Decompression panel assembly and methods of assembling the same

Patent metadata

Field	Value
Publication number	US-10399660-B2
Application number	US-201615174064-A
Country	US
Kind code	B2
Filing date	Jun 6, 2016
Priority date	Jun 6, 2016
Publication date	Sep 3, 2019
Grant date	Sep 3, 2019

Abstract

A decompression panel assembly for use in an aircraft includes a frame including a first surface and an opposing second surface, wherein the frame defines a grille opening and at least partially defines a flow path opening. The decompression panel assembly also includes a face panel having a first surface retained against the frame second surface such that the face panel at least partially covers the grille opening. A retention mechanism is coupled to the face panel and is configured to retain the face panel against the frame in a closed position.

First claim

What is claimed is:

1. A decompression panel assembly for use in an aircraft, said decompression panel assembly comprising:
a frame comprising a first surface and an opposing second surface, wherein said frame defines a grille opening configured to receive a grille member, wherein said frame further at least partially defines a flow path opening;
a face panel comprising a first surface and an opposing second surface, wherein said first surface is retained against said frame second surface such that said face panel at least partially covers said grille opening;
a retention mechanism coupled to and extending from said second surface of said face panel away from said frame, said retention mechanism configured to retain said face panel against said frame in a closed position; and
a containment device positioned adjacent a second surface of said face panel and configured to enclose said face panel when said face panel is in an open position.

2. The decompression panel assembly in accordance with claim 1 , wherein said retention mechanism extends from said face panel to said containment device.

3. The decompression panel assembly in accordance with claim 1 , wherein said retention mechanism comprises at least one spring that biases said face panel towards said frame.

4. The decompression panel assembly in accordance with claim 1 , wherein said retention mechanism comprises at least one frangible member that is configured to fracture when said face panel is subjected to a predetermined pressure differential.

5. The decompression panel assembly in accordance with claim 1 , wherein said retention mechanism is configured to allow said face panel to move from the closed position to an open position when said face panel is subjected to a predetermined pressure differential.

6. The decompression panel assembly in accordance with claim 1 , wherein said grille member is coupled to said frame such that said grille member spans said grille opening, wherein the flow path opening is defined between said frame and said grille member.

7. An aircraft comprising the decompression panel assembly in accordance with claim 1 .

8. The decompression panel assembly in accordance with claim 1 , wherein the flow path opening extends about a perimeter of said frame and wherein said grille opening is bounded by said frame.

9. The decompression panel assembly in accordance with claim 8 , wherein the flow path opening is at least partially defined by said second surface of said frame, and wherein said grille opening is defined by said first surface of said frame.

10. A method of installing a decompression panel assembly in an aircraft, the decompression panel assembly including a body panel, frame, a face panel, and at least one retention mechanism, said method comprising:
coupling the frame to the body panel, wherein the frame includes a first surface and an opposing second surface, and wherein the frame defines a grille opening configured to receive a grille member, wherein the frame further at least partially defines a flow path opening;
positioning the face panel adjacent the frame such that a first surface of the face panel is retained against the frame second surface such that the face panel at least partially covers the grille opening;
coupling the at least one retention mechanism to a second surface of the face panel such that the at least one retention mechanism extends away from the frame and is configured to retain the face panel against the frame in a closed position, wherein the second surface of the face panel is opposite the first surface of the face panel; and
coupling a containment device to at least one of the frame and the body panel such that the containment device is positioned adjacent a second surface of the face panel, wherein the containment device is configured to contain said face panel when said face panel is in an open position.

11. The method in accordance with claim 10 , wherein coupling the at least one retention mechanism to the face panel comprises coupling at least one spring to the face panel to bias the face panel towards the frame.

12. The method in accordance with claim 10 , wherein coupling the at least one retention mechanism to the face panel comprises coupling at least one frangible member to the face panel, wherein the at least one frangible member is configured to fracture when the face panel is subjected to a predetermined pressure differential.

13. The method in accordance with claim 10 , further comprising coupling a grille member to the frame such that the grille member spans the grille opening, wherein the flow path opening is defined between the frame and the grille member.

14. The method in accordance with claim 10 , wherein coupling the at least one retention mechanism to the face panel comprises coupling the at least one retention mechanism such that the retention mechanism is configured to allow the face panel to move from the closed position to an open position when the face panel is subjected to a predetermined pressure differential.

15. An aircraft comprising:
a sidewall assembly comprising:
a sidewall; and
a decompression panel assembly coupled to said sidewall, wherein said decompression panel assembly comprises:
a frame comprising a first surface and an opposing second surface, wherein said frame defines a grille opening configured to receive a grille member, wherein said frame further at least partially defines a flow path opening that are each defined between said first and said second surfaces;
a face panel comprising a first surface and an opposing second surface, wherein said first surface is retained against said frame second surface such that said face panel at least partially covers said grille opening; and
a retention mechanism coupled to and extending from said second surface of said face panel away from said frame, said retention mechanism configured to retain said face panel against said frame in a closed position; and
a containment device positioned adjacent a second surface of said face panel and configured to enclose said face panel when said face panel is in an open position.

16. The aircraft in accordance with claim 15 , wherein said retention mechanism comprises at least one of at least one spring that biases said face panel towards said frame and at least one frangible member that is configured to fracture when said face panel is subjected to a predetermined pressure differential.

17. The aircraft in accordance with claim 15 , wherein said retention mechanism is configured to allow said face panel to move from the closed position to an open position when said face panel is subjected to a predetermined pressure differential.

Assignees

• Boeing Co
• The Boening Company

Inventors

• Brown Douglas Alan
• Weston Adam Robert
• Imada Brian Tatsuo

Classifications

• B64C1/066

  Interior liners · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C2001/009

  comprising decompression panels or valves for pressure equalisation in fuselages or floors · CPC title

• B64C1/18 Primary

  Floors · CPC title

• Y02T50/46

  Cross-Sectional Technologies · mapped topic