Gasket seal, door of aircraft, seal structure for opening portion of aircraft, and aircraft

• US 9,617,783 B2
• Filed: 09/20/2012
• Issued: 04/11/2017
• Est. Priority Date: 09/20/2011
• Status: Active Grant

• Current Assignee: Msj Asset Management Co.
• Original Assignee: Mitsubishi Aircraft Corporation (Mitsubishi Heavy Industries, Ltd.)
• Inventors: Yahata, Yusaku, Yokoi, Takashi, Doi, Keiichiro, Ibaragi, Mikishige
• Primary Examiner(s): O'Hara, Brian M
• Assistant Examiner(s): KREINER, MICHAEL B
• Application Number:
  US14/345,460
• Publication Number:
  US 20140345199A1
• Time in Patent Office: 1,664 Days
• 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: B64C 1/1407 Doors; surrounding frames
• CPC Class Codes: E06B 7/23 Plastic, sponge rubber, or like strips or tubes
• CPC Class Codes: F16J 15/024 the packing being locally weakened in order to increase elasticity
• CPC Class Codes: F16J 15/027 and with a hollow profile
• CPC Class Codes: F16J 15/064 the packing combining the sealing function with other functions

Abstract

To reliably prevent entrance of electro-magnetic waves in a door that closes an opening portion formed in an airframe of an aircraft. A gasket seal 20 which is arranged between an opening portion 12 formed in an airframe of an aircraft and a door 13 for closing the opening portion 12, includes: a gasket seal body that is made of a rubber material; and conductive fiber 24 that covers a surface of the gasket seal body. When the door 13 is in a closed state, the gasket seal 20 whose surface is made conductive is abutted against a striker 30 provided on a skin 11 side of the airframe and made of a conductive material. The door 13 and the skin 11 of the airframe are electrically connected together via the conductive fiber 24 and the striker 30, and electro-magnetic waves can be reliably shielded.

Claims

1. A seal structure for an opening portion of an aircraft comprising a gasket seal which is arranged between the opening portion formed in an airframe of the aircraft and a closing body for closing the opening portion, wherein the seal structure comprises:

the closing body that closes the opening portion;

the gasket seal provided on one of the opening portion and the closing body; and

a metallic fitting that is provided on the other of the opening portion and the closing body, and electrically connected to the gasket seal, and

the gasket seal comprises;

a gasket seal body that is made of a rubber material; and

conductive fiber that covers a surface of the gasket seal body, and wherein

the metallic fitting includes a plating layer (32) at least on a contact surface with the conductive fiber of the gasket seal, and a boundary portion between the plating layer (32) and a base material of the metallic fitting is covered with an anticorrosion coating (33) having insulating properties.

2. The seal structure according to claim 1, wherein the conductive fiber is one of a) synthetic fiber where a metal plating film is formed on a surface, b) metal fiber, and c) polymer fiber including a conductive material.

3. The seal structure according to claim 1, wherein the rubber material is silicone rubber.

4. The seal structure according to claim 1, wherein the rubber material is conductive rubber into which a conductive filler is mixed.

5. The seal structure according to claim 1, wherein the closing body is a door of an aircraft using the gasket seal.

6. The seal structure according to claim 1,

wherein the metallic fitting is

a striker or a scuff plate that is provided so as to be abutted against the gasket seal when the closing body is closed.

7. The seal structure according to claim 6, wherein the metallic fitting is a striker.

8. The seal structure according to claim 6, wherein a region of the striker other than a region where the plating layer is formed is covered with the anticorrosion coating.

9. The seal structure according to claim 1,

wherein the closing body is a door,

the gasket seal is provided on the door, and

the metallic fitting is provided on a door frame formed at the opening portion.

10. The seal structure according to claim 1,

wherein the conductive fiber of the gasket seal is a synthetic fiber where a metal plating film is formed on a surface, and

an anodic index of a metal material constituting the metal plating film is equal to or almost equal to an anodic index of a metal material constituting the plating layer of the metallic fitting.

11. The seal structure according to claim 1,

wherein the conductive fiber of the gasket seal is a metal fiber, and

an anodic index of a metal material constituting the metal fiber is equal to or almost equal to an anodic index of a metal material constituting the plating layer of the metallic fitting.

12. The seal structure according to claim 1, wherein the plating layer of the metallic fitting is a plating layer containing nickel or chrome as a main component.

13. The seal structure according to claim 12, wherein the plating layer of the metallic fitting is an electroless nickel plating layer or a hard chrome plating layer.

14. The seal structure according to claim 1, wherein the plating layer of the metallic fitting is a plating layer containing tin as a main component.

15. The seal structure according to claim 1,

wherein the plating layer of the metallic fitting is a nickel plating layer, and

the conductive fiber of the gasket seal is obtained by forming a metal plating film containing nickel, copper, silver, gold, or alloy thereof as a main component on a surface of synthetic fiber.

16. The seal structure according to claim 1,

wherein the plating layer of the metallic fitting is a chrome plating layer or a tin plating layer, and

the conductive fiber of the gasket seal is made of metal fiber formed of 300 series stainless steel, 400 series stainless steel, or 2000 series aluminum alloy.

17. An aircraft having the seal structure according to claim 1.

18. The seal structure according to claim 1, wherein the base material of the metallic fitting is an aluminum alloy.