Hybrid Inertial Navigation System Based on A Kinematic Model

• US 20080221794A1
• Filed: 12/07/2005
• Published: 09/11/2008
• Est. Priority Date: 12/07/2004
• Status: Active Grant

• Current Assignee: Safran Electronics & Defense
• Original Assignee: Sagem Defense Securite SA (Safran SA)
• Inventors: Debailleul, Frederic
• Granted Patent: US 8,165,795 B2
• Time in Patent Office: Days
• US Class Current: 701/220
• 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

The invention concerns a method for improving determination of inertial navigation parameters (1) of a carrier (1) moving along modelizable kinematic movement components, the method including the following steps: (a) selecting, taking into account a kinematic model (13) of the carrier (1), at least one movement component whereby integration (11) of the inertial measurements (20) is assumed to give a predetermined value, (b) integrating (11) the inertial measurements (20) in accordance with the selected component(s), (c) determining (14) based on the component(s) a variation between the integration (11) obtained at step (b) and the predetermined value of step (a), (d) estimating on the basis of the variation(s) thus obtained a global inertial error resulting from internal errors associated with said modelizable components, and values to be updated of variable parameters of the kinematic model (13), (e) correcting said inertial navigation based on the thus determined global inertial error. The invention also concerns an inertial navigation system for implementing said method.

Claims

1. A method intended to determine the inertial navigation parameters (18) of a carrier (1) moving along with modelizable kinematic movement components, the method including a step of inertial measurements (20) which can include an error, known as the inertia error, which results in determining these parameters inaccurately (18), with the method being characterised in that it includes the following steps:

a) choosing, on a kinematic model (13) of the carrier (1), at least one movement component according to which the integration (11) of the inertial measurements (20) is assumed to give a predetermined value,

b) integration (11) of the measurements (20) according to the chosen component or components,

c) determining (14), according to these components, a difference between the integration (11) obtained at step (b) and the predetermined value from step (a),

d) estimating, as a function of the difference or differences thus obtained, an overall inertia error resulting from the inertia errors associated with the said modelizable components, and the values of the variable parameters of the kinematic model that are to be updated (13),

e) correction of the said inertial navigation parameters as a function of the overall inertia error thus determined.

2. A method according to claim 1, characterised in that the estimates in step (d) are made by means of a filter.

3. A method according to claim 2, characterised in that the filter is a Kalman filter.

4. A method according to one of the preceding claims, characterised in that one of the variable parameters of the kinematic model is an angle α

between at least one axis (Xb) of the carrier and an axis (Xr) of a road travelled by this carrier.

5. A method according to claim 4, characterised in that the angle α

is modeled as a function of at least one parameter reflecting an operational state of the carrier.

6. A method according to one of claims 4 to 5, characterized in that one of the variable parameters of the kinematic model is a distance coordinate between the axes of the road and of the carrier.

8. A system according to claim 7, characterised in that it also includes means designed to implement the method according to any of claims 2 to 6.

7. An inertial navigation system mounted in a carrier (1) moving along with modelizable kinematic movement components (X;

Y;

Z), and that includes;

inertial measurement means,

means designed to choose, on a kinematic model (13) of the carrier, at least one movement component (X;

Y;

Z) according to which integration of the inertial measurements is assumed to give a predetermined value,

means designed to integrate measurements according to the chosen component or components (X;

Y;

Z),

means designed to determine, in accordance with the said components, a difference between the integration and the predetermined value,

means designed to estimate, as a junction of the difference or differences thus obtained, an overall inertia error resulting from the inertia errors associated with the said modelizable components (X;

Y;

Z),

means designed to correct the said inertial navigation parameters as a function of the overall inertia error determined,

characterised in that it also includes means designed to estimate, in accordance with the said difference, values of the variable parameters of the kinematic model that are to be updated (13).