Seal design for vehicle and structure application

Patent metadata

Field	Value
Publication number	US-9517830-B2
Application number	US-201414217673-A
Country	US
Kind code	B2
Filing date	Mar 18, 2014
Priority date	Mar 18, 2014
Publication date	Dec 13, 2016
Grant date	Dec 13, 2016

Abstract

Provided is a captured seal assembly that can be positioned between a first surface and a second surface of a structure or vehicle, such as an aircraft. The captured seal assembly includes a geometric-shaped seal such as a bulb-shaped seal that can be secured to an outer perimeter of the first surface and a receiving land capture that can be secured to an outer perimeter of the second surface. The geometric-shaped seal is designed to engage with the receiving land capture, and join the first surface and second surface when the geometric-shaped seal is engaged with the receiving land capture. In addition, the seal assembly can maintain a differential in pressure between a first region adjacent to the first surface and a second region adjacent to the second surface.

First claim

What is claimed is:

1. An apparatus comprising:
a seal assembly for interposition between a first surface and a second surface,
the seal assembly comprising:
a seal secured to an outer perimeter of the first surface,
wherein the seal comprises two layers, the first layer being a core layer and the second layer being a stiffening layer disposed over the core layer,
wherein the stiffening layer comprises a magnetic material,
wherein both the core layer and the stiffening layer of the seal include a neck portion and a head portion, the neck portion being proximate to the first surface, the neck portion being narrower than the head portion, and
wherein the seal is elastically deformable;
a capture secured to an outer perimeter of the second surface,
wherein the shape of the capture is configured to be conforming to the shape of the seal such that a portion of the capture distal to the second surface is narrower than a portion of the capture proximate to the second surface, the capture being configured to form a snug and secure fit with the seal while engaged with the seal, wherein the portion of the capture distal to the second surface directly contacts the neck portion of the seal while the capture is engaged with the seal,
wherein the capture is further configured to elastically deform to allow both the core layer and the stiffening layer of the seal to be inserted into the capture, wherein the capture opens to allow placement of the seal and subsequently returns substantially to its original shape to secure the seal in place,
wherein the magnetic material in the stiffening layer magnetically attracts the capture.

2. The apparatus of claim 1 , wherein the first surface is a first aircraft surface and the second surface is a second aircraft surface.

3. The apparatus of claim 2 , wherein the first aircraft surface is part of a door, and wherein the second aircraft surface is formed by an opening configured for engaging with the door.

4. The apparatus of claim 1 , wherein the capture engages two sides of the seal.

5. The apparatus of claim 1 , wherein the capture engages a first side of the seal while a second side of the seal does not engage the receiving land capture, and wherein the first side of the seal is opposite to the second side of the seal.

6. The apparatus of claim 1 , wherein the seal includes a reinforcement layer comprising one of ceramic fiber, glass fiber, metal, magnetic material, or non-metallic material.

7. The apparatus of claim 1 , wherein the seal includes an embedded layer in between the first layer and the second layer.

8. The apparatus of claim 1 , wherein the seal includes a stiffening material that is embedded in the seal.

9. The apparatus of claim 1 , wherein the capture comprises one of a ferritic material, stainless steel, aluminum, magnetic material, or non-metallic material.

10. A seal assembly comprising:
a seal configured to be secured to an outer perimeter of a first surface wherein the seal comprises two layers, the first layer being a core layer and the second layer being a stiffening layer disposed over the core layer, wherein the stiffening layer comprises a magnetic material, wherein both the core layer and the stiffening layer of the seal include a neck portion and a head portion, the neck portion being proximate to the first surface, the neck portion being narrower than the head portion, and wherein the seal is elastically deformable; and
a capture configured to be secured to an outer perimeter of a second surface, wherein the shape of the capture is configured to be conforming to the shape of the seal such that a portion of the capture distal to the second surface is narrower than a portion of the capture proximate to the second surface, the capture being configured to form a snug and secure fit with the seal while engaged with the seal, wherein the capture is further configured to elastically deform to allow both the core layer and the stiffening layer of the seal to be inserted into the capture, wherein the capture opens to allow placement of the seal and subsequently returns substantially to its original shape to secure the seal in place, wherein the portion of the capture distal to the second surface directly contacts the neck portion of the seal while the capture is engaged with the seal, wherein the magnetic material in the stiffening layer magnetically attracts the capture.

11. The seal assembly of claim 10 , wherein the first surface is a first aircraft surface and the second surface is a second aircraft surface.

12. The seal assembly of claim 10 , wherein the capture engages two sides of the seal.

13. The seal assembly of claim 10 , wherein the capture engages one side of the seal.

14. The seal assembly of claim 10 , wherein the seal includes a reinforcement layer comprising one of ceramic fiber, glass fiber, metal, or non-metallic material.

15. The seal assembly of claim 10 , wherein the seal can be disengaged from the capture by applying a force normal to the first surface.

16. A method comprising:
securing a seal to an outer perimeter of a first surface of an aircraft, wherein the seal comprises two layers, the first layer being a core layer and the second layer being a stiffening layer disposed over the core layer, wherein the stiffening layer comprises a magnetic material, wherein both the core layer and the stiffening layer of the seal include a neck portion and a head portion, the neck portion being proximate to the first surface, the neck portion being narrower than the head portion, and wherein the seal is elastically deformable;
placing a capture on a corresponding outer perimeter of a second surface of an aircraft;
engaging the seal with the capture, wherein the shape of the capture is configured to be conforming to the shape of the seal such that a portion of the capture distal to the second surface is narrower than a portion of the capture proximate to the second surface, the capture being further configured to form a snug and secure fit with the seal while engaged with the seal, wherein the capture is further configured to elastically deform to allow both the core layer and the stiffening layer of the seal to be inserted into the capture, wherein the capture opens to allow placement of the seal and subsequently returns substantially to its original shape to secure the seal in place, wherein the portion of the capture distal to the second surface directly contacts the neck portion of the seal while the capture is engaged with the seal, wherein the magnetic material in the stiffening layer magnetically attracts the capture.

17. The method of claim 16 , wherein the second surface includes an opening, and wherein the first surface is configured to cover the opening.

18. The method of claim 16 , wherein the seal includes a reinforcement layer comprising one of ceramic fiber, glass fiber, metal, or non-metallic material.

Assignees

• Boeing Co

Inventors

• Hariram Sham S
• Philipp Paul B

Classifications

• B60J10/38

  using magnetic means · CPC title

• F16J15/121

  with metal reinforcement · CPC title

• B60J10/24

  having tubular parts · CPC title

• B64C1/1407 Primary

  Doors; surrounding frames · CPC title

• E06B7/16

  Sealing arrangements on wings or parts co-operating with the wings ({specially adapted for fireproof or similar closures E06B5/164; } E06B7/098 takes precedence {; fixed sealing joints E04B1/68; devices for fitting sealing strips E04F21/00}) · CPC title