Decompression panel assembly and methods of manufacturing the same

Patent metadata

Field	Value
Publication number	US-10494079-B2
Application number	US-201615085411-A
Country	US
Kind code	B2
Filing date	Mar 30, 2016
Priority date	Mar 30, 2016
Publication date	Dec 3, 2019
Grant date	Dec 3, 2019

Abstract

A decompression panel assembly for use in an aircraft includes a body portion comprising a plurality of frame members defining a plurality of openings in the body portion. The decompression panel assembly also includes a baffle member integrally formed with the plurality of frame members such that the baffle member removably obstructs at least one opening of the plurality of openings. The baffle member is configured for at least partial displacement from the at least one opening during a decompression event.

First claim

What is claimed is:

1. A decompression panel assembly for use in an aircraft, said decompression panel assembly comprising:
a body portion comprising a plurality of frame members defining a plurality of openings in said body portion;
a baffle member integrally formed with said plurality of frame members, the baffle member comprising a plurality of detachable sections each associated with, and configured to removably obstruct, at least one opening of said plurality of openings, wherein said baffle member is configured for at least partial displacement from said at least one opening during a decompression event.

2. The decompression panel assembly in accordance with claim 1 , wherein said baffle member comprises a plurality of frangible seams configured to yield during a decompression event.

3. The decompression panel assembly in accordance with claim 2 , wherein said plurality of detachable sections are defined by said plurality of frangible seams.

4. The decompression panel assembly in accordance with claim 3 , wherein said frangible seams form an entire perimeter of each detachable section such that each detachable section is detached from said plurality of frame members during a decompression event to enable air flow through said plurality of openings.

5. The decompression panel assembly in accordance with claim 3 , wherein said frangible seams form only a portion of a perimeter of each detachable section such that each detachable section is hingedly coupled to said plurality of frame members during a decompression event to enable air flow through said plurality of openings.

6. The decompression panel assembly in accordance with claim 1 , wherein said plurality of frame members comprise an inboard edge and an outboard edge, wherein said baffle member is integrally formed with said plurality of frame members proximate said outboard edge.

7. The decompression panel assembly in accordance with claim 1 , wherein said baffle member obstructs each opening of said plurality of openings.

8. The decompression panel assembly in accordance with claim 1 , wherein said baffle member obstructs fewer than all of said plurality of openings.

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

10. A method of manufacturing a decompression panel assembly for use in an aircraft, said method comprising:
forming a body portion with a plurality of frame members, wherein the plurality of frame members define a plurality of openings in the body portion;
integrally forming a baffle member with the body portion and the plurality of frame members such that the baffle member removably obstructs at least one opening of the plurality of openings, wherein the baffle member is configured for at least partial displacement from the at least one opening during a decompression event; and
forming a plurality of frangible seams in the baffle member to define a plurality of detachable sections each being associated with an opening of the plurality of openings, wherein the frangible seams are configured to yield in a decompression event.

11. The method in accordance with claim 10 , further comprising forming the baffle member and the plurality of frame members from the same material.

12. The method in accordance with claim 10 , wherein forming the body portion and forming the baffle member comprises forming the body portion and forming the baffle member via at least one of injection molding and additive manufacturing.

13. The method in accordance with claim 10 , further comprising forming the frangible seams simultaneously with the baffle member.

14. The method in accordance with claim 10 , further comprising forming the frangible seams after forming the baffle member.

15. The method in accordance with claim 10 , wherein forming a plurality of frangible seams includes forming a plurality of frangible seams about an entire perimeter of each detachable section such that each detachable section is fully detached from the plurality of frame members during a decompression event to enable air flow through the plurality of openings.

16. The method in accordance with claim 10 , wherein forming a plurality of frangible seams includes forming a plurality of frangible seams about only a portion of a perimeter of each detachable section such that each detachable section is hingedly coupled to the plurality of frame members during a decompression event to enable air flow through the plurality of openings.

17. A decompression panel assembly for use in an aircraft, said decompression panel assembly comprising:
a body portion comprising a plurality of frame members defining a plurality of openings in said body portion;
a baffle member integrally formed with said plurality of frame members such that said baffle member removably obstructs at least one opening of said plurality of openings, wherein said baffle member is configured for at least partial displacement from said at least one opening during a decompression event, wherein said baffle member comprises a plurality of frangible seams configured to yield during a decompression event.

18. The decompression panel assembly in accordance with claim 17 , wherein said baffle member comprises a plurality of detachable sections defined by said plurality of frangible seams, wherein each detachable section is associated with an opening of said plurality of openings.

19. The decompression panel assembly in accordance with claim 18 , wherein said frangible seams form an entire perimeter of each detachable section such that each detachable section is detached from said plurality of frame members during a decompression event to enable air flow through said plurality of openings.

20. The decompression panel assembly in accordance with claim 18 , wherein said frangible seams form only a portion of a perimeter of each detachable section such that each detachable section is hingedly coupled to said plurality of frame members during a decompression event to enable air flow through said plurality of openings.

Assignees

• Boeing Co

Inventors

• Sterling David E
• Griffing James Scott
• Perkins Thomas Seth
• Beck Hannah Katherine
• Weston Adam Robert
• Walter Sara Lynn

Classifications

• 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