METHOD OF MONITORING A COMPOSITE MATERIAL

• US 20170313436A1
• Filed: 04/25/2017
• Published: 11/02/2017
• Est. Priority Date: 04/27/2016
• Status: Active Grant

• Current Assignee: Leonardo S.p.A.
• Original Assignee: Leonardo S.p.A.
• Inventors: LAMBERTI, Patrizia, SPINELLI, Giovanni, TUCCI, Vincenzo, VERTUCCIO, Luigi, GUADAGNO, Liberata, RUSSO, Salvatore, IANNUZZO, Generoso
• Granted Patent: US 10,196,153 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G01B 7/18 using change in resistance
• CPC Class Codes: G01M 5/0041 by determining deflection or stress
• CPC Class Codes: G01M 5/0083 by measuring variation of impedance, e.g. resistance, capacitance, induction
• CPC Class Codes: G01N 27/041 of a solid body
• CPC Class Codes: G01N 27/20 Investigating the presence of flaws

Abstract

The method allows to monitor a composite material comprising an epoxy resin tilled with electrically conductive nanoparticles, wherein at least one electrical property i.e. impedance of the composite material is influenced by being subjected to a mechanical deformation. The method provides for inserting the composite material in an electric circuit emitting an electric signal whose value depends on the electrical property, so that, when the value of the signal overcomes a given threshold value, a warning message is delivered.

Claims

1. A method for monitoring a composite material comprising an epoxy resin filled with electrically conductive nanoparticles, at least one electrical property of said composite material being influenced by being subjected to a mechanical deformation, said method providing for inserting said composite material in an electric circuit emitting an electric signal whose value depends on said electrical property, so that, when the value of said signal overcomes a given threshold value, a warning message is delivered, wherein said electrical property is the electrical impedance.

2. The method according to claim 1, wherein said electrical property is the overall electrical impedance of the composite material constituting a structural element.

3. The method according to claim 1 or 2, wherein said electric circuit is subject to an electrical tension in the range 1 mV to 220 V, and preferably in the range 1 mV to 20V.

4. The method according to claim 1 or 2, wherein said warning message is a visual and/or acoustic message.

5. The method according to claim 1 or 2, wherein said electrical circuit is fed with AC.

6. The method according to claim 5, wherein said AC has a frequency in the range 1 Hz to 1 GHz.

7. The method according to claim 1 or 2, wherein said electrically conductive nanoparticles are multi-walled carbon nanotubes (MWCNTs).

8. The method according to claim 1 or 2, wherein said electrically conductive nanoparticles are carbon nanofibers or graphene-based nanoparticles, in particular graphene single layers, graphene layers or exfoliated graphite.

9. The method according to claim 1 or 2, wherein said electrically conductive nanoparticles constitute 0.01 to 5% by weight of the total weight of said composite material.

10. The method according to claim 1 or 2, which is a real-time self-health monitoring method of a structure, in particular an aircraft structure, incorporating said composite material.

11. The method according to claim 1 or 2, wherein said composite material constitutes an aircraft structure which is monitored.

12. The method according to claim 11, wherein said warning message is delivered when a crack of at least 1 nm is formed within said aircraft structure.

13. The method according to claim 12, wherein said crack is up to 5 nm.

14. The method according to claim 11, wherein the Young'"'"'s modulus of said composite material is in the range 500 to 3000 MPa at room temperat