Aircraft with protective nanocoating

• US 9,352,829 B2
• Filed: 03/07/2013
• Issued: 05/31/2016
• Est. Priority Date: 03/07/2013
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Sottiaux, Daniel P., Stamps, Frank Bradley
• Primary Examiner(s): MCFALL, NICHOLAS A
• Application Number:
  US13/789,273
• Publication Number:
  US 20140252157A1
• Time in Patent Office: 1,181 Days
• US Class Current: 1/1
• CPC Class Codes: B64C 27/35 having elastomeric joints
• CPC Class Codes: B64D 2045/009 Fire detection or protection; Erosion protection, e.g. from airborne particles
• CPC Class Codes: F16C 33/04 Brasses; Bushes; Linings
• CPC Class Codes: F16C 33/121 Use of special materials

Abstract

An aircraft component has an exterior surface and a protective nanocoating carried by the exterior surface. An aircraft has an engine, a fuselage, and a component having an exterior surface and a protective nano coating carried by the exterior surface. A method of protecting an aircraft component includes selecting at least one harmful environmental component and applying a protective nanocoating to the aircraft component, wherein the protective nanocoating is configured to protect the aircraft component from the selected harmful environmental component.

Claims

1. An aircraft component, comprising:

an exterior surface configured to flex in response to applied forces; and

a protective nanocoating carried by the exterior surface;

wherein the protective nanocoating protects the aircraft component from oil, ultraviolet radiation, and ozone.

2. The aircraft component of claim 1, wherein the exterior surface comprises an exterior surface of a bearing.

3. The aircraft component of claim 2, wherein the bearing comprises an elastomeric material.

4. The aircraft component of claim 3, wherein the bearing comprises offset metallic shims that bound the elastomeric material, and wherein the protective nanocoating is applied only to the elastomeric material of the exterior surface.

5. The aircraft component of claim 1, wherein the protective nanocoating comprises a thickness of about 0.1 nanometers to about 200 nanometers.

6. The aircraft component of claim 1, wherein the protective nanocoating comprises protective particles comprising a maximum dimension of about 0.1 nanometers to about 200 nanometers.

7. The aircraft component of claim 6, wherein the protective particles are configured to protect against at least one of oil, ultraviolet radiation, and ozone;

wherein a first subset of the particles provides protection against oil smoke particles;

wherein a second subset of the particles provides protection against ultraviolet radiation;

wherein a third subset of the particles provides protection against ozone particles; and

wherein the first subset of the particles, the second subset of the particles, and the third subset of the particles are evenly dispersed in the protective nanocoating.

8. The aircraft component of claim 1, wherein the exterior surface comprises a first area having a first flexure and a second area having a second flexure that is greater than the first flexure, wherein a thickness of the protective nanocoating at the first area is greater than a thickness of the protective nanocoating at the second area.

9. The aircraft component of claim 1, wherein the protective nanocoating is substantially transparent.

10. An aircraft, comprising:

an engine;

a fuselage; and

a component, comprising;

an exterior surface configured to flex in response to applied forces; and

a protective nanocoating carried by the exterior surface;

wherein the protective nanocoating protects the component from oil, ultraviolet radiation, and ozone.

11. The aircraft of claim 10, wherein the component comprises a centrifugal force bearing.

12. The aircraft of claim 10, wherein the component comprises a shear bearing.

13. The aircraft of claim 10, wherein the protective nanocoating comprises a thickness of about 0.1 nanometers to about 200 nanometers.

14. The aircraft of claim 10, wherein the protective nanocoating comprises protective particles comprising a maximum dimension of about 0.1 nanometers to about 200 nanometers;

wherein a first subset of the particles provides protection against oil smoke particles;

wherein a second subset of the particles provides protection against ultraviolet radiation;

wherein a third subset of the particles provides protection against ozone particles; and

wherein the first subset of the particles, the second subset of the particles, and the third subset of the particles are evenly dispersed in the protective nanocoating.

15. A method of protecting an aircraft component, comprising:

protecting an exterior surface of an aircraft component with a protective nanocoating applied to the exterior surface of to the aircraft component, the exterior surface configured to flex in response to applied forces; and

wherein the protective nanocoating protects the aircraft component from oil, ultraviolet radiation, and ozone.

16. The method of claim 15, wherein the protective nanocoating comprises a thickness of about 0.1 nanometers to about 200 nanometers.

17. The method of claim 15, further comprising providing the protective nanocoating with protective particles comprising a maximum dimension of about 0.1 nanometers to about 200 nanometers.

18. The method of claim 15, further comprising providing the protective nanocoating with protective particles comprising a maximum dimension of about 0.5 nanometers to about 10 nanometers.

19. The method of claim 15, wherein the protective nanocoating is applied directly to an exterior surface of the aircraft component.

20. The method of claim 15, wherein the aircraft component comprises at least one of a centrifugal force bearing and a shear bearing.