Sandwich structure, method of producing sandwich structure, and aircraft

Patent metadata

Field	Value
Publication number	US-2025065595-A1
Application number	US-202418800895-A
Country	US
Kind code	A1
Filing date	Aug 12, 2024
Priority date	Aug 24, 2023
Publication date	Feb 27, 2025
Grant date	—

Abstract

A sandwich structure includes a first ply of CFRP, a second ply of CFRP and a honeycomb or foam core. The first ply of the CFRP includes first carbon fibers and thermoset resin which is matrix reinforced with the first carbon fibers. The second ply of the CFRP includes second carbon fibers and thermoset resin which is matrix reinforced with the second carbon fibers. The core is sandwiched between the first and second plies of the CFRP. Ply thicknesses of the first and second plies of the CFRP are each not less than 0.05 mm and not more than 0.15 mm. The first thermoset resin is directly bonded to the core without interposing any other layer between the first thermoset resin and the core. The second thermoset resin is directly bonded to the core without interposing any other layer between the second thermoset resin and the core.

First claim

What is claimed is:

1 . A sandwich structure comprising:
at least one first ply of carbon fiber reinforced plastic including first carbon fibers and first thermoset resin which is matrix reinforced with the first carbon fibers; at least one second ply of carbon fiber reinforced plastic including second carbon fibers and second thermoset resin which is matrix reinforced with the second carbon fibers; and a core sandwiched between the at least one first ply of the carbon fiber reinforced plastic and the at least one second ply of the carbon fiber reinforced plastic, the core being a honeycomb core or a foam core, wherein a first ply thickness of the at least one first ply of the carbon fiber reinforced plastic and a second ply thickness of the at least one second ply of the carbon fiber reinforced plastic are each not less than 0.05 mm and not more than 0.15 mm, wherein the first thermoset resin is directly bonded to the core without interposing any other layer between the first thermoset resin and the core, and wherein the second thermoset resin is directly bonded to the core without interposing any other layer between the second thermoset resin and the core.

2 . An aircraft including a structural material made of the sandwich structure according to claim 1 .

3 . A method of producing a sandwich structure,
the sandwich structure comprising: at least one first ply of carbon fiber reinforced plastic; at least one second ply of carbon fiber reinforced plastic; and a core sandwiched between the at least one first ply of the carbon fiber reinforced plastic and the at least one second ply of the carbon fiber reinforced plastic, the core being a honeycomb core or a foam core, the method comprising: using a first prepreg sheet, of which thickness is not less than 0.05 mm and not more than 0.15 mm, as a material of the at least one first ply of the carbon fiber reinforced plastic, the first prepreg sheet including first carbon fibers and first uncured thermoset resin which is matrix reinforced with the first carbon fibers; using a second prepreg sheet, of which thickness is not less than 0.05 mm and not more than 0.15 mm, as a material of the at least one second ply of the carbon fiber reinforced plastic, the second prepreg sheet including second carbon fibers and second uncured thermoset resin which is matrix reinforced with the second carbon fibers; heating and curing the first uncured thermoset resin with the first uncured thermoset resin in direct contact with one side of the core without interposing any other layer between the first uncured thermoset resin and the core so that the first cured thermoset resin is directly bonded to the one side of the core; and heating and curing the second uncured thermoset resin with the second uncured thermoset resin in direct contact with another side of the core without interposing any other layer between the second uncured thermoset resin and the core so that the second cured thermoset resin is directly bonded to the another side of the core.

4 . The method according to claim 3 ,
wherein a fiber volume of the first prepreg sheet and a fiber volume of the second prepreg sheet are each not less than 20 volume % and not more than 40 volume %.

