Device and method for detecting an impact on a composite material structure

Patent metadata

Field	Value
Publication number	US-9470659-B2
Application number	US-201314109598-A
Country	US
Kind code	B2
Filing date	Dec 17, 2013
Priority date	Dec 18, 2012
Publication date	Oct 18, 2016
Grant date	Oct 18, 2016

Abstract

A device for detecting an impact on a composite material structure. This detection device comprises at least two acoustic modules intended to be secured to the composite material structure and a processing unit able to communicate remotely with each of the acoustic modules. Each acoustic module is electrically autonomous and comprises its own means for recording the sound waves sensed by its acoustic sensor. An aircraft structure is also provided comprising a composite material structural element equipped with the impact detection device. A method is also provided for detecting an impact on a composite material aircraft structural element equipped with an impact detection device.

First claim

The invention claimed is:

1. A device for detecting an impact on a composite material structure of an aircraft, the detection device comprising:
at least two acoustic modules mounted to the composite material structure of the aircraft, and configured to communicate wirelessly with each other, and
a processing unit configured to communicate remotely and wirelessly with each of the acoustic modules,
each acoustic module having:
an acoustic sensor,
electrical energy generating means,
means for recording sound waves sensed by the acoustic sensor, and
remote communication means configured to communicate with the processing unit,

wherein the electrical energy generating means of the acoustic module includes a micro-kinetic generator for producing an electrical energy on the basis of the vibrations undergone by the composite material structure of the aircraft, and an accumulator for storing up the electrical energy produced by the mirco-kinetic generator.

2. The device for detecting an impact on a composite material structure according to claim 1 , wherein at least one acoustic module acts as a master module, and includes a clock.

3. The device for detecting an impact on a composite material structure according to claim 2 , wherein the remote communication means of the master acoustic module are configured to communicate with the other acoustic modules of the detection device.

4. A method for detecting an impact on a composite material structural element of an aircraft, the structural element being equipped with an impact detection device according to claim 1 , the detection method implementing the detection device according to the following steps:
emission by the communication means of a master acoustic module of a radio frequency signal comprising a time base common to the set of modules of the device towards the other acoustic modules of the device,
recording by the recording means of each acoustic module of the sound waves travelling through the structural element over a determined duration,
transferring, by the communication means, the sound waves recorded by each acoustic module to the processing unit,
analyzing the transferred sound waves so as to detect any impacts occurring on the structural element.

5. The method for detecting an impact on a composite material structural element of an aircraft according to claim 4 , in which the step of analyzing the transferred sound waves comprises a step of evaluating a criticality of an impact occurring on the structural element.

6. The method for detecting an impact on a composite material structural element of an aircraft according to claim 4 , in which the step of analyzing the transferred sound waves comprises a step of locating an impact occurring on the structural element.

7. The method for detecting an impact on a composite material structural element of an aircraft according to claim 4 , in which the detection device is implemented during a flight of the aircraft.

8. An aircraft structure comprising a composite material structural element, the aircraft structure comprising the structural element being equipped with an impact detection device according to claim 1 .

9. The aircraft structure according to claim 8 , wherein the acoustic modules are fastened to a surface of the structural element.

10. The aircraft structure according to claim 8 , wherein the acoustic modules are provided in the structural element.

11. The aircraft structure according to claim 8 , wherein at least one acoustic module is fastened to a surface of the structural element, and wherein at least one acoustic module is provided in the structural element.

12. The aircraft structure according to claim 8 , wherein the structural element extends principally in one dimension and wherein the detection device comprises only a first acoustic module secured to a first end of the structural element, and a second acoustic module secured to a second end of the structural element.

13. The aircraft structure according to claim 8 , wherein the structural element extends principally in two dimensions, and wherein the detection device comprises at least three acoustic modules secured to the structural element, the distances separating the modules pairwise from among the at least three modules all being different.

Assignees

• Airbus Operations Sas
• Airbus Operations Sas

Inventors

• Chaume Olivier
• Kern Xavier
• Cabot Jean-Pascal

Classifications

• G01N29/2481

  Wireless probes, e.g. with transponders or radio links · CPC title

• G01N29/2475

  Embedded probes, i.e. probes incorporated in objects to be inspected · CPC title

• G01N2291/2694

  Wings or other aircraft parts · CPC title

• G01N29/04 Primary

  Analysing solids (using acoustic emission techniques G01N29/14) · CPC title

• G01N29/045 Primary

  by imparting shocks to the workpiece and detecting the vibrations or the acoustic waves caused by the shocks (measuring resonant frequency G01H13/00; measuring strength properties by application of mechanical stress G01N3/00) · CPC title