gyroscopes to produce a compensated acceleration and a compensated rotational rate of the IMU; and

a Kalman estimator module configured to;

determine a change in integrated acceleration of the IMU over a time interval based on the compensated acceleration and the compensated rotational rate of the IMU;

determine a set of error correction values based on a difference between the change in the integrated acceleration of the IMU and a change in true airspeed of the IMU; and

provide the set of error correction values to the inertial sensor compensation and correction module;

wherein the inertial sensor compensation and correction module is further configured to;

apply the set of error correction values to each of the compensated acceleration and the compensated rotational rate to produce an error-corrected acceleration and an error-corrected rotational rate; and

output the error-corrected acceleration and the error-corrected rotational rate.

2. The IMU of claim 1,

wherein the Kalman estimator module is configured to determine the set of error correction values via an extended Kalman filter that utilizes the difference between the change in the integrated acceleration of the IMU and the change in the true airspeed of the IMU as input and produces the set of error correction values as output.

3. The IMU of claim 1,

wherein the inertial sensor assembly further comprises a plurality of temperature sensors configured to sense temperature of an operating environment of the plurality of accelerometers and the plurality of rate gyroscopes;

wherein the set of error compensation values comprises temperature-dependent error compensation values; and

wherein the inertial sensor compensation and correction module is configured to apply the set of error compensation values by determining the temperature-dependent error compensation values based on sensed temperature from each of the plurality of temperature sensors.

4. The IMU of claim 3,

wherein the temperature-dependent error compensation values comprise temperature-dependent scale factor error compensation values, temperature-dependent bias error compensation values, and temperature-dependent non-linearity error compensation values for each of the plurality of accelerometers and each of the plurality of rate gyroscopes.

5. The IMU of claim 4,

wherein each of the temperature-dependent scale factor error compensation values corresponds to an error in a slope of sensor output over a temperature range for a respective one of the plurality of accelerometers and the plurality of rate gyroscopes;

wherein each of the temperature-dependent bias error compensation values corresponds to a non-zero offset error of sensor output over the temperature range for a respective one of the plurality of accelerometers and the plurality of rate gyroscopes; and

wherein each of the temperature-dependent non-linearity error compensation values corresponds to a non-linearity of the sensor output over the temperature range for a respective one of the plurality of accelerometers and the plurality of rate gyroscopes.

6. The IMU of claim 1,

wherein the set of error compensation values comprises a non-orthogonality error compensation value corresponding to a non-orthogonality error of the plurality of axes.

7. The IMU of claim 1,

wherein the plurality of axes comprises a first plurality of axes defining a sensor axis reference frame;

and

wherein the Kalman estimator module is configured to determine the change in the integrated acceleration of the IMU by;

transforming the compensated acceleration from the sensor axis reference frame to a body axis reference frame defined by a second plurality of axes aligned with respect to a moving body that includes the IMU; and

integrating the compensated acceleration in the body axis reference frame over the time interval.

8. The IMU of claim 1,

wherein the Kalman estimator module is further configured to determine the set of error correction values by removing an effect of gravity from the difference between the change in the integrated acceleration of the IMU and the change in the true airspeed of the IMU.

9. The IMU of claim 1,

wherein the Kalman estimator module is further configured to determine the set of error correction values by removing an effect of Coriolis acceleration forces from the difference between the change in the integrated acceleration of the IMU and the change in the true airspeed of the IMU.

11. A method comprising:

sensing acceleration of an inertial measurement unit (IMU) along a plurality of axes via a plurality of accelerometers of the IMU;

sensing rotational rate of the IMU along the plurality of axes via a plurality of rate gyroscopes of the IMU;

applying a set of error compensation values to each of the sensed acceleration and the sensed rotational rate to produce a compensated acceleration and a compensated rotational rate of the IMU;

determining a change in integrated acceleration of the IMU over a time interval based on the compensated acceleration and the compensated rotational rate of the IMU;

determining a set of error correction values based on a difference between the change in the integrated acceleration of the IMU and a change in true airspeed of the IMU;

applying the set of error correction values to each of the compensated acceleration and the compensated rotational rate to produce an error-corrected acceleration and an error-corrected rotational rate; and

outputting the error-corrected acceleration and the error-corrected rotational rate.

10. The IMU of claim 11,

wherein the plurality of accelerometers comprises three accelerometers;

wherein the plurality of rate gyroscopes comprises three rate gyroscopes;

wherein the plurality of axes comprises three axes;

wherein each of the three accelerometers is aligned to sense the acceleration of the IMU along one of the three axes; and

wherein each of the three rate gyroscopes is aligned to sense the rotational rate of the IMU along one of the three axes.

12. The method of claim 11,

wherein determining the set of error correction values comprises determining the set of error correction values via an extended Kalman filter that utilizes the difference between the change in the integrated acceleration of the IMU and the change in the true airspeed of the IMU as input and produces the set of error correction values as output.

13. The method of claim 11, further comprising:

sensing temperature of an operating environment of the plurality of accelerometers and the plurality of rate gyroscopes via a plurality of temperature sensors of the IMU;

wherein the set of error compensation values comprises temperature-dependent error compensation values; and

wherein applying the set of error compensation values comprises determining the temperature-dependent error correction values based on the sensed temperature from each of the plurality of temperature sensors.

14. The method of claim 13,

wherein the temperature-dependent error compensation values comprise temperature-dependent scale factor error compensation values, temperature-dependent bias error compensation values, and temperature-dependent non-linearity error compensation values for each of the plurality of accelerometers and each of the plurality of rate gyroscopes.

15. The method of claim 14,

wherein each of the temperature-dependent scale factor error compensation values corresponds to an error in a slope of sensor output over a temperature range for a respective one of the plurality of accelerometers and the plurality of rate gyroscopes;

wherein each of the temperature-dependent bias error compensation values corresponds to a non-zero offset error of sensor output over the temperature range for a respective one of the plurality of accelerometers and the plurality of rate gyroscopes; and

wherein each of the temperature-dependent non-linearity error compensation values corresponds to a non-linearity of the sensor output over the temperature range for a respective one of the plurality of accelerometers and the plurality of rate gyroscopes.

16. The method of claim 11,

wherein the set of error compensation values comprises a non-orthogonality error compensation value corresponding to a non-orthogonality error of the plurality of axes.

17. The method of claim 11,

wherein the plurality of axes comprises a first plurality of axes defining a sensor axis reference frame;

and

wherein determining the change in the integrated acceleration of the IMU comprises;

transforming the compensated acceleration from the sensor axis reference frame to a body axis reference frame defined by a second plurality of axes aligned with respect to a moving body that includes the IMU; and

integrating the compensated acceleration in the body axis reference frame over the time interval.

18. The method of claim 11,

wherein determining the set of error correction values comprises removing an effect of gravity from the difference between the change in the integrated acceleration of the IMU and the change in the true airspeed of the IMU

19. The method of claim 11,

wherein determining the set of error correction values comprises removing an effect of Coriolis acceleration forces from the difference between the change in the integrated acceleration of the IMU and the change in the true airspeed of the IMU.

20. The method of claim 11,

wherein the plurality of accelerometers comprises three accelerometers;

wherein the plurality of rate gyroscopes comprises three rate gyroscopes;

wherein the plurality of axes comprises three axes;

wherein each of the three accelerometers is aligned to sense the acceleration of the IMU along one of the three axes; and

wherein each of the three rate gyroscopes is aligned to sense the rotational rate of the IMU along one of the three axes.