WO2007048426A1 - Titanium barrier - Google Patents
Titanium barrier Download PDFInfo
- Publication number
- WO2007048426A1 WO2007048426A1 PCT/EP2005/011481 EP2005011481W WO2007048426A1 WO 2007048426 A1 WO2007048426 A1 WO 2007048426A1 EP 2005011481 W EP2005011481 W EP 2005011481W WO 2007048426 A1 WO2007048426 A1 WO 2007048426A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- composite material
- titanium foil
- material according
- titanium
- fibre reinforced
- Prior art date
Links
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 title claims abstract description 71
- 239000010936 titanium Substances 0.000 title claims description 13
- 229910052719 titanium Inorganic materials 0.000 title claims description 13
- 230000004888 barrier function Effects 0.000 title claims description 11
- 239000002131 composite material Substances 0.000 claims abstract description 90
- 239000000835 fiber Substances 0.000 claims abstract description 26
- 239000000463 material Substances 0.000 claims abstract description 23
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 6
- 238000004519 manufacturing process Methods 0.000 claims abstract description 6
- 239000003973 paint Substances 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 11
- 229920005989 resin Polymers 0.000 claims description 7
- 239000011347 resin Substances 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 239000000126 substance Substances 0.000 claims description 6
- 239000003822 epoxy resin Substances 0.000 claims description 5
- 150000002894 organic compounds Chemical class 0.000 claims description 5
- 229920006122 polyamide resin Polymers 0.000 claims description 5
- 229920000647 polyepoxide Polymers 0.000 claims description 5
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- OGIDPMRJRNCKJF-UHFFFAOYSA-N titanium oxide Inorganic materials [Ti]=O OGIDPMRJRNCKJF-UHFFFAOYSA-N 0.000 claims description 4
- 241000531908 Aramides Species 0.000 claims description 3
- 229920003235 aromatic polyamide Polymers 0.000 claims description 3
- SOQBVABWOPYFQZ-UHFFFAOYSA-N oxygen(2-);titanium(4+) Chemical class [O-2].[O-2].[Ti+4] SOQBVABWOPYFQZ-UHFFFAOYSA-N 0.000 claims description 3
- 229910044991 metal oxide Inorganic materials 0.000 claims description 2
- 150000004706 metal oxides Chemical class 0.000 claims description 2
- 229920001568 phenolic resin Polymers 0.000 claims description 2
- 238000007788 roughening Methods 0.000 claims description 2
- 238000005488 sandblasting Methods 0.000 claims description 2
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims 1
- 239000005007 epoxy-phenolic resin Substances 0.000 claims 1
- 239000011521 glass Substances 0.000 claims 1
- 239000010410 layer Substances 0.000 description 45
- 239000011888 foil Substances 0.000 description 6
- 238000002360 preparation method Methods 0.000 description 6
- 229920001169 thermoplastic Polymers 0.000 description 5
- 239000004416 thermosoftening plastic Substances 0.000 description 5
- 239000000853 adhesive Substances 0.000 description 4
- 230000001070 adhesive effect Effects 0.000 description 4
- 239000010408 film Substances 0.000 description 4
- 239000003365 glass fiber Substances 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 239000004593 Epoxy Substances 0.000 description 2
- 239000004952 Polyamide Substances 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 2
- 239000005030 aluminium foil Substances 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 230000006866 deterioration Effects 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 238000010422 painting Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 239000004698 Polyethylene Substances 0.000 description 1
- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 description 1
- 239000002313 adhesive film Substances 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000012993 chemical processing Methods 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000005530 etching Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 description 1
- 239000000049 pigment Substances 0.000 description 1
- 229920002647 polyamide Polymers 0.000 description 1
- 229920000728 polyester Polymers 0.000 description 1
- 229920001225 polyester resin Polymers 0.000 description 1
- -1 polyethylene Polymers 0.000 description 1
- 229920000573 polyethylene Polymers 0.000 description 1
- 229920005990 polystyrene resin Polymers 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 229920002994 synthetic fiber Polymers 0.000 description 1
- 239000010409 thin film Substances 0.000 description 1
- 239000002759 woven fabric Substances 0.000 description 1
Classifications
-
- 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
- B32B3/10—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 discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—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 discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
-
- 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
- B32B3/28—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 a layer comprising a deformed thin sheet, i.e. the layer having its entire thickness deformed out of the plane, e.g. corrugated, crumpled
-
- 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
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
-
- 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
- B32B15/00—Layered products comprising a layer of metal
- B32B15/14—Layered products comprising a layer of metal 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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/02—Synthetic macromolecular fibres
- B32B2262/0261—Polyamide fibres
- B32B2262/0269—Aromatic polyamide fibres
-
- 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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/101—Glass fibres
-
- 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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
-
- 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
- B32B2305/00—Condition, form or state of the layers or laminate
- B32B2305/08—Reinforcements
-
- 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
- B32B2311/00—Metals, their alloys or their compounds
- B32B2311/18—Titanium
-
- 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
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B5/00—Hulls characterised by their construction of non-metallic material
- B63B5/24—Hulls characterised by their construction of non-metallic material made predominantly of plastics
- B63B2005/242—Hulls characterised by their construction of non-metallic material made predominantly of plastics made of a composite of plastics and other structural materials, e.g. wood or metal
- B63B2005/245—Hulls characterised by their construction of non-metallic material made predominantly of plastics made of a composite of plastics and other structural materials, e.g. wood or metal made of a composite of plastics and metal
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B2231/00—Material used for some parts or elements, or for particular purposes
- B63B2231/02—Metallic materials
- B63B2231/18—Titanium or titanium alloys
Definitions
- the invention relates to a composite material comprising a laminate structure containing at least one fibre reinforced synthetic layer, which is in particular used as a structural material for aircraft and boats. Furthermore, the invention relates to a method of producing such a composite material.
