IRREGULARITY DETECTION IN A STRUCTURE OF AN AIRCRAFT

• US 20110248732A1
• Filed: 05/26/2009
• Published: 10/13/2011
• Est. Priority Date: 05/28/2008
• Status: Active Grant

• Current Assignee: EADS Deutschland GmbH (Airbus SE), EADS Secure Networks
• Original Assignee: EADS Deutschland GmbH (Airbus SE)
• Inventors: Monet, Didier, Zimmerman, Werner, Rolet, Sebastien, Steinwandel, Jurgen
• Granted Patent: US 8,896,329 B2
• Time in Patent Office: Days
• US Class Current: 324/693
• CPC Class Codes: G01M 5/0016 of aircraft wings or blades
• CPC Class Codes: G01M 5/0033 by determining damage, crack or wear
• CPC Class Codes: G01M 5/0083 by measuring variation of impedance, e.g. resistance, capacitance, induction
• CPC Class Codes: G01M 5/0091 by using electromagnetic excitation or detection

Abstract

A device, a system and a method for detecting an irregularity in a structure of an aircraft are proposed. The device includes a resonant circuit with a resonance frequency and a probe for tuning the resonance frequency of the resonant circuit. The resonant circuit and the probe are operatively connected in such a way that the probe changes the resonance frequency of the resonant circuit if the structure changes due to a formation of an irregularity.

Claims

1. Device for detecting an irregularity in a structure of an aircraft, the device comprising:

a resonant circuit with a resonance frequency;

a probe for tuning the resonance frequency of the resonant circuit;

wherein the probe is attachable to the structure; and

wherein the resonant circuit and the probe are operably connected in such a way that the probe changes the resonance frequency of the resonant circuit, if the structure changes due to a formation of an irregularity.

2. Device according to claim 1,

wherein a change of the structure causes a damage of the probe due to a formation of the irregularity.

3. Device according to claim 1,

wherein the device is adapted to be stimulated at a first resonance frequency, if the probe is not damaged;

and

wherein the device is adapted to be stimulated at a second resonance frequency, if the probe is damaged.

4. Device according to claim 1,

wherein the resonant circuit is part of an RFID tag.

5. Device according to claim 1, wherein the probe is a crack wire;

and

wherein the resonant circuit is an LC circuit.

6. Device according to claim 1,

wherein the structure is one of a wing, a skin and a tail unit of the aircraft.

7. System for detecting an irregularity in a structure of an aircraft, the system comprising:

a device according to claim 1;

a readout unit adapted for reading out the device in a contactless manner.

11. Aircraft comprising a device according to claim 1.

12. Device according to claim 2,

wherein the device is adapted to be stimulated at a first resonance frequency, if the probe is not damaged;

and

wherein the device is adapted to be stimulated at a second resonance frequency, if the probe is damaged.

8. Method for detecting an irregularity in a structure of an aircraft, the method comprising the following steps:

Stimulating a resonant circuit at a resonance frequency of the resonant circuit;

Receiving a signal from the resonant circuit;

wherein the signal from the resonant circuit corresponds with a change of the structure due to a formation of an irregularity.

9. Method according to claim 8, wherein the method is carried out with a device comprising:

a resonant circuit with a resonance frequency;

a probe for tuning the resonance frequency of the resonant circuit;

wherein the probe is attachable to the structure; and

wherein the resonant circuit and the probe are operably connected in such a way that the probe changes the resonance frequency of the resonant circuit, if the structure changes due to a formation of an irregularity.

10. Method according to claim 8,

wherein, if the probe is not damaged, an ID number of an RFID tag, in which the resonant circuit is comprised, is not readable;

and

wherein, if the probe is damaged, the ID number of the RFID tag, in which the resonant circuit is comprised, is readable.

13. Method according to claim 9, wherein, if the probe is not damaged, an ID number of an RFID tag, in which the resonant circuit is comprised, is not readable;

and wherein, if the probe is damaged, the ID number of the RFID tag, in which the resonant circuit is comprised, is readable.