Technique to improve navigation performance through carouselling

• US 9,599,474 B2
• Filed: 04/06/2009
• Issued: 03/21/2017
• Est. Priority Date: 04/06/2009
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Bye, Charles T.
• Primary Examiner(s): Zeender, Florian
• Assistant Examiner(s): Haider, Fawaad
• Application Number:
  US12/419,156
• Publication Number:
  US 20100256907A1
• Time in Patent Office: 2,906 Days
• Field of Search: 701/505, 701/508, 701/509, 701/510, 701/1
• US Class Current: 1/1
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G01C 21/183 Compensation of inertial measurements, e.g. for temperature effects
• CPC Class Codes: G01C 21/185 for gravity
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems
• 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

Abstract

A method to improve estimation and stabilization of heading in an inertial navigation system is provided. The method includes operating an inertial measurement unit oriented in a first orientation, forward-rotating the operational inertial measurement unit by a selected-rotation angle about a Z-body axis of the inertial navigation system, wherein the inertial measurement unit is oriented in a second orientation, operating the inertial measurement unit oriented in the second orientation, reverse-rotating the operational inertial measurement unit by the selected-rotation angle about the Z-body axis, wherein the inertial measurement unit is oriented in the first orientation, continuously receiving information indicative of an orientation of the inertial measurement unit at a rotational compensator, and continuously-rotationally compensating navigation module output at the rotational compensator, wherein output of the rotational compensator is independent of the rotating.

Claims

1. An inertial navigation system, comprising:

an inertial measurement unit including at least three sensors including at least one gyroscope and at least two accelerometers;

a rotational device on which the inertial measurement unit including the at least three sensors is positioned, the rotational device configured to simultaneously rotate the at least three sensors positioned on the rotational device about a Z-body axis of the inertial navigation system from a first orientation to a second orientation;

a rotational position sensor to sense;

a forward-rotation of the inertial measurement unit first from the first orientation to the second orientation and then a reverse-rotation of the inertial measurement unit from the second orientation to the first orientation;

or

a forward-rotation of the inertial measurement unit first from the first orientation through the second orientation to first orientation and then a reverse-rotation of the inertial measurement unit from the first orientation through the second orientation to the first orientation,

wherein the inertial measurement unit operates first while forward-rotating and then while reverse-rotating;

a software module stored in a non-transitory storage medium including;

a rotational control algorithm configured, when executed by a processor, to control the rotation of the rotational device;

a rotational compensator;

a sensor compensation module configured to receive input from the inertial measurement unit;

a navigation module configured, when executed by the processor, to receive input from the sensor compensation module; and

a Kalman filter communicatively coupled to send error correction data to the navigation module, the sensor compensation module, the rotational control algorithm, and the rotational compensator; and

the processor configured to execute the software module,

wherein the rotational compensator receives information indicative of an orientation of the inertial measurement unit from the rotational position sensor and from the rotational control algorithm, and, when executed by the processor, the rotational compensator compensates for the rotation of the inertial measurement unit about the Z-body axis, wherein navigational data output from the rotational compensator is compensated for the forward-rotation and the subsequent reverse-rotation of the inertial measurement unit,

wherein the software module is configured, when executed;

to remove the effect of the forward-rotation and the subsequent reverse-rotation of the inertial measurement unit; and

to generate error correction data based on the operation of the inertial measurement unit first while forward-rotating and then while reverse-rotating, and

wherein gyroscope bias errors are distributed based on consecutive operations of the inertial measurement unit in the first orientation and the second orientation, and wherein a heading error of the inertial navigation system is reduced by the distribution of the gyroscope bias errors.

2. The inertial navigation system of claim 1, further comprising an aiding sensor to input information to the Kalman filter.

3. The inertial navigation system of claim 1, wherein the at least three sensors of the inertial measurement unit include a first-horizontal-sensing gyroscope, a second-horizontal-sensing gyroscope, and a vertical-sensing gyroscope, the gyroscopes being orthogonally mounted.

4. The inertial navigation system of claim 1, wherein the rotational device is configured to rotate the inertial measurement unit by one hundred eighty degrees from the first orientation to the second orientation in at least one rotation step.

5. The inertial navigation system of claim 1, wherein the inertial measurement unit is a micro-electro-mechanical system (MEMS) inertial measurement unit.

6. The inertial navigation system of claim 3, wherein the Z-body axis of the inertial navigation system is parallel to an input axis of the vertical-sensing gyroscope.

7. The inertial navigation system of claim 6, further comprising:

a fixture in which the rotational device is fixedly attached, wherein the fixture permits the input axis of the vertical-sensing gyroscope to align to a gravitational field of the earth, wherein the Z-body axis is parallel to a vertical-earth axis while the rotational position sensor rotates about the Z-body axis.

8. The inertial navigation system of claim 3, further comprising:

a fixture in which the rotational device is fixedly attached, wherein the fixture permits an axis of the rotational device to align to a gravitational field of the earth, wherein the Z-body axis Z_body is parallel to a vertical-earth axis while the rotational position sensor rotates about the Z-body axis.