Light-limiting header assembly for a transition area within an interior cabin of an aircraft

Patent metadata

Field	Value
Publication number	US-2016167786-A1
Application number	US-201514835850-A
Country	US
Kind code	A1
Filing date	Aug 26, 2015
Priority date	Dec 12, 2014
Publication date	Jun 16, 2016
Grant date	—

Abstract

A header assembly is configured to be secured between an inboard structure and an outboard structure within an internal cabin of an aircraft. The header assembly may include a main body including a first panel connected to an opposed second panel by a base panel. The main body is configured to limit light from passing therethrough. At least three anchoring members are configured to securely connect the main body to at least three reciprocal structures of the inboard and outboard structures.

First claim

What is claimed is:

1 . A header assembly configured to be secured between an inboard structure and an outboard structure within an internal cabin of an aircraft, the header assembly comprising:
a main body including a first panel connected to an opposed second panel by a base panel, wherein the main body is configured to limit light from passing therethrough; and at least three anchoring members that are configured to securely connect the main body to at least three reciprocal structures of the inboard and outboard structures.

2 . The header assembly of claim 1 , wherein the main body includes an inboard end configured to connect to the inboard structure and an outboard end configured to connect to the outboard structure, wherein the at least three anchoring members comprise first and second anchoring members proximate to the outboard end and a third anchoring member proximate to the inboard end.

3 . The header assembly of claim 1 , wherein the base panel comprises a track channel configured to receive and retain a curtain track.

4 . The header assembly of claim 1 , wherein the main body is formed of a solid, non-porous composite material.

5 . The header assembly of claim 1 , wherein a space is formed between the first and second panels, and wherein at least one seal is positioned within the space between the first and second panels, wherein the at least one seal is configured to sealingly connect to an internal surface of the internal cabin of the aircraft.

6 . The header assembly of claim 1 , wherein one or both of the first and second panels includes an outwardly-curved surface.

7 . The header assembly of claim 1 , wherein the main body is symmetrical about a central longitudinal plane.

8 . The header assembly of claim 1 , further comprising an extension beam secured to the main body, wherein the at least three anchoring members are secured to the extension beam.

9 . The header assembly of claim 1 , wherein the at least three anchoring members comprise an inboard support fitting, a first outboard support fitting, and a second outboard support fitting.

10 . The header assembly of claim 9 , wherein the inboard support fitting comprises a grommet having a bracket that defines an internal channel that is configured to receive and retain a bayonet of a connection fastener extending from the inboard structure, and wherein each of the first and second outboard support fittings comprises one of a structure that is configured to be latchably engaged or a latch that is configured to latchably engage the structure.

11 . The header assembly of claim 1 , wherein the main body is configured to be moved between a secured position between the inboard and outboard structures and a pivoted position in which the main body is pivotally secured to one of the inboard or outboard structure and disconnected from the other of the inboard or outboard structures.

12 . An aircraft assembly comprising:
a fuselage defining an internal cabin; an inboard structure and an outboard structure separated by an aisle within the internal cabin; and a header assembly secured between the inboard structure and the outboard structure, wherein the header assembly is positioned above a moveable curtain assembly, the header assembly comprising:
a main body formed of a solid, non-porous composite material, wherein the main body comprises a first panel connected to an opposed second panel by a base panel, wherein the main body is configured to limit light from passing therethrough; and
at least three anchoring members that are configured to securely connect the main body to at least three reciprocal structures of the inboard and outboard structures.

13 . The aircraft assembly of claim 12 , wherein the main body includes an inboard end that connects to the inboard structure and an outboard end that connects to the outboard structure, wherein the at least three anchoring members comprise first and second anchoring members proximate to the outboard end and a third anchoring member proximate to the inboard end.

14 . The aircraft assembly of claim 12 , further comprising a curtain track, wherein the base panel comprises a track channel that retains the curtain track that connects to the moveable curtain assembly.

15 . The aircraft assembly of claim 12 , wherein a space is formed between the first and second panels, and wherein at least one seal is secured within the space between the first and second panels, wherein the at least one seal sealingly connects to an internal surface of the internal cabin of the aircraft.

16 . The aircraft assembly of claim 12 , wherein one or both of the first and second panels includes an outwardly-curved surface.

17 . The aircraft assembly of claim 12 , wherein the header assembly further comprises an extension beam secured to the main body, wherein the at least three anchoring members are secured to the extension beam, wherein the at least three anchoring members comprise an inboard support fitting, a first outboard support fitting, and a second outboard support fitting, wherein the inboard support fitting comprises a grommet having a bracket that defines an internal channel that retains a bayonet of a connection fastener extending from the inboard structure, and wherein each of the first and second outboard support fittings comprises one of a structure that is latchably engaged or a latch that latchably engages the structure.

18 . The aircraft assembly of claim 12 , wherein the main body is movable between a secured position between the inboard and outboard structures and a pivoted position in which the main body is pivotally secured to one of the inboard or outboard structure and disconnected from the other of the inboard or outboard structures.

19 . The aircraft assembly of claim 12 , wherein the outboard structure comprises one of a first overhead storage bin, a partition wall, a galley, or a lavatory, and wherein the inboard structure comprises one or more of a second overhead storage bin, a partition wall, a galley, or a lavatory.

20 . A header assembly configured to be secured between an inboard structure and an outboard structure within an internal cabin of an aircraft, the header assembly comprising:
a main body formed of a solid, opaque, on-porous composite material, wherein the main body is configured to limit light from passing therethrough, wherein the main body comprises a first panel connected to an opposed second panel by a base panel, an inboard end configured to connect to the inboard structure, and an outboard end configured to connect to the outboard structure, wherein the base panel comprises a track channel configured to receive and retain a curtain track, wherein a space is formed between the first and second panels, wherein the main body is configured to be moved between a secured position between the inboard and outboard structures and a pivoted position in which the main body is pivotally secured to one of the inboard or outboard structure and disconnected from the other of the inboard or outboard structures; at least one seal secured within the space between the first and second panels, wherein the at least one seal is configured to sealingly connect to an internal surface of the internal cabin of the aircraft an extension beam secured to the main body; and at least three anchoring members secured to the extension beam, wherein the at least three anchoring members are configured to securely connect the main body to at least three reciprocal structures of the inboard and o

Assignees

• Boeing Co

Inventors

• Maclay William H
• Withers Kevan
• Zarkowskyj Peter J
• Jensen Charles C
• Wentland Mark E
• Iaszfalvi Alexandru

Classifications

• B64D11/0023 Primary

  Movable or removable cabin dividers, e.g. for class separation · CPC title