Dynamic attitude measurement method and apparatus

• US 6,647,352 B1
• Filed: 05/01/2002
• Issued: 11/11/2003
• Est. Priority Date: 06/05/1998
• Status: Expired due to Term

• Current Assignee: Aceinna Transducer Systems Company Limited
• Original Assignee: Crossbow Technology Incorporated (Moog Incorporated)
• Inventors: Horton, Michael A.
• Primary Examiner(s): Barlow, John
• Assistant Examiner(s): Washburn, Douglas N
• Application Number:
  US10/136,955
• Time in Patent Office: 559 Days
• Field of Search: 333/38, 701/200, 702/150, 702/151, 702/153
• US Class Current: 702/151
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems

Abstract

A method and system attitude of an accelerating object by measuring acceleration with accelerometers in three orthogonal axes and measuring angular rate with angular rate sensors disposed about each such axis to compute attitude of the object accurately relative to a vertical axis. A processor updates a quaternion representation of attitude based upon the angular rate of the object, and a corrective rate signal is determined from level frame acceleration as a reference for a Kalman filter in calculating the attitude of the object.

Claims

1. A method for determining an attitude of an accelerating object exclusively from acceleration and angular rate, comprising:

determining an angular rate of the object to obtain a quaternion representation of attitude;

converting the quaternion in to a direction cosine matrix;

determining a level frame acceleration value of the object based upon the direction cosine matrix and an acceleration of the object;

supplying attitude error and rate sensor bias estimates to a Kalman filter operating on the level frame acceleration value as a reference to determine the attitude of the object.

2. The method of claim 1 in which attitude error estimate includes determining acceleration magnitude from acceleration information along multiple orientation axes excluding gravity orientation;

and

invalidating attitude determination in response to the acceleration magnitude exceeding a selected value as indicative of a dynamic maneuver.

3. The method according to claim 1 in which attitude determination is invalidated in response to yaw rate information exceeding a selected value as indicative of a turn maneuver.

4. The method according to claim 1 including also supplying heading information to the Kalman filter operating on the level frame acceleration value as a reference to determine the attitude of the object.

5. The method according to claim 4 in which heading information includes compass heading data.

6. The method according to claim 4 in which heading information includes magnetometer data.

7. The method according to claim 4 in which heading information includes GPS information.

8. The method according to claim 3 in which yaw rate information supplied to the Kalman filter prior to the indicated turn maneuver is supplied for the duration of the yaw rate information exceeding the selected value.

9. The method according to claim 8 in which the state model noise covariance of the Kalman filter is lowered during the acceleration magnitude exceeding the selected value.

10. The method according to claim 8 in which the weighting of the accelerometer attitude reference is lowered in the Kalman filter during the yaw rate information exceeding the selected value.

11. The method according to claim 1 in which the determination of angular rate of an object includes manipulating the object through a predefined set of maneuvers including an initial position as the final position of the maneuvers, and estimating calibration parameters therefrom.

12. The method according to claim 11 in which a Kalman filter calculates the calibration parameters from acceleration and angular rate data from the object as manipulated through the set of maneuvers.