Aircraft Interior Panel Material and Manufacturing Method Therefor

Patent metadata

Field	Value
Publication number	US-2016264229-A1
Application number	US-201415026933-A
Country	US
Kind code	A1
Filing date	Oct 3, 2014
Priority date	Oct 3, 2013
Publication date	Sep 15, 2016
Grant date	—

Abstract

An aircraft interior panel material includes a core member and surface members attached to both surfaces of the core member. The core member includes a plate member composed of balsa wood and having a rectangular shape and uniform thickness. Both surfaces of the plate member in the thickness direction are flat surfaces. Balsa wood is a light weight natural material whereby environmental impact can be reduced. Both surfaces of the plate member in the thickness direction are impregnated with flame retardant, which reduces the flammability of the balsa wood. Impregnation of the plate member with the flame retardant may be performed by: spraying the flame retardant; by immersing the plate member in the flame retardant; or
upon the plate member being immersed in the flame retardant, by applying a pressure larger than the pressure at the depth where the plate member is immersed or cycles thereof to the plate member.

First claim

1 . An aircraft interior panel material comprising:
a core member; and surface members including fiber-reinforced composite material, the surface members being attached to both surfaces of the core member, wherein the core member includes a plate member composed of balsa wood; and both surfaces of the plate member are impregnated with a flame retardant.

2 . The aircraft interior panel material according to claim 1 , wherein each of the surfaces of the plate member is provided with a plurality of surface-area increasing components recessed from the surface and configured to increase the surface area of the surface.

3 . The aircraft interior panel material according to claim 2 , wherein the surface-area increasing components are constituted by any one of: a hole passing through the plate member in a thickness direction thereof, a recessed portion with a closed bottom that has depth in the thickness direction of the plate member, and grooves formed extending in both surfaces of the plate member in the thickness direction of the plate member; or a combination thereof.

4 . A method of manufacturing an aircraft interior panel material provided with surface members including fiber-reinforced composite material attached to both surfaces of a core member, wherein
both surfaces of a plate member to be used as the core member are impregnated with flame retardant.

5 . The method of manufacturing an aircraft interior panel material according to claim 4 , further comprising:
disposing a plurality of surface-area increasing components in each of the surfaces of the plate member prior to impregnation of the surfaces of the plate member with the flame retardant, the surface-area increasing components being recessed from the surface and configured to increase the surface area of the surface.

6 . The method of manufacturing an aircraft interior panel material according to claim 5 , wherein
the attaching of the surface members to both surfaces of the core member is performed by: upon the surface members being layered on both surfaces of the core member, melting resin with which the surface members have been impregnated by applying pressure and heat to bond the resin to the surfaces of the plate member and the surface-area increasing components.

7 . The method of manufacturing an aircraft interior panel material according to claim 4 , wherein
the impregnation of the surfaces of the plate member with the flame retardant is performed by: upon immersing the plate member in the flame retardant and applying a pressure larger than a pressure at a depth where the plate member is immersed to the plate member, maintaining this state for a predetermined period of time.

8 . The method of manufacturing an aircraft interior panel material according to claim 5 , wherein
the impregnation of the surfaces of the plate member with the flame retardant is performed by: upon immersing the plate member in the flame retardant and applying a pressure larger than a pressure at a depth where the plate member is immersed to the plate member, maintaining this state for a predetermined period of time.

9 . The method of manufacturing an aircraft interior panel material according to claim 6 , wherein
the impregnation of the surfaces of the plate member with the flame retardant is performed by: upon immersing the plate member in the flame retardant and applying a pressure larger than a pressure at a depth where the plate member is immersed to the plate member, maintaining this state for a predetermined period of time.

Assignees

• Yokohama Rubber Co Ltd

Inventors

• Taguchi Yuji
• Kobayashi Takafumi
• Hirose Ayano

Classifications

• B64C1/066 Primary

  Interior liners · CPC title

• B64D2045/009

  Fire detection or protection; Erosion protection, e.g. from airborne particles · CPC title

• B64D11/00 Primary

  Passenger or crew accommodation; Flight-deck installations not otherwise provided for · CPC title

• B32B2260/021

  Fibrous or filamentary layer · CPC title

• B32B2307/718

  Weight, e.g. weight per square meter · CPC title