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1. WO2020003610 - COMPOSITE MATERIAL AND METHOD FOR CURING COMPOSITE MATERIAL

Publication Number WO/2020/003610
Publication Date 02.01.2020
International Application No. PCT/JP2019/007162
International Filing Date 26.02.2019
IPC
B PERFORMING OPERATIONS; TRANSPORTING
32
LAYERED PRODUCTS
B
LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
3
Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form
10
characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material
12
characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B PERFORMING OPERATIONS; TRANSPORTING
32
LAYERED PRODUCTS
B
LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
3
Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form
02
characterised by features of form at particular places, e.g. in edge regions
04
characterised by a layer folded at the edge, e.g. over another layer
B PERFORMING OPERATIONS; TRANSPORTING
32
LAYERED PRODUCTS
B
LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
3
Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form
10
characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material
24
characterised by an apertured layer, e.g. of expanded metal
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
C
AEROPLANES; HELICOPTERS
1
Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
D
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS
45
Aircraft indicators or protectors not otherwise provided for
02
Lightning protectors; Static dischargers
B32B 3/12 (2006.01)
B32B 3/04 (2006.01)
B32B 3/24 (2006.01)
B64C 1/00 (2006.01)
B64D 45/02 (2006.01)
CPC
B32B 3/04
B32B 3/12
B64C 1/00
B64D 45/02
Applicants
  • 三菱重工業株式会社 MITSUBISHI HEAVY INDUSTRIES, LTD. [JP/JP]; 東京都千代田区丸の内三丁目2番3号 2-3, Marunouchi 3-Chome, Chiyoda-ku, Tokyo 1008332, JP
Inventors
  • 野間 一希 NOMA, Kazuki; JP
  • 秋山 浩庸 AKIYAMA, Hiromichi; JP
  • 小佐々 敏生 KOZASA, Toshio; JP
  • 金升 将征 KANEMASU Masayuki; JP
  • 森島 駿一 MORISHIMA, Shunichi; JP
Agents
  • 藤田 考晴 FUJITA, Takaharu; JP
Priority Data
2018-12306728.06.2018JP
Publication Language Japanese (JA)
Filing Language Japanese (JA)
Designated States
Title
(EN) COMPOSITE MATERIAL AND METHOD FOR CURING COMPOSITE MATERIAL
(FR) MATÉRIAU COMPOSITE ET PROCÉDÉ POUR LE DURCISSEMENT D'UN MATÉRIAU COMPOSITE
(JA) 複合材及び複合材の硬化方法
Abstract
(EN)
The purpose of the present invention is to provide a composite material that is capable of suppressing decrease in the strength, which is caused by bending of fibers of a skin material during the time when the composite material is cured. A composite material (1) according to the present invention is provided with a honeycomb core (2), a first skin material (4), a second skin material (6), a thunder-resistant mesh (7) and a resin material (8); and the resin material (8) is not arranged in a neighborhood portion (9) which is the region corresponding to the region at the front end of the honeycomb core (2). A first film adhesive (3) is arranged between the first skin material (4) and the honeycomb core (2); a second film adhesive (5) is arranged between the second skin material (6) and the honeycomb core (2); and a fourth film adhesive is arranged in the neighborhood portion (9) of the resin material (8) in a weight per square meter, which is lower than those of the first film adhesive (3) and the second film adhesive (5).
(FR)
La présente invention a pour objet un matériau composite qui permet de supprimer une diminution de la résistance, qui est provoquée par la flexion de fibres d'un matériau de peau pendant la période où le matériau composite est durci. À cet effet, la présente invention porte sur un matériau composite (1) qui est pourvu d'une âme en nid-d'abeilles (2), d'un premier matériau de peau (4), d'un second matériau de peau (6), d'un maillage résistant au tonnerre (7) et d'un matériau en résine (8), le matériau en résine (8) n'étant pas disposé dans une partie de voisinage (9) qui est la zone correspondant à la zone à l'extrémité avant de l'âme en nid-d'abeilles (2). Un premier adhésif sous forme de film (3) est disposé entre le premier matériau de peau (4) et l'âme en nid-d'abeilles (2) ; un deuxième adhésif sous forme de film (5) est disposé entre le second matériau de peau (6) et l'âme en nid-d'abeilles (2) ; et un quatrième adhésif sous forme de film est disposé dans la partie de voisinage (9) du matériau en résine (8) en un certain poids par mètre carré, qui est inférieur à ceux du premier adhésif sous forme de film (3) et du deuxième adhésif sous forme de film (5).
(JA)
複合材の硬化時において、スキン材の繊維が屈曲し、強度低下を招くことを抑制することができる複合材を提供することを目的とする。複合材(1)は、ハニカムコア(2)と、第1のスキン材(4)と、第2のスキン材(6)と、耐雷メッシュ(7)と、樹脂材料(8)と、を備え、樹脂材料(8)のうち、ハニカムコア(2)の端部の先端の領域に対応する領域の近傍部分(9)には、樹脂材料(8)が配置されていない。第1のスキン材(4)とハニカムコア(2)との間に、第1のフィルム接着剤(3)が配置されており、第2のスキン材(6)とハニカムコア(2)との間に、第2のフィルム接着剤(5)が配置されており、樹脂材料(8)における近傍部分(9)には、第1のフィルム接着剤(3)及び第2のフィルム接着剤(5)よりも低目付の第4のフィルム接着剤が配置されている。
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