METHOD AND DEVICE FOR DETECTING NOISE ON A GUIDE SIGNAL OF LOC TYPE RECEIVED BY AN AIRCRAFT

• US 20090005920A1
• Filed: 04/25/2008
• Published: 01/01/2009
• Est. Priority Date: 05/09/2007
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus France
• Inventors: COLOMER, Alexandre
• Granted Patent: US 8,239,077 B2
• Time in Patent Office: Days
• US Class Current: 701/14
• CPC Class Codes: G01S 1/026 of associated receivers
• CPC Class Codes: G01S 1/16 Azimuthal guidance systems, e.g. system for defining aircraft approach path, localiser system
• CPC Class Codes: G05D 1/0202 specially adapted to aircraft
• CPC Class Codes: G08G 5/025 Navigation or guidance aids radar or analogous systems specially adapted for landing purposes G01S13/913

Abstract

The invention has as an object a method and a device for an aircraft for detecting noise in a signal of LOC type. A first step consists in estimating a first lateral speed (105) of the said aircraft according to a first set of parameters. Concurrently, at least one second lateral speed (120) of the said aircraft is estimated according to at least one second set of parameters, among which at least one parameter is of different nature from each parameter of the said first set of parameters. A second step consists in comparing the said first lateral speed and the said at least one second lateral speed according to a threshold. If the difference between the said first lateral speed and the said at least one second lateral speed is greater than the said threshold, the presence of noise in the said signal of LOC type is detected. Advantageously, an additional step of validation of the said detection of noise in the said signal of LOC type is implemented. Similarly, according to a preferred embodiment, a step of validation relating to the said first and at least one second lateral speed is implemented,

Claims

1. A method in an aircraft for detecting the presence of noise in a signal of LOC type, this method being characterized in that it comprises the following steps,

estimation of a first lateral speed (105) of the said aircraft according to a first set of parameters;

estimation of at least one second lateral speed (120) of the said aircraft according to at least one second set of parameters, among which at least one parameter is of different nature from each parameter of the said first set of parameters;

comparison of the said first lateral speed and of the said at least one second lateral speed according to a threshold (500);

detection of the presence of noise in the said signal of LOC type if the difference between the said first lateral speed and the said at least one second lateral speed is greater than the said threshold.

2. A method according to claim 1, characterized in that it additionally comprises a step of validation (505, 510) of the said detection of the presence of noise in the said signal of LOC type.

3. A method according to claim 2, characterized in that the said validation step (505) is based on at least one parameter of state of the said aircraft.

4. A method according to any one of the preceding claims, characterized in that it additionally comprises a step of relative validation (510) of the said estimates of the said first and at least one second lateral speed.

5. A method according to any one of the preceding claims, characterized in that the said first set of parameters comprises parameters of inertial type.

6. A method according to any one of the preceding claims, characterized in that the said at least one second set of parameters comprises parameters of guide type determined on the basis of data obtained from a source external to the said aircraft.

7. A method according to any one of the preceding claims, characterized in that it additionally comprises a step of deactivation (610) of an automatic control device of the said aircraft.

8. A device comprising means suitable for implementation of each of the steps of the method according to any one of the preceding claims.

9. A computer program comprising instructions suitable for implementation of each of the steps of the method according to any one of claims 1 to 7.

10. An aircraft characterized in that it is equipped with a device according to claim 8.