Method of calibrating an inertial assembly comprising a dynamic phase between two static phases

• US 9,464,916 B2
• Filed: 05/15/2012
• Issued: 10/11/2016
• Est. Priority Date: 05/20/2011
• Status: Active Grant

• Current Assignee: Safran Electronics & Defense
• Original Assignee: Sagem Defense Securite (Safran SA)
• Inventors: Becheret, Yves
• Primary Examiner(s): Rogers, David A
• Application Number:
  US14/117,596
• Publication Number:
  US 20140298883A1
• Time in Patent Office: 1,610 Days
• US Class Current: 1/1
• 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: G01C 25/005 initial alignment, calibration or starting-up of inertial devices
• CPC Class Codes: G01P 21/00 Testing or calibrating of apparatus or devices covered by the preceding groups

Abstract

A method of calibrating an inertial unit is provided. During a first static stage, in which the inertial unit is in a first orientation, measurements are taken by means of the accelerometers and the inertial rotation sensors. During a dynamic stage, the orientation of the inertial unit is changed, at least in part in azimuth, from the first orientation towards a second orientation, while taking measurements by means of the inertial rotation sensors. During a second static stage, in which the inertial unit is in the second position, measurements are taken by means of the accelerometers and of the inertial rotation sensors. For each static stage, a direction, an amplitude, and a mean speed of rotation for apparent gravity in an inertial frame of reference is estimated, variation is calculated in orientation between the static stages, and the accelerometer biases is deduced therefrom.

Claims

1. A method of calibrating accelerometers of an inertial unit having also inertial rotation sensors, comprising the following steps:

during a first static stage, in which the inertial unit is in a first orientation, taking measurements by means of the accelerometers and the inertial rotation sensors;

during a dynamic stage, changing the orientation of the inertial unit, at least in part in azimuth, from the first orientation towards a second orientation, while taking measurements by means of the inertial rotation sensors;

during a second static stage, in which the inertial unit is in the second position, taking measurements by means of the accelerometers and of the inertial rotation sensors; and

estimating a direction, an amplitude, and a mean speed of rotation for apparent gravity in an inertial frame of reference for each static stage, calculating variation in orientation between the static stages during the dynamic stage, and deducing therefrom the accelerometer biases.

2. The method according to claim 1, wherein the accelerometer biases are determined by the least squares method jointly with the initially determined first orientation in such a manner as to minimize the movements measured during the static stages.

3. The method according to claim 1, wherein the measurements are performed by means of the accelerometers during the dynamic stage.

4. The method according to claim 1, wherein the method is launched automatically after detecting a pair of static stages.

5. The method according to claim 1, comprising the step of deducing from the calculated variation, if the rotation in the intermediate stage makes this possible, the drifts.