Lightning strike protection

• US 8,561,934 B2
• Filed: 08/28/2009
• Issued: 10/22/2013
• Est. Priority Date: 08/28/2009
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Rtx Corporation), ROHR Incorporated (Rtx Corporation)
• Original Assignee: Goodrich Corporation (Rtx Corporation), ROHR Incorporated (Rtx Corporation)
• Inventors: Kruckenberg, Teresa M., Pujar, Vijay V.
• Primary Examiner(s): Swiatek, Rob
• Assistant Examiner(s): BENEDIK, JUSTIN M
• Application Number:
  US12/549,871
• Publication Number:
  US 20110049292A1
• Time in Patent Office: 1,516 Days
• Field of Search: 244/1.A, 244/133, 244/123.1, 244/119
• US Class Current: 244/1.A
• CPC Class Codes: B64D 45/02 Lightning protectors; Static dischargers in general H01T
• CPC Class Codes: C08J 5/005 Reinforced macromolecular compounds with nanosized materials, e.g. nanoparticles, nanofibres, nanotubes, nanowires, nanorods or nanolayered materials
• CPC Class Codes: C08J 5/042 with carbon fibres
• CPC Class Codes: D06M 11/74 with carbon or graphite; with carbides; with graphitic acids or their salts
• CPC Class Codes: D06M 15/55 Epoxy resins
• CPC Class Codes: D06M 2101/40 Fibres of carbon
• CPC Class Codes: Y10T 428/24 Structurally defined web or sheet [e.g., overall dimension, etc.]
• CPC Class Codes: Y10T 428/25 Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
• CPC Class Codes: Y10T 428/26 Web or sheet containing structurally defined element or component, the element or component having a specified physical dimension
• CPC Class Codes: Y10T 442/10 Scrim [e.g., open net or mesh, gauze, loose or open weave or knit, etc.]
• CPC Class Codes: Y10T 442/2008 Fabric composed of a fiber or strand which is of specific structural definition
• CPC Class Codes: Y10T 442/60 Nonwoven fabric [i.e., nonwoven strand or fiber material]

Abstract

An aircraft component having an external surface includes an improved lightning strike protection surface film disposed on or proximate to the external surface. The surface film includes a preform that includes a substrate having a first areal weight density and a plurality of spaced carbon nanotubes grown on the substrate, the nanotubes having a second areal weight density. The sum of the first areal weight density and the second areal weight density is less than about 500 grams per square meter, and the preform has a surface resistance less than about 1 ohm/square.

Claims

1. An aircraft component having an external surface and comprising:

a. a lightning strike protection surface film disposed on or proximate to the external surface and including a preform comprising;

a substrate having a first areal weight density; and

a plurality of spaced carbon nanotubes grown on the substrate, the nanotubes having a second areal weight density, wherein the nanotubes decrease a surface resistance of the preform;

wherein the sum of the first areal weight density and the second weight density is less than about 500 grams per square meter; and

wherein the surface resistance is less than about 1 ohm/square.

2. The aircraft component according to claim 1 wherein the surface resistance is less than about 0.5 ohm/square.

3. The aircraft component according to claim 1 wherein the preform is disposed within a polymeric material.

4. The aircraft component according to claim 1 wherein the substrate comprises a plurality of electrically conductive fibers, and wherein ends of the carbon nanotubes are connected to the electrically conductive fibers.

5. The aircraft component according to claim 4 wherein the electrically conductive fibers comprise carbon fibers or carbon nanotube reinforced polyacrylonitrile carbonized fibers, and wherein the first area weight density is between about 70 grams per square meter and about 400 grams per square meter.

6. The aircraft component according to claim 4 wherein the substrate is a woven, braided or non-crimp fabric, or a non-woven mat, veil, or scrim, or a paper.

7. The aircraft component according to claim 6 wherein the electrically conductive fibers are carbon nanotubes, wherein the first areal weight density is between about 15 grams per square meter and about 200 grams per square meter, and wherein the sum of the first areal weight density and the second areal weight density is less than about 300 grams per square meter.

8. The aircraft component according to claim 6 wherein the electrically conductive fibers have lengths greater than about 6 mm.

9. The aircraft component according to claim 1 wherein the substrate comprises a metal screen or mesh, and wherein the first areal weight density is between about 40 grams per square meter and about 400 grams per square meter.

10. The aircraft component according to claim 1 wherein the carbon nanotubes have lengths from about 5 microns to about 100 microns.

11. The aircraft component according to claim 1 wherein the carbon nanotubes have diameters from about 1 nanometer to about 200 nanometers.

12. The aircraft component according to claim 1 further comprising a metallic material deposited on the substrate or on the preform.

13. The aircraft component according to claim 1 wherein the external surface defines an aircraft engine nacelle, fuselage, wing or vertical tail, a helicopter rotor blade or other helicopter component, or components or portions thereof.

14. A lightning strike protection surface film comprising:

a substrate having a first areal weight density and a plurality of spaced carbon nanotubes grown on the substrate, the nanotubes having a second areal weight density, wherein the nanotubes decrease a surface resistance of the surface film;

wherein the sum of the first areal weight density and the second areal weight density is less than about 500 grams per square meter, and the nanotubes are substantially uniformly distributed on the fibers and have a length between about 1 and 100 microns.

15. The lightning strike protection surface film according to claim 14 wherein the surface resistivity is less than about 1.0 ohm/square.

16. The lightning strike protection surface film according to claim 14 wherein the substrate and nanotubes are disposed within a polymeric material.

17. The lightning strike protection surface film according to claim 14 wherein the substrate comprises a plurality of fibers comprising carbon fibers or carbon nanotube reinforced polyacrylonitrile carbonized fibers, and wherein the first areal weight density is between about 70 grams per square meter and about 400 grams per square meter.

18. The lightning strike protection surface film according to claim 14 wherein the spaced carbon nanotubes are grown on a plurality of carbon nanotubes having lengths greater than about 6 mm, wherein the first areal weight density is between about 15 grams per square meter and about 200 grams per square meter, and the sum of the first areal weight density and the second areal weight density is less than about 300 grams per square meter.

19. The lightning strike protection surface film according to claim 14 wherein the plurality of carbon nanotubes comprises carbon nanotubes having lengths from about 5 microns to about 100 microns and having diameters from about 1 nanometer to about 200 nanometers.

20. The lightning strike protection surface film according to claim 14 wherein the substrate comprises a woven or expanded metal screen and wherein the first areal weight density is between about 70 grams per square meter and about 400 grams per square meter.

21. A method of producing an aircraft component with lightning strike protection, the method comprising:

providing an aircraft structure having an outer surface portion;

forming a lightning strike protection surface film by providing a substrate having a first areal weight density and growing on the substrate a plurality of spaced carbon nanotubes, the nanotubes having a second areal weight density, wherein the nanotubes decrease a surface resistance of the substrate;

bonding the lightning strike protection surface film to the outer surface portion to form an external surface portion; and

selecting the composition and areal weight density of the substrate and controlling the areal weight density of the carbon nanotubes such that the sum of the first areal weight density and the second areal weight density is less than about 500 grams per square meter and such that the surface resistivity is less than about 1 ohm/square.

22. The method according to claim 21 further comprising the step of heat treating the surface film between about 600°

C. and 1,800°

C. for about 0.25 to 24 hours after growing nanotubes on the substrate.

23. The method according to claim 21 wherein the areal weight density of the carbon nanotubes is between about 2 grams per square meter and about 100 grams per square meter and wherein the substrate with grown-on nanotubes has a surface resistivity less than about 0.5 ohm/square.

24. A composite aircraft component comprising:

a polymeric material;

at least one layer comprising a woven or non-woven substrate and a plurality of carbon nanotubes grown on the substrate, wherein at least 75 percent of the plurality of carbon nanotubes are located within 5 microns of another nanotube in the plurality of nanotubes, such that the plurality of carbon nanotubes provide a conductive path through the polymeric material; and

wherein the substrate provides structural reinforcement to the polymeric material and wherein the carbon nanotubes provide lightning strike protection to an outer surface of the composite aircraft component; and

wherein the substrate and the plurality of carbon nanotubes have a combined areal density that is less than about 500 grams per square meter.

25. The composite aircraft component according to claim 24 wherein the component has an external surface and the layer is positioned within at least about 0.5 mm of the surface.