5 . The method according to claim 3 ,
further comprising: curing or semi-curing at least one surface ply by heating a third prepreg sheet or a laminate of prepreg sheets, including the third prepreg sheet, under pressure, the third prepreg sheet being a material of a carbon fiber reinforced plastic ply which does not directly contact with the core and forms one surface of the sandwich structure; disposing the core sandwiched between the first prepreg sheet and the second prepreg sheet, on the cured or semi-cured at least one surface ply directly or with another prepreg interposed; and producing the sandwich structure including the cured at least one surface ply by heating and curing the first uncured thermoset resin and the second uncured thermoset resin disposed on the cured at least one surface ply, or heating and curing the semi-cured at least one surface ply, the first uncured thermoset resin disposed on the semi-cured at least one surface ply and the second uncured thermoset resin disposed on the semi-cured at least one surface ply.

6 . The method according to claim 3 ,
further comprising: using a fourth prepreg sheet, of which a fiber volume is more than 40 volume % and not more than 60 volume %, as another material of the at least one first ply of the carbon fiber reinforced plastic, the fourth prepreg sheet including uncured thermoset resin which is not brought into direct contact with the core.

7 . The method according to claim 4 ,
further comprising: curing or semi-curing at least one surface ply by heating a third prepreg sheet or a laminate of prepreg sheets, including the third prepreg sheet, under pressure, the third prepreg sheet being a material of a carbon fiber reinforced plastic ply which does not directly contact with the core and forms one surface of the sandwich structure; disposing the core sandwiched between the first prepreg sheet and the second prepreg sheet, on the cured or semi-cured at least one surface ply directly or with another prepreg interposed; and producing the sandwich structure including the cured at least one surface ply by heating and curing the first uncured thermoset resin and the second uncured thermoset resin disposed on the cured at least one surface ply, or heating and curing the semi-cured at least one surface ply, the first uncured thermoset resin disposed on the semi-cured at least one surface ply and the second uncured thermoset resin disposed on the semi-cured at least one surface ply.

8 . The method according to claim 4 ,
further comprising: using a fourth prepreg sheet, of which a fiber volume is more than 40 volume % and not more than 60 volume %, as another material of the at least one first ply of the carbon fiber reinforced plastic, the fourth prepreg sheet including uncured thermoset resin which is not brought into direct contact with the core.

9 . The method according to claim 5 ,
further comprising: using a fourth prepreg sheet, of which a fiber volume is more than 40 volume % and not more than 60 volume %, as another material of the at least one first ply of the carbon fiber reinforced plastic, the fourth prepreg sheet including uncured thermoset resin which is not brought into direct contact with the core.

10 . The method according to claim 7 ,
further comprising: using a fourth prepreg sheet, of which a fiber volume is more than 40 volume % and not more than 60 volume %, as another material of the at least one first ply of the carbon fiber reinforced plastic, the fourth prepreg sheet including uncured thermoset resin which is not brought into direct contact with the core.

11 . The sandwich structure according to claim 1 ,
wherein a fiber volume of the at least one first ply of the carbon fiber reinforced plastic and a fiber volume of the at least one second ply of the carbon fiber reinforced plastic are each not less than 20 volume % and not more than 40 volume %.

12 . The sandwich structure according to claim 1 ,
further comprising: another ply of carbon fiber reinforced plastic, of which a fiber volume is more than 40 volume % and not more than 60 volume %, the another ply of the carbon fiber reinforced plastic being non-contact with the core.

13 . The sandwich structure according to claim 11 ,
further comprising: another ply of carbon fiber reinforced plastic, of which a fiber volume is more than 40 volume % and not more than 60 volume %, the anot

Assignees

• Subaru Corp
• Gh Craft Ltd

Inventors

• Hirabayashi Daisuke
• Suyama Yoichi
• SUKEMUNE Takeshi

Classifications

• B64C2001/0072

  from composite materials · CPC title

• B32B2605/18

  Aircraft · CPC title

• B32B2262/106

  Carbon fibres, e.g. graphite fibres · CPC title

• B29D99/0089

  Producing honeycomb structures (consisting of porous ceramic ware C04B38/0006) · CPC title

• B64C1/068

  Fuselage sections · CPC title