Structural component as well as system and method for the detection of damage

Patent metadata

Field	Value
Publication number	US-10794849-B2
Application number	US-201916396990-A
Country	US
Kind code	B2
Filing date	Apr 29, 2019
Priority date	Apr 30, 2018
Publication date	Oct 6, 2020
Grant date	Oct 6, 2020

Abstract

A structural component has a plurality of material layers, which are stacked and bonded together in a thickness direction, wherein at least one of the material layers is formed by a fibre composite material, and wherein an outermost material layer in relation to the thickness direction is formed at least in sections by a sensor device, having at least one sensor unit with an electroactive polymer arranged between electrically conductive electrodes. Moreover, a system and a method for the detection of damage and an aircraft are described.

First claim

The invention claimed is:

1. A structural component having a plurality of material layers, which are stacked and bonded together in a thickness direction;
wherein at least one of the material layers comprises a fibre composite material, and
wherein an outermost material layer of the plurality of material layers in relation to the thickness direction comprises at least in sections a sensor device having at least one sensor unit with an electroactive polymer arranged between first and second electrically conductive electrodes.

2. The structural component according to claim 1 , wherein the sensor device forms the entire surface of the outermost material layer.

3. The structural component according to claim 1 , wherein the at least one sensor unit is in the form of a band.

4. The structural component according to claim 1 , wherein in addition to the outermost material layer, also a first inner material layer adjoining the outermost material layer in the thickness direction comprises at least in sections the sensor device.

5. The structural component according to claim 4 , wherein at least one sensor unit is provided respectively in the first inner material layer and the outermost material layer.

6. The structural component according to claim 5 , wherein the sensor units arranged in the outermost material layer and those arranged in the first inner material layer are in each case formed as bands and cross over each other.

7. The structural component according to claim 1 , wherein the electroactive polymer is a dielectric electroactive polymer.

8. The structural component according to claim 7 , wherein the electroactive polymer is a thermoplastic polyurethane elastomer.

9. The structural component according to claim 1 , wherein the first and second electrically conductive electrodes of the sensor unit are formed from an electrically conductive polymer.

10. A system for the detection of damage, comprising:
a structural component having a plurality of material layers, which are stacked and bonded together in a thickness direction;
wherein at least one of the material layers comprises a fibre composite material, and
wherein an outermost material layer in relation to the thickness direction comprises at least in sections a sensor device having at least one sensor unit with an electroactive polymer arranged between first and second electrically conductive electrodes; and
at least one voltage measuring device connected to the first and second electrically conductive electrodes of the at least one sensor unit, in order to measure an electrical voltage present between the electrodes.

11. The system according to claim 10 , further comprising a number of voltage measuring devices corresponding to the number of sensor units,
wherein the at least one voltage measuring device is connected to the first and second electrically conductive electrodes of each sensor unit.

12. The system according to claim 10 , further comprising a deformation detecting device arranged on the structural component to detect a deformation of the structural component.

13. An aircraft having a system according to claim 10 .

14. A method for the detection of damage of a structural component according to claim 1 , comprising:
providing the structural component of claim 1 ;
generating shear forces along boundary surfaces of the material layers by mechanical deformation of the structural component;
detecting an electrical voltage at the first and second electrically conductive electrodes of the at least one sensor unit of the sensor device over a predetermined period of time; and
analyzing a resulting plot of the electrical voltage over the predetermined period of time in regard to the existence of a damage criterion indicative of damage.

15. The method according to claim 14 , wherein the damage criterion is fulfilled by a change in the voltage plot, by a change in the voltage plot as compared to a plot of a deformation of the structural component detected over the predetermined period of time, or by a deviation of the voltage plot in a first partial period of time of the predetermined period of time from the voltage plot in a second, later partial period of time of the predetermined period of time.

Assignees

• Airbus Operations Gmbh

Inventors

• Linde Peter

Classifications

• G01N27/20 Primary

  Investigating the presence of flaws · CPC title

• B29C70/54 Primary

  Component parts, details or accessories; Auxiliary operations {, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing} · CPC title

• G01N27/041

  of a solid body · CPC title

• B32B27/40

  comprising polyurethanes · CPC title

• G01L1/06

  by measuring the permanent deformation of gauges, e.g. of compressed bodies · CPC title