- composite materials containing fibre reinforced synthetic layers require a number of properties to be met by this material. Firstly, the laminate structures have to be protected from water, atmospheric moisture and chemical ingression. Secondly, these structures have to be protected from mechanical damage and from deterioration by ultra-violet light. To meet these requirements, the composite materials in question are commonly coated with an adhesive film or an especially formulated resin to protect its surface. However, to provide a moisture sealing of the composite material being suitable to withstand the combination of mechanical attacks and sharp temperature differences, it has been found in practice that such coatings do not provide satisfactory- results .
- thermoplastic films are difficult to bond permanently to the composite and are easily damaged by mechanical attacks. Furthermore, these thermoplastic films do not present a vapor barrier having sufficient sealing properties. Moreover, in particular when used as a structural component for aircraft, thermoplastics do not offer a protection against lightning strikes. Finally, these thermoplastic films are relatively heavy.
- aluminium foils present a sufficient water and vapor barrier and are easy to bond to the composite, they are easy to damage and, most particularly, corrosive with Carbon. Furthermore, there is a mismatch between the thermal coefficient of expansion and the modulus of elasticity between the aluminium and the composite material.
- composites are made from epoxy or other resin which degrade through ultra-violet light exposure when not protected with ultra-violet resistant paint.
- these composite materials are quite difficult to paint. In general, these composite materials are black, which is difficult to cover.
- any surface preparation for painting is difficult without damaging the composite structure. Paint does not adhere well to some composite surfaces when exposed to rain erosion and other attacks. Finally, it is often necessary to strip the paint from the composite materials, even when used as structural material for aircraft, and both chemical and mechanical removal techniques run the risk of damage to the structure .
- an object of the invention to provide a composite structure, which does not present the drawbacks known from the prior art. It is another object of the invention to provide a material being suitable for use in aircraft, boats and other structure, which is light and strong, offers long durability even when exposed to variable and extreme climatic conditions. It is yet another object of the invention to provide a composite material having a moisture barrier property against atmospheric humidity and water, and which offers a shielding capacity against lightning strikes.
- a composite material comprising a laminate structure containing at least one fibre reinforced synthetic layer and a titanium foil constituting an outermost layer of the composite material.
- this titanium foil has a thickness of 100 ⁇ m or less.
- the metal meshes or fabrics often used to protect the composite parts against lightning strikes are rendered unnecessary, since the titanium foil according to the invention can provide the same function. Furthermore, any electrical or electronical equipment to be protected from interference is also protected by the titanium foil.
- the titanium foil according to the invention does also provide an adequate fire barrier.
- the titanium foil applied to the outermost layer can enhance the decorative appearance of the composite material. Since the titanium used for the production of the foil can contain white pigments, the paintability of the material is surprisingly improved.
- the composite material according to the invention can provide an off-axis mechanical reinforcement, since composite materials generally have better properties like strength, toughness and the like in a first direction than in a second direction being substantially perpendicular to this first direction.
- This dependency of the mechanical property on the orientation of the composite material can at least partially be overcome by a suitable orientation of the titanium foil applied to the surface of the synthetic layer.
- the composite material and the titanium foil can be produced by using conventional machines and processes.
- the thin gauge of the foil according to the invention will allow the conformity of the material to some compound contours. In this regard, the narrow width of the foil will also allow an overlapping and conformity to the contour of adjacent structural components or materials.
- a composite material for the use as structural material for aircraft or boats.
- the composite material according to the invention also serves as a burn-through barrier and/or as an electric shielding for electronic or electric components embedded in the composite material.
- a method for producing a composite material comprising the steps of providing at least one fibre reinforced synthetic layer and providing a titanium foil, wherein the first surface of the titanium foil facing the synthetic layer on which the titanium foil is to be applied is prepared for an adhesive bