WO2015050239A1 - 航空機内装品用パネル材およびその製造方法 - Google Patents
航空機内装品用パネル材およびその製造方法 Download PDFInfo
- Publication number
- WO2015050239A1 WO2015050239A1 PCT/JP2014/076508 JP2014076508W WO2015050239A1 WO 2015050239 A1 WO2015050239 A1 WO 2015050239A1 JP 2014076508 W JP2014076508 W JP 2014076508W WO 2015050239 A1 WO2015050239 A1 WO 2015050239A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- plate
- aircraft interior
- flame retardant
- panel material
- core material
- Prior art date
Links
- 239000000463 material Substances 0.000 title claims abstract description 128
- 238000004519 manufacturing process Methods 0.000 title claims description 13
- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 claims abstract description 58
- 239000003063 flame retardant Substances 0.000 claims abstract description 57
- 239000011162 core material Substances 0.000 claims abstract description 41
- 240000007182 Ochroma pyramidale Species 0.000 claims abstract description 21
- 238000005470 impregnation Methods 0.000 claims abstract description 5
- 239000011347 resin Substances 0.000 claims description 8
- 229920005989 resin Polymers 0.000 claims description 8
- 239000003733 fiber-reinforced composite Substances 0.000 claims description 7
- 238000010438 heat treatment Methods 0.000 claims description 6
- 238000003825 pressing Methods 0.000 claims description 3
- 238000002844 melting Methods 0.000 claims description 2
- 230000008018 melting Effects 0.000 claims description 2
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000007613 environmental effect Effects 0.000 abstract description 8
- 239000013585 weight reducing agent Substances 0.000 abstract description 5
- 239000005445 natural material Substances 0.000 abstract description 2
- 238000005507 spraying Methods 0.000 abstract description 2
- 230000001351 cycling effect Effects 0.000 abstract 1
- 238000002474 experimental method Methods 0.000 description 13
- 238000002485 combustion reaction Methods 0.000 description 12
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 8
- 238000000034 method Methods 0.000 description 7
- 230000005484 gravity Effects 0.000 description 6
- 239000000853 adhesive Substances 0.000 description 5
- 230000001070 adhesive effect Effects 0.000 description 5
- 238000007654 immersion Methods 0.000 description 5
- 230000003068 static effect Effects 0.000 description 4
- KGBXLFKZBHKPEV-UHFFFAOYSA-N boric acid Chemical compound OB(O)O KGBXLFKZBHKPEV-UHFFFAOYSA-N 0.000 description 3
- 239000004327 boric acid Substances 0.000 description 3
- 238000005553 drilling Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000011521 glass Substances 0.000 description 3
- 239000002023 wood Substances 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N Phenol Chemical compound OC1=CC=CC=C1 ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 description 2
- NBIIXXVUZAFLBC-UHFFFAOYSA-N Phosphoric acid Chemical compound OP(O)(O)=O NBIIXXVUZAFLBC-UHFFFAOYSA-N 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 238000003801 milling Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910000147 aluminium phosphate Inorganic materials 0.000 description 1
- 239000004760 aramid Substances 0.000 description 1
- 229920006231 aramid fiber Polymers 0.000 description 1
- 229920003235 aromatic polyamide Polymers 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 230000012447 hatching Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 239000005011 phenolic resin Substances 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- RMAQACBXLXPBSY-UHFFFAOYSA-N silicic acid Chemical compound O[Si](O)(O)O RMAQACBXLXPBSY-UHFFFAOYSA-N 0.000 description 1
- 235000012239 silicon dioxide Nutrition 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000002759 woven fabric Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/066—Interior liners
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B21/00—Layered products comprising a layer of wood, e.g. wood board, veneer, wood particle board
- B32B21/10—Next to a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2250/00—Layers arrangement
- B32B2250/40—Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/30—Properties of the layers or laminate having particular thermal properties
- B32B2307/306—Resistant to heat
- B32B2307/3065—Flame resistant or retardant, fire resistant or retardant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/718—Weight, e.g. weight per square meter
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2471/00—Floor coverings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2607/00—Walls, panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/009—Fire detection or protection; Erosion protection, e.g. from airborne particles
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Definitions
- the present invention relates to a panel material for aircraft interior parts and a manufacturing method thereof.
- aircraft interior items examples include an aircraft restroom unit, a galley, a luggage compartment, and the like, and these aircraft interior items include a panel material.
- panel materials for aircraft interior parts such as floor panels, wall panels, and ceiling panels, are required to have strength and rigidity, as well as flame retardancy and weight reduction.
- a panel material is comprised by sticking the surface material which consists of a fiber reinforced composite material on both surfaces of the core material of the honeycomb structure which consists of an aramid fiber, glass fiber, aluminum, etc. (patent document 1). reference).
- the present invention has been devised in view of the above circumstances, and its object is to provide aircraft interior parts that are advantageous in reducing environmental impact while satisfying the demands for cost reduction, strength, rigidity, flame retardancy, and weight reduction. It is providing the panel material for manufacturing, and its manufacturing method.
- an invention according to claim 1 is a panel material for aircraft interior parts in which a surface material made of a fiber-reinforced composite material is attached to both surfaces of a core material, wherein the core material is a balsa material.
- the surface of the plate member is impregnated with a flame retardant.
- the invention according to claim 2 is characterized in that the surface of the plate-like member is provided with a plurality of surface area increasing structures that are recessed from the surface and increase the surface area of the surface.
- the invention according to claim 3 is characterized in that the surface area increasing structure portion includes a hole penetrating the plate member in the thickness direction, a recess having a depth in the thickness direction of the plate member and a bottom portion, It is characterized by comprising one or a combination of concave grooves formed on both sides in the thickness direction of the plate member.
- Invention of Claim 4 is a manufacturing method of the panel material for aircraft interior parts by which the surface material which consists of a fiber reinforced composite material was attached to both surfaces of the core material, Comprising: A flame retardant is given to the surface as said core material A plate member made of impregnated balsa material is used.
- the invention according to claim 5 is a plurality of surface area increasing structures for increasing the surface area of the surface of the plate-like member that is recessed from the surface before the surface of the plate-like member is impregnated with the flame retardant. It is characterized by providing a part.
- the attachment of the surface material to both surfaces of the core material is performed by applying pressure and heating in a state where the surface material is laminated on both surfaces of the core material, and impregnating the surface material. It is characterized in that it is carried out by melting the existing resin and adhering it to the surface of the plate member and the surface area increasing structure.
- the invention according to claim 7 is a depth in which the surface of the plate member is impregnated with the flame retardant, the plate member is immersed in the flame retardant, and the plate member is immersed in the plate member. It is characterized in that it is carried out by continuing a state in which a pressure larger than the pressure by is continued for a predetermined time.
- the balsa material that is inexpensive and easy to dispose and recycle is used as the core material, cost reduction, strength, rigidity, flame retardancy, and weight reduction of the panel material for aircraft interior parts are achieved. This is advantageous in reducing the environmental load while satisfying the above requirements.
- the surface area increasing structure portion is provided, the surface area of the plate-like member impregnated with the flame retardant increases, which is advantageous in securing higher flame retardancy. It is possible to reduce the weight of the interior panel material, which is advantageous in further reducing the weight of the aircraft interior.
- a panel material for aircraft interior parts can be formed by simple processing of the structure for increasing the surface area, which is advantageous in reducing the cost of the panel material for aircraft interior parts.
- the balsa material that is inexpensive and easy to dispose and recycle is used as the core material, the cost reduction, strength, rigidity, flame retardancy, and weight reduction of the panel material for aircraft interior parts are achieved. This is advantageous in reducing the environmental load while satisfying the above requirements.
- the surface area increasing structure portion since the surface area of the plate-like member impregnated with the flame retardant is increased, which is advantageous in securing higher flame retardancy, and aircraft.
- the weight of the interior panel material which is advantageous in further reducing the weight of the aircraft interior.
- the adhesion area between the surface material and the plate-like member increases, the adhesion strength between the surface material and the plate-like member is further increased, and the strength of the panel material for aircraft interior parts is ensured. This is advantageous.
- the surface of the plate-like member can be impregnated in a short time, which is advantageous in increasing the production efficiency of the aircraft interior panel material while ensuring high flame retardancy. .
- the aircraft interior panel material 10A widely includes, for example, a panel material constituting an aircraft restroom unit, a panel material constituting a galley, a panel material constituting a luggage compartment, and the like.
- the aircraft interior product panel material 10 ⁇ / b> A includes a core material 12 and a surface material 14 attached to both surfaces of the core material 12.
- the core material 12 is composed of a rectangular plate-like member 12A having a uniform thickness made of a balsa material, and both surfaces in the thickness direction of the plate-like member 12A are formed as flat surfaces.
- the plate-like member 12A is configured by combining a plurality of single plates. That is, the plate-shaped member 12A having a desired size is configured by arranging a plurality of single plates 1202 produced in an elongated shape along the width direction. In addition, a plurality of single plates 1202 are arranged along the width direction, and a plurality of single plates 1202 are stacked in the thickness direction to form a plate-like member 12A having a desired thickness. In this case, the end surfaces of the adjacent single plates 1202 are arbitrarily bonded with an adhesive, or the side surfaces of the stacked single plates 1202 are bonded with an adhesive.
- the balsa material has the characteristics that it is lightweight, has high strength, and is soft and easy to process. Moreover, since the balsa material is a natural material, it is easy to dispose and recycle and is advantageous in reducing the environmental burden.
- the specific gravity of the balsa material used is preferably 0.90 or more and 0.26 or less, and more preferably 0.90 or more and 0.10 or less, from the viewpoint of securing strength while reducing the weight.
- a flame retardant 18 for making the balsa material difficult to burn is impregnated on both surfaces in the thickness direction of the plate-like member 12A.
- the flame retardant 18 various conventionally known flame retardants for wood such as phosphoric acid, boric acid, silicic acid, aluminum, and iron can be used.
- Various methods can be considered for impregnating the flame retardant 18 on both surfaces in the thickness direction of the plate-like member 12A.
- the spraying device 2 may be used to spray the flame retardant 18 on both surfaces of the plate-like member 12 ⁇ / b> A or to apply it.
- the plate member 12 ⁇ / b> A may be immersed in the flame retardant 18 in the container 4.
- the pressure water pressure
- the surface of the plate-like member 12A can be impregnated in a short time, thereby improving the production efficiency while ensuring high flame retardancy. Is advantageous.
- the surface material 14 has the same size and the same size as the plate-like member 12 ⁇ / b> A, and is attached and disposed on both surfaces of the plate-like member 12 ⁇ / b> A in the thickness direction.
- a fiber reinforced composite material is used as the surface material 14.
- a woven fabric such as glass, aramid, carbon, or a sheet-like prepreg material in which a single fiber is impregnated with a phenol resin or an epoxy resin is used.
- each surface material 14 is attached to both surfaces in the thickness direction of the plate-like member 12A by pressing and heating the surface material 14 on both surfaces in the thickness direction of the plate-like member 12A.
- the resin impregnated in the surface material 14 is thermally cured and adhered to both surfaces in the thickness direction of the plate-like member 12A.
- the core material 12 is made of balsa material that is lightweight, strong, soft, and easy to process. Therefore, the aircraft restroom unit, galley, luggage compartment This is extremely advantageous in reducing the weight of aircraft interior parts. Moreover, since the balsa material that is inexpensive and easy to dispose and recycle is used as the core material 12, it is advantageous in reducing the environmental burden while reducing the cost of the aircraft interior parts. Further, since the surface of the plate-like member 12A is impregnated with the flame retardant 18, it is advantageous in obtaining an aircraft interior product in which high flame resistance is ensured.
- an aircraft interior panel material 10B according to a second embodiment will be described with reference to FIGS.
- the same parts and members as those in the first embodiment are denoted by the same reference numerals, and the description thereof is omitted.
- the configuration of the core material 12 is different from that of the first embodiment, and the configuration other than the core material 12 is the same as that of the first embodiment.
- the plate-like member 12A constituting the core material 12 is provided with a plurality of surface area increasing structures 16 that are recessed from the surface of the plate-like member 12A and increase the surface area of the surface.
- the surface area increasing structure 16 is configured by a hole 1602 that penetrates the plate member 12A in the thickness direction.
- the hole 1602 is formed in the plate-like member 12A using, for example, a processing machine such as a drilling machine.
- a processing machine such as a drilling machine.
- both surfaces in the thickness direction of the plate-like member 12A and the inner peripheral surface of the hole 1602 are impregnated with a flame retardant 18 for making the balsa material difficult to burn.
- the impregnation method of the flame retardant 18 into the plate member 12A and the attachment of the surface material 14 to the plate member 12A are the same as in the first embodiment.
- the surface area of the plate member 12A impregnated with the flame retardant 18 is increased. It is advantageous in securing higher flame retardancy, and by providing a plurality of surface area increasing structure portions 16, it is possible to reduce the weight of the aircraft interior panel material 10A. This is advantageous for further planning. Further, since the surface area increasing structure portion 16 (hole 1602) is recessed from the surface of the plate-like member 12A, the surface material 14 made of a sheet-like prepreg material is laminated on both surfaces in the thickness direction of the plate-like member 12A.
- the surface area increasing structure 16 has a depth in the thickness direction of the plate-like member 12A and is constituted by a recess 1604 having a bottom.
- the recess 1604 may be formed only on one surface in the thickness direction of the plate-like member 12A, or may be formed on both surfaces in the thickness direction.
- the concave portion 1604 is formed on the plate-like member 12A using, for example, a processing machine such as a drilling machine.
- Both sides of the plate-like member 12A in the thickness direction, the inner peripheral surface of the recess 1604, and the bottom surface of the recess 1604 are impregnated with a flame retardant 18 for making the balsa material difficult to burn.
- the impregnation method of the flame retardant 18 into the plate member 12A and the attachment of the surface material 14 to the plate member 12A are the same as in the first embodiment.
- the aircraft interior panel material 10C of the third embodiment the same effects as those of the second embodiment are exhibited.
- the surface area increasing structure portion 16 (recessed portion 1604) is recessed from the surface of the plate-like member 12A, the surface material 14 made of a sheet-like prepreg material is laminated on both surfaces in the thickness direction of the plate-like member 12A.
- the resin impregnated in the surface material 14 is melted and the surface and surface area increasing structure portion 16 of the plate-like member 12A are melted.
- Adhering to the (recess 1604) increases the adhesion area. Thereby, it becomes advantageous in raising the adhesive strength of the surface material 14 and the plate-like member 12A, and ensuring the strength of the aircraft interior panel material 10C.
- the fourth embodiment is different from the second and third embodiments in the structure of the surface area increasing structure 16, and the other configurations are the same as those of the second and third embodiments. That is, the surface area increasing structure portion 16 is composed of concave grooves 1610 that are formed to extend on both surfaces in the thickness direction of the plate-like member 12A.
- the concave groove 1610 is formed on the plate-like member 12A using, for example, a processing machine such as a milling machine.
- Both surfaces in the thickness direction of the plate-like member 12A, which is the surface of the plate-like member 12A, and the surfaces of the plurality of concave grooves 1610 are impregnated with a flame retardant 18 for making the balsa material difficult to burn.
- Both surfaces of the plate-like member 12A in the thickness direction and the surface of the groove 1610 are impregnated with a flame retardant 18 for making the balsa material difficult to burn.
- the impregnation method of the flame retardant 18 into the plate member 12A and the attachment of the surface material 14 to the plate member 12A are the same as in the first embodiment.
- a concave groove 1610 formed on one surface in the thickness direction of the plate-like member 12A of each surface material 14 and the other surface are extended.
- the formed recessed grooves 1610 are arranged so as to be shifted in positions so as to be alternately located in a direction orthogonal to the extending direction of the recessed grooves 1610. Therefore, it is advantageous for keeping the thickness of the core material 12 uniform and keeping the strength of the core material 12 uniform.
- the aircraft interior panel material 10D of the fourth exemplary embodiment it is needless to say that the same effect as the second and third exemplary embodiments is achieved, and a plurality of milling machines are used in a short time. Since the concave groove 1610 can be formed in the plate-like member 12A, as compared with the case where a plurality of holes 1602 and concave portions 1204 are provided in the plate-like member 12A using a drilling machine as in the second and third embodiments. Thus, the processing time can be reduced, which is more advantageous in reducing the cost.
- the surface area increasing structure portion 16 (concave groove 1610) is recessed from the surface of the plate member 12A, the surface material 14 made of a sheet-like prepreg material is laminated on both surfaces in the thickness direction of the plate member 12A.
- the resin impregnated in the surface material 14 is melted and the surface and the surface area increasing structure portion of the plate-like member 12A It adheres to 16 (concave groove 1610), and an adhesion area increases. This is advantageous in increasing the adhesive strength between the surface material 14 and the plate-like member 12A and securing the strength of the aircraft interior panel material 10D.
- the surface area increasing structure portion 16 is configured by any one of the hole 1602, the recessed portion 1604, and the recessed groove 1610 has been described. May be composed of one of a hole 1602, a concave portion 1604, a concave groove 1610, or a combination thereof.
- the first experiment and the second experiment were performed as follows.
- a combustion test was performed for the case where the plate member 12A was immersed in a flame retardant solution and the surface of the plate member 12A was impregnated with the flame retardant without applying a pressure load to the plate member 12A.
- a combustion test was performed in the case where the plate member 12A was immersed in a flame retardant solution and the surface of the plate member 12A was impregnated with the flame retardant by applying a large water pressure to the solution. .
- a flame retardant is applied to the surface of the plate member 12A by immersing a plate member 12A having a specific gravity of about 0.1 having a rectangular plate shape of 31 ⁇ 8 cm and a thickness of 1 cm in a boric acid flame retardant solution of various concentrations for 24 hours.
- a boric acid flame retardant solution of various concentrations for 24 hours.
- the specific gravity of the core material 12 was 0.11 to 0.16.
- Specific contents of the combustion test will be described. Specific gravity of the plate-like member 12A before treatment: 0.098 Product name of the plate member 12A: BALTEK (registered trademark) SB (SB.50) Manufacturer name of plate member 12A: 3A Composites Product name of flame retardant 18: Fireless B (registered trademark) Manufacturer of flame retardant 18: Trust Life Co., Ltd. Treatment method of core material 12 after immersion in various concentrations of flame retardant 18: Dry at room temperature
- the combustion test samples of Experimental Examples 1 to 3 were prepared by changing the concentration of the flame retardant 18.
- the combustion test sample is obtained by using the core material 12 impregnated with the flame retardant 18 and bonding the following surface material 14 to both surfaces of the core material 12.
- Surface Material 14 Glass / Phenol Prepreg As shown in FIG. 12, Examples 1, 2, and 3 passed the F1 test.
- the produced aircraft interior panel material 10A is as follows.
- a plate member 12A having a rectangular plate shape of 31 ⁇ 8 cm and a thickness of 1 cm and having a specific gravity of about 0.1 is immersed in a boric acid flame retardant solution having a concentration of 10 wt% under the following immersion conditions. The surface of this was impregnated with a flame retardant. As a result, the specific gravity of the core material 12 was about 0.11.
- the combustion test samples of Experimental Examples 4 to 6 were prepared by changing the immersion conditions.
- the combustion test sample was obtained by using the core material 12 impregnated with the flame retardant 18 and having the glass / phenol prepreg surface material 14 bonded to both surfaces of the core material 12. It is.
- Experimental Example 4 As shown in FIG. 5, a cycle in which a water pressure of 50 kPa was applied for 5 minutes with the plate-like member 12A immersed in the flame retardant 18 in the container 6 and then left for 1 minute except for the load of the water pressure was 4 Repeated for hours.
- Experimental Example 5 With the plate member 12A immersed in the flame retardant 18 in the container 6, a water pressure (static pressure) of 50 kPa was applied and left for 4 hours.
- Experimental Example 6 With the plate-like member 12A immersed in the flame retardant 18 in the container 6, water pressure (static pressure) of 100 kPa was applied and left for 2 hours. As shown in FIG. 13, Experimental Examples 4, 5, and 6 passed the F1 test.
- the surface of the plate member 12A is impregnated with the flame retardant 18 in a short time of about 2 to 4 hours by applying a large water pressure to the solution while the plate member 12A is immersed in the solution of the flame retardant 18. It has become clear that it is advantageous in increasing the production efficiency while ensuring the flame retardancy of the aircraft interior panel material 10A.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Wood Science & Technology (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
Description
航空機内装品用パネル材、例えば床パネル、壁パネル、天井パネルには強度、剛性が要求されることは無論のこと、さらに難燃性や軽量化が求められている。
そして、このようなパネル材は、アラミド繊維、ガラス繊維、アルミニウムなどからなるハニカム構造のコア材の両面に、繊維強化複合材料からなる表面材を貼着することで構成されている(特許文献1参照)。
本発明は前記事情に鑑み案出されたものであり、その目的は、コスト低減化、強度、剛性、難燃性、軽量化の要求を満たしつつ環境負荷を低減する上で有利な航空機内装品用パネル材およびその製造方法を提供することにある。
請求項2記載の発明は、前記板状部材の表面には、前記表面から窪んで前記表面の表面積を増加させる複数の表面積増加用構造部が設けられていることを特徴とする。
請求項3記載の発明は、前記表面積増加用構造部は、前記板状部材にその厚さ方向に貫通された孔、前記板状部材の厚さ方向の深さを有し底部を有する凹部、前記板状部材の厚さ方向の両面にそれぞれ延在形成された凹溝のうちの一つまたはそれらの組み合わせで構成されていることを特徴とする。
請求項4記載の発明は、コア材の両面に繊維強化複合材料からなる表面材が取着された航空機内装品用パネル材の製造方法であって、前記コア材として、その表面に難燃剤を含浸させたバルサ材からなる板状部材を用いるようにしたことを特徴とする。
請求項5記載の発明は、前記板状部材の表面に前記難燃剤を含浸させる前に、前記板状部材の表面に、前記表面から窪んで前記表面の表面積を増加させる複数の表面積増加用構造部を設けるようにしたことを特徴とする。
請求項6記載の発明は、前記コア材の両面への前記表面材の取着は、前記コア材の両面へ前記表面材を積層した状態で加圧および加熱し、前記表面材に含浸されている樹脂を溶融して前記板状部材の表面および前記表面積増加用構造部に付着させることにより行なうようにしたことを特徴とする。
請求項7記載の発明は、前記板状部材の表面への前記難燃剤の含浸を、前記板状部材を前記難燃剤に浸漬させ、前記板状部材に前記板状部材が浸漬された深さによる圧力よりも大きな圧力を掛けた状態を所定の時間継続させることで行なうことを特徴とする。
請求項2記載の発明によれば、表面積増加用構造部を設けたので、難燃剤が含浸する板状部材の表面積が増加し、より高い難燃性を確保する上で有利となり、また、航空機内装品用パネル材の軽量化を図れ、したがって、航空機内装品の軽量化をより一層図る上で有利となる。
請求項3記載の発明によれば、表面積増加用構造部を簡単な加工により航空機内装品用パネル材を形成でき、航空機内装品用パネル材のコスト低減化を図る上で有利となる。
請求項4記載の発明によれば、コア材として安価で処分やリサイクル処理が容易なバルサ材を用いたので、航空機内装品用パネル材のコスト低減化、強度、剛性、難燃性、軽量化の要求を満たしつつ環境負荷を低減する上で有利となる。
請求項5記載の発明によれば、表面積増加用構造部を設けたので、難燃剤が含浸する板状部材の表面積が増加し、より高い難燃性を確保する上で有利となり、また、航空機内装品用パネル材の軽量化を図れ、したがって、航空機内装品の軽量化をより一層図る上で有利となる。
請求項6記載の発明によれば、表面材と板状部材との接着面積が増加するため、表面材と板状部材との接着強度をより高め、航空機内装品用パネル材の強度を確保する上で有利となる。
請求項7記載の発明によれば、短時間で板状部材の表面に含浸させることが可能となり、高い難燃性を確保しつつ航空機内装品用パネル材の生産効率を高める上で有利となる。
次に、第1の実施の形態の航空機内装品用パネル材10Aについて図1~図5を参照して説明する。
ここで、航空機内装品用パネル材とは、例えば、航空機用化粧室ユニットを構成するパネル材や、ギャレーを構成するパネル材や、荷物入れを構成するパネル材などを広く含む。
図1に示すように、航空機内装品用パネル材10Aは、コア材12と、コア材12の両面に取着された表面材14とを含んで構成されている。
コア材12は、バルサ材からなる均一の厚さの矩形の板状部材12Aで構成され、板状部材12Aの厚さ方向の両面は平坦面で形成されている。
なお、1本の原木から製材し得る単板の大きさには限りがあるため、板状部材12Aは、複数の単板を組み合わせて構成されている。
すなわち、細長形状に製材された複数の単板1202を幅方向に沿って並べることで、所望の大きさの板状部材12Aが構成されている。
また、複数の単板1202を幅方向に沿って並べると共に、複数の単板1202を厚さ方向に積層することで所望の厚さの板状部材12Aを構成するなど任意である。この場合、隣り合う単板1202の端面同士を接着剤で接着し、あるいは、積層された単板1202の側面同士を接着剤で接着するなど任意である。
バルサ材は、軽量で強度が大きく、軟らかいため加工が容易であるという特徴を有している。しかも、バルサ材は、天然材料であることから、処分やリサイクル処理が容易で環境負荷の軽減を図る上で有利である。
用いるバルサ材は、軽量化を図りつつ強度を確保する観点から、比重が0.90以上0.26以下が好ましく、0.90以上0.10以下がより好ましい。
また、バルサ材は、板木目に対する垂直面(木口面)を、表面材14が配置されるコア材12の表面として使用することが、強度を向上させる上で好ましい。
難燃剤18としては、リン酸系、ホウ酸系、ケイ酸系、アルミニウム系、鉄系などの従来公知の様々な木材用の難燃剤が使用可能である。
板状部材12Aの厚さ方向の両面への難燃剤18の含浸は、種々の方法が考えられる。
例えば、図3に示すように、噴霧器2を用いて板状部材12Aの両面に難燃剤18を噴霧することで、あるいは、塗布することで行なうようにしてもよい。
あるいは、図4に示すように、容器4内の難燃剤18に板状部材12Aを浸漬することで行なうようにしてもよい。
あるいは、図5に示すように、容器6内の難燃剤18に板状部材12Aを浸漬した状態で、板状部材12Aに板状部材12Aが浸漬された深さによる圧力(水圧)よりも大きな静圧もしくは板状部材12Aに浸漬された深さによる圧力(水圧)よりも大きな静圧サイクルを掛けることで行なうようにしてもよい。板状部材12Aに浸漬された深さによる圧力よりも大きな圧力を掛けると、短時間で板状部材12Aの表面に含浸させることが可能となり、高い難燃性を確保しつつ生産効率を高める上で有利となる。
表面材14として繊維強化複合材料が用いられる。このような繊維強化複合材料としては、ガラス、アラミド、カーボンなどの織物や単繊維にフェノール樹脂やエポキシ樹脂を含浸させたシート状のプリプレグ材が用いられる。
また、各表面材14の板状部材12Aの厚さ方向の両面への取着は、板状部材12Aの厚さ方向の両面に表面材14を積層した状態で、加圧および加熱することにより、表面材14に含浸されている樹脂が熱硬化して板状部材12Aの厚さ方向の両面に接着することでなされる。
また、コア材12として安価で処分やリサイクル処理が容易なバルサ材を用いたので、航空機内装品のコスト低減を図りつつ環境負荷を低減する上で有利となる。
また、板状部材12Aの表面に難燃剤18を含浸させたので、高い難燃性が確保された航空機内装品を得る上で有利となる。
次に、第2の実施の形態の航空機内装品用パネル材10Bについて図6、図7を参照して説明する。
なお、以下の実施の形態において、第1の実施の形態と同様の部分、部材については同一の符号を付してその説明を省略する。
なお、以下の実施の形態では、コア材12の構成が第1の実施の形態と異なり、コア材12以外の他の構成は第1の実施の形態と同様である。
第2の実施の形態では、コア材12を構成する板状部材12Aに、板状部材12Aの表面から窪んでその表面の表面積を増加させる複数の表面積増加用構造部16が設けられている。
本実施の形態では、表面積増加用構造部16は、板状部材12Aにその厚さ方向に貫通された孔1602で構成されている。
板状部材12Aに対する孔1602の形成は、例えば、ボール盤などの加工機械を用いてなされる。
そして、図7(A)に示すように、板状部材12Aの厚さ方向の両面と孔1602の内周面とに、バルサ材を燃えにくくするための難燃剤18が含浸されている。
板状部材12Aへの難燃剤18の含浸方法および表面材14の板状部材12Aへの取着は第1の実施の形態と同様である。
第2の実施の形態の航空機内装品用パネル材10Bによれば、第1の実施の形態と同様な効果が奏される他、難燃剤18が含浸する板状部材12Aの表面積が増加し、より高い難燃性を確保する上で有利となり、また、複数の表面積増加用構造部16を設けることで航空機内装品用パネル材10Aの軽量化を図れ、したがって、航空機内装品の軽量化をより一層図る上で有利となる。
また、表面積増加用構造部16(孔1602)が板状部材12Aの表面から窪んでいるため、板状部材12Aの厚さ方向の両面にシート状のプリプレグ材からなる表面材14を積層した状態で、加圧および加熱することにより板状部材12Aの厚さ方向の両面に接着する場合、表面材14に含浸されている樹脂が溶融して板状部材12Aの表面および表面積増加用構造部16(孔1602)に付着し接着面積が増加する。この表面材14に含浸されている樹脂が溶融して表面積増加用構造部16(孔1602)に付着した状態を、図7(B)にハッチングおよび符号17で示す。これにより、表面材14と板状部材12Aとの接着強度をより高め、航空機内装品用パネル材10Bの強度を確保する上で有利となる。
次に、第3の実施の形態の航空機内装品用パネル材10Cについて図8、図9を参照して説明する。
第3の実施の形態は、第2の実施の形態と表面積増加用構造部16の構造が異なっており、他の構成は第2の実施の形態と同様である。
すなわち、表面積増加用構造部16は、板状部材12Aの厚さ方向の深さを有し、底部を有する凹部1604で構成されている。
この凹部1604は、板状部材12Aの厚さ方向の一方の面のみに形成されていてもよく、厚さ方向の両面に形成されていてもよい。
板状部材12Aに対する凹部1604の形成は、例えば、ボール盤などの加工機械を用いてなされる。
板状部材12Aの厚さ方向の両面と凹部1604の内周面と凹部1604の底面とに、バルサ材を燃えにくくするための難燃剤18が含浸されている。
板状部材12Aへの難燃剤18の含浸方法および表面材14の板状部材12Aへの取着は第1の実施の形態と同様である。
第3の実施の形態の航空機内装品用パネル材10Cによれば、第2の実施の形態と同様な効果が奏される。
また、表面積増加用構造部16(凹部1604)が板状部材12Aの表面から窪んでいるため、板状部材12Aの厚さ方向の両面にシート状のプリプレグ材からなる表面材14を積層した状態で、加圧および加熱することにより板状部材12Aの厚さ方向の両面に接着する場合、表面材14に含浸されている樹脂が溶融して板状部材12Aの表面および表面積増加用構造部16(凹部1604)に付着し接着面積が増加する。これにより、表面材14と板状部材12Aとの接着強度をより高め、航空機内装品用パネル材10Cの強度を確保する上で有利となる。
次に、第4の実施の形態の航空機内装品用パネル材10Dについて図10、図11を参照して説明する。
第4の実施の形態は、第2、第3の実施の形態と表面積増加用構造部16の構造が異なっており、他の構成は第2、第3の実施の形態と同様である。
すなわち、表面積増加用構造部16は、板状部材12Aの厚さ方向の両面にそれぞれ延在形成された凹溝1610で構成されている。
板状部材12Aに対する凹溝1610の形成は、例えば、フライス盤などの加工機械を用いてなされる。
板状部材12Aの表面である板状部材12Aの厚さ方向の両面と、複数の凹溝1610の表面とには、バルサ材を燃えにくくするための難燃剤18が含浸されている。
板状部材12Aの厚さ方向の両面と凹溝1610の表面とに、バルサ材を燃えにくくするための難燃剤18が含浸されている。
板状部材12Aへの難燃剤18の含浸方法および表面材14の板状部材12Aへの取着は第1の実施の形態と同様である。
また、表面積増加用構造部16(凹溝1610)が板状部材12Aの表面から窪んでいるため、板状部材12Aの厚さ方向の両面にシート状のプリプレグ材からなる表面材14を積層した状態で、加圧および加熱することにより板状部材12Aの厚さ方向の両面に接着する場合、表面材14に含浸されている樹脂が溶融して板状部材12Aの表面および表面積増加用構造部16(凹溝1610)に付着し接着面積が増加する。これにより、表面材14と板状部材12Aとの接着強度をより高め、航空機内装品用パネル材10Dの強度を確保する上で有利となる。
以下のように第1の実験と第2の実験とを行った。
第1の実験では、板状部材12Aを難燃剤の溶液に浸漬させ板状部材12Aに圧力負荷をかけない状態で板状部材12Aの表面に難燃剤を含浸させた場合について燃焼試験を行った。
また、第2の実験では、板状部材12Aを難燃剤の溶液に浸漬させた状態で溶液に大きな水圧を掛けて板状部材12Aの表面に難燃剤を含浸させた場合について燃焼試験を行った。
第1の実験では、第1の実施の形態で示す航空機内装品用パネル材10Aについて、以下に示すような試料を作製し、連邦航空規則であるFAR 25.853 Appendix F Part I (a)(1)(i) に規定されている燃焼試験60秒垂直燃焼試験(以下F1試験という)を行った。その結果、航空機内装品用パネル材10Aは難燃性要求を満たした。
F1試験において自己消火時間が15秒以下、燃焼長さが6インチ以下、ドリップ消火時間が3秒以下を合格とした。
作製した航空機内装品用パネル材10Aは以下の通りである。
31×8cmで厚さ1cmの矩形板状を呈する比重約0.1の板状部材12Aを各種濃度のホウ酸系難燃剤の溶液に24時間浸漬させることで板状部材12Aの表面に難燃剤を含浸させた。その結果、コア材12の比重は0.11~0.16となった。
処理前の板状部材12Aの比重:0.098
板状部材12Aの商品名:BALTEK(登録商標) SB(SB.50)
板状部材12Aのメーカー名:3A Composites
難燃剤18の商品名:ファイアレスB(登録商標)
難燃剤18のメーカー名:株式会社トラストライフ
難燃剤18の各種濃度の溶液に浸漬後のコア材12の処理方法:室温で乾燥
なお、燃焼試験サンプルは、上記の難燃剤18を含浸させた上記のコア材12を用い、コア材12の両面に以下の表面材14を接着したものである。
表面材14:ガラス/フェノールプリプレグ
図12に示すように、実施例1、2、3はF1試験に合格した。
第2の実験では、第1の実施の形態で示す航空機内装品用パネル材10Aについて、以下に示すような浸漬条件で試料を作製し、第1の実験と同様にF1試験を行った。その結果、航空機内装品用パネル材10Aは難燃性要求を満たした。
作製した航空機内装品用パネル材10Aは以下の通りである。
31×8cmで厚さ1cmの矩形板状を呈する比重約0.1の板状部材12Aを10wt%の濃度のホウ酸系難燃剤の溶液に以下の浸漬条件で浸漬させることで板状部材12Aの表面に難燃剤を含浸させた。その結果、コア材12の比重は約0.11となった。
上記燃焼試験の具体的な内容については、第1の実験の場合と同様である。
上記燃焼試験に際しては、図13に示すように、浸漬条件を変化させて実験例4~6の燃焼試験サンプルを作製した。
なお、燃焼試験サンプルは、第1の実験と同様に、上記の難燃剤18を含浸させた上記のコア材12を用い、コア材12の両面にガラス/フェノールプリプレグの表面材14を接着したものである。
実験例4:図5に示すように、容器6内の難燃剤18に板状部材12Aを浸漬した状態で50kPaの水圧を5分間掛け、次いで水圧の負荷を除いて1分間放置するサイクルを4時間繰り返した。
実験例5:容器6内の難燃剤18に板状部材12Aを浸漬した状態で50kPaの水圧(静圧)を掛けて4時間放置した。
実験例6:容器6内の難燃剤18に板状部材12Aを浸漬した状態で100kPaの水圧(静圧)を掛けて2時間放置した。
図13に示すように、実験例4、5、6はF1試験に合格した。
したがって、板状部材12Aを難燃剤18の溶液に浸漬させた状態で溶液に大きな水圧を掛けることにより、2~4時間程度の短時間で難燃剤18を板状部材12Aの表面に含浸させることができ、航空機内装品用パネル材10Aの難燃性を確保しつつ生産効率を高める上で有利となることが明らかとなった。
12 コア材
12A 板状部材
14 表面材
16 表面積増加用構造部
1602 孔
1604 凹部
1610 凹溝
18 難燃剤
Claims (7)
- コア材の両面に繊維強化複合材料からなる表面材が取着された航空機内装品用パネル材であって、
前記コア材は、バルサ材からなる板状部材で構成され、
前記板状部材の表面に難燃剤が含浸されている、
ことを特徴とする航空機内装品用パネル材。 - 前記板状部材の表面には、前記表面から窪んで前記表面の表面積を増加させる複数の表面積増加用構造部が設けられている、
ことを特徴とする請求項1記載の航空機内装品用パネル材。 - 前記表面積増加用構造部は、前記板状部材にその厚さ方向に貫通された孔、前記板状部材の厚さ方向の深さを有し底部を有する凹部、前記板状部材の厚さ方向の両面にそれぞれ延在形成された凹溝のうちの一つまたはそれらの組み合わせで構成されている、
ことを特徴とする請求項2記載の航空機内装品用パネル材。 - コア材の両面に繊維強化複合材料からなる表面材が取着された航空機内装品用パネル材の製造方法であって、
前記コア材として、その表面に難燃剤を含浸させたバルサ材からなる板状部材を用いるようにした、
ことを特徴とする航空機内装品用パネル材の製造方法。 - 前記板状部材の表面に前記難燃剤を含浸させる前に、前記板状部材の表面に、前記表面から窪んで前記表面の表面積を増加させる複数の表面積増加用構造部を設けるようにした、
ことを特徴とする請求項4記載の航空機内装品用パネル材の製造方法。 - 前記コア材の両面への前記表面材の取着は、前記コア材の両面へ前記表面材を積層した状態で加圧および加熱し、前記表面材に含浸されている樹脂を溶融して前記板状部材の表面および前記表面積増加用構造部に付着させることにより行なうようにした、
ことを特徴とする請求項5記載の航空機内装品用パネル材の製造方法。 - 前記板状部材の表面への前記難燃剤の含浸を、前記板状部材を前記難燃剤に浸漬させ、前記板状部材に前記板状部材が浸漬された深さによる圧力よりも大きな圧力を掛けた状態を所定の時間継続させることで行なう、
ことを特徴とする請求項4~6の何れか1項記載の航空機内装品用パネル材の製造方法。
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14850209.9A EP3053829A4 (en) | 2013-10-03 | 2014-10-03 | Aircraft interior panel material and manufacturing method therefor |
US15/026,933 US20160264229A1 (en) | 2013-10-03 | 2014-10-03 | Aircraft Interior Panel Material and Manufacturing Method Therefor |
JP2015540565A JPWO2015050239A1 (ja) | 2013-10-03 | 2014-10-03 | 航空機内装品用パネル材およびその製造方法 |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2013207834 | 2013-10-03 | ||
JP2013-207834 | 2013-10-03 | ||
JP2014078369 | 2014-04-07 | ||
JP2014-078369 | 2014-04-07 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015050239A1 true WO2015050239A1 (ja) | 2015-04-09 |
Family
ID=52778822
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2014/076508 WO2015050239A1 (ja) | 2013-10-03 | 2014-10-03 | 航空機内装品用パネル材およびその製造方法 |
Country Status (4)
Country | Link |
---|---|
US (1) | US20160264229A1 (ja) |
EP (1) | EP3053829A4 (ja) |
JP (1) | JPWO2015050239A1 (ja) |
WO (1) | WO2015050239A1 (ja) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107718265A (zh) * | 2016-08-11 | 2018-02-23 | 南通奥王节能建筑材料科技发展有限公司 | 一种吸音一体板及其制备方法 |
US11426983B2 (en) * | 2019-04-19 | 2022-08-30 | Goodrich Corporation | Carbon fiber decorative veneer |
US20210024196A1 (en) * | 2019-07-25 | 2021-01-28 | Gulfstream Aerospace Corporation | Aircraft, interior panels for aircfraft, and methods for making interior panels |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4741971A (en) * | 1986-05-23 | 1988-05-03 | The Dow Chemical Company | Method for imparting flame resistance to wood surfaces |
JPH05309792A (ja) * | 1992-05-14 | 1993-11-22 | Hamaguchi Keiki Kogyo Kk | Frp複合板およびその製造方法 |
JP2000238154A (ja) | 1999-02-19 | 2000-09-05 | Toray Ind Inc | ハニカムサンドイッチパネル |
JP2003146252A (ja) * | 2001-11-14 | 2003-05-21 | Toray Ind Inc | Frp製自動車用パネルおよびその製造方法 |
JP2003211412A (ja) * | 2001-11-16 | 2003-07-29 | Asano Mokuzai Kogyo Kk | 不燃木材の製造方法 |
JP2006002869A (ja) * | 2004-06-18 | 2006-01-05 | Toho Tenax Co Ltd | サンドイッチパネル |
JP2006175606A (ja) * | 2004-12-20 | 2006-07-06 | Toyota Motor Corp | Frp用インサート |
EP1930138A1 (de) * | 2006-12-10 | 2008-06-11 | Moralt Tischlerplatten GmbH & Co. KG | Leichtbauplatte sowie Herstellungsverfahren |
JP2010095943A (ja) * | 2008-10-17 | 2010-04-30 | Ihi Corp | サンドイッチパネル |
JP2012126387A (ja) * | 2010-12-13 | 2012-07-05 | Boeing Co:The | 改善されたグリーンな航空機内部パネル |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4428993A (en) * | 1982-05-11 | 1984-01-31 | Baltek Corporation | Structural laminate with expanded wood core |
BR112014013616A2 (pt) * | 2011-12-05 | 2018-09-04 | Airbus Sas | método de fabricação de um artefato e artefato à prova de chama |
EP2894136B1 (en) * | 2014-01-08 | 2019-12-04 | The Boeing Company | Improved method of making fire resistant sustainable aircraft interior panels |
EP2894029B1 (en) * | 2014-01-08 | 2017-04-12 | The Boeing Company | Fire resistant sustainable aircraft interior panel |
