AIRFRAME COMPONENT WITH ELECTRICALLY BONDED CONNECTIONS

• US 20160052615A1
• Filed: 08/03/2015
• Published: 02/25/2016
• Est. Priority Date: 08/25/2014
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Ulsamer, Karl, Shortt, Robert F. Jr., Agria, Thomas R.
• Granted Patent: US 9,896,183 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 1/14 Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipersfairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06
• CPC Class Codes: H01Q 1/286 substantially flush mounted with the skin of the craft
• CPC Class Codes: H01Q 1/44 using equipment having another main function to serve additionally as an antenna , e.g. means for giving an antenna an aesthetic aspectH01Q1/27 - H01Q1/34 take precedence

Abstract

An airframe component is provided and includes first and second components having respective first and second opposite surfaces and edge portions, the first component defining a plane and the second component being attachable to the first surface of the first component as a protrusion from the plane, a first conductive layer disposed to wrap around the edge portion of the first component from the first surface to the second surface, a second conductive layer disposed on the first surface of the second component to extend beyond the edge portion and an insulation layer interposable between the first and second conductive layers and between a periphery of the first surface of the second component and the second conductive layer.

Claims

1. An airframe component, comprising:

first and second components having respective first and second opposite surfaces and edge portions, the first component defining a plane and the second component being attachable to the first surface of the first component as a protrusion from the plane;

a first conductive layer disposed to wrap around the edge portion of the first component from the first surface to the second surface;

a second conductive layer disposed on the first surface of the second component to extend beyond the edge portion; and

an insulation layer interposable between the first and second conductive layers and between a periphery of the first surface of the second component and the second conductive layer.

2. The airframe component according to claim 1, wherein the first and second components each comprise curable composite materials.

3. The airframe component according to claim 1, wherein the first component comprises a door panel and the second component comprises a door jamb.

4. The airframe component according to claim 1, wherein the first and second conductive layers each comprise an electrically conductive wire mesh.

5. The airframe component according to claim 1, wherein the insulation layer comprises at least one or more of Fluorinated ethylene propylene (FEP) and Polytetrafluoroethylene (PTFE).

6. The airframe component according to claim 1, wherein the first and second conductive layers are contactable with the second component attached to the first surface of the first component.

7. A method of forming an airframe component, the method comprising:

wrapping a first conductive layer around an edge portion of a first component defining a plane from a first surface thereof to a second surface thereof;

disposing a second conductive layer on a first surface of a second component, which is attachable to the first component as a protrusion from the plane, to extend beyond an edge portion thereof; and

interposing an insulation layer between the first and second conductive layers and between a periphery of the first surface of the second component and the second conductive layer.

8. The method according to claim 7, wherein the first and second components each comprise curable composite materials.

9. The method according to claim 7, wherein the first and second conductive layers each comprise an electrically conductive wire mesh.

10. The method according to claim 7, wherein the insulation layer comprises at least one or more of Fluorinated ethylene propylene (FEP) and Polytetrafluoroethylene (PTFE).

11. The method according to claim 7, further comprising separately curing the first and second components.

12. The method according to claim 7, further comprising:

pulling back the second conductive layer from the periphery of the first surface of the second component; and

trimming the second component.

13. The method according to claim 7, further comprising:

bonding the second component to the first surface of the first component;

removing the insulation layer; and

bonding the first conductive layer to the second conductive layer.

14. The method according to claim 13, wherein the bonding of the second component to the first surface of the first component comprises autoclave co-curing.

15. The method according to claim 13, wherein at least the bonding of the first conductive layer to the second conductive layer comprises applying conductive sealant between the first and second conductive layers.