-
2014
- 2014-10-03 EP EP14850209.9A patent/EP3053829A4/en not_active Withdrawn
- 2014-10-03 US US15/026,933 patent/US20160264229A1/en not_active Abandoned
- 2014-10-03 WO PCT/JP2014/076508 patent/WO2015050239A1/ja active Application Filing
- 2014-10-03 JP JP2015540565A patent/JPWO2015050239A1/ja active Pending
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4741971A (en) * | 1986-05-23 | 1988-05-03 | The Dow Chemical Company | Method for imparting flame resistance to wood surfaces |
JPH05309792A (ja) * | 1992-05-14 | 1993-11-22 | Hamaguchi Keiki Kogyo Kk | Frp複合板およびその製造方法 |
JP2000238154A (ja) | 1999-02-19 | 2000-09-05 | Toray Ind Inc | ハニカムサンドイッチパネル |
JP2003146252A (ja) * | 2001-11-14 | 2003-05-21 | Toray Ind Inc | Frp製自動車用パネルおよびその製造方法 |
JP2003211412A (ja) * | 2001-11-16 | 2003-07-29 | Asano Mokuzai Kogyo Kk | 不燃木材の製造方法 |
JP2006002869A (ja) * | 2004-06-18 | 2006-01-05 | Toho Tenax Co Ltd | サンドイッチパネル |
JP2006175606A (ja) * | 2004-12-20 | 2006-07-06 | Toyota Motor Corp | Frp用インサート |
EP1930138A1 (de) * | 2006-12-10 | 2008-06-11 | Moralt Tischlerplatten GmbH & Co. KG | Leichtbauplatte sowie Herstellungsverfahren |
JP2010095943A (ja) * | 2008-10-17 | 2010-04-30 | Ihi Corp | サンドイッチパネル |
JP2012126387A (ja) * | 2010-12-13 | 2012-07-05 | Boeing Co:The | 改善されたグリーンな航空機内部パネル |
Non-Patent Citations (1)
Title |
---|
See also references of EP3053829A4 |
Also Published As
Publication number | Publication date |
---|---|
JPWO2015050239A1 (ja) | 2017-03-09 |
US20160264229A1 (en) | 2016-09-15 |
EP3053829A4 (en) | 2017-06-07 |
EP3053829A1 (en) | 2016-08-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CA2759976A1 (en) | Improved, green aircraft interior panels | |
EP2674091A1 (en) | Honeycomb-based high temperature structural damper | |
JP2009508709A5 (ja) | ||
WO2015050239A1 (ja) | 航空機内装品用パネル材およびその製造方法 | |
JP2008137204A (ja) | サンドイッチパネル | |
JP2008137203A (ja) | サンドイッチパネル | |
US20140302736A1 (en) | Flame-Proofed Artefact and a Method of Manufacture Thereof | |
JP2016028838A (ja) | 炭素繊維複合材の孔あけ加工方法 | |
JP2017100326A (ja) | 化粧パネル | |
GB2450359A (en) | Multi-Core Structural Insulated Panels | |
EP3126133A1 (en) | Systems and methods of producing a structural and non-structural homogeneous and hybrid composite panels, prepregs, hand layup panels with "basalt" fiber, various composite materials, and additives | |
US10794058B2 (en) | Structural panel | |
JP2017105158A (ja) | 化粧パネル及びパネル製造方法 | |
JP2014012467A (ja) | 航空機用部材 | |
JP2010106553A (ja) | 木製防火ドアー | |
US9567754B2 (en) | Flooring assembly with heat dissipation layer | |
KR20160130620A (ko) | 스티로폼 및 에프알피 복합판넬 | |
KR101366785B1 (ko) | 불연성 섬유 강화 플라스틱을 이용한 천장판 및 그 제조방법 | |
US11739523B2 (en) | Multi-layered reinforced wood material | |
JPH01306236A (ja) | 自己支持構造物用素子 | |
JP2019188823A (ja) | 化粧パネル | |
KR20000018198A (ko) | 페놀 폼 샌드위치 판넬의 제조 방법 | |
JP6847510B2 (ja) | 炭素繊維複合化粧板 | |
WO2017164199A1 (ja) | 表面化粧パネル及びこれを備えた化粧パネル | |
US20170157883A1 (en) | Composite stiffener |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 14850209 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 2015540565 Country of ref document: JP Kind code of ref document: A |
|
WWE | Wipo information: entry into national phase |
Ref document number: 15026933 Country of ref document: US |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
REEP | Request for entry into the european phase |
Ref document number: 2014850209 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2014850209 Country of ref document: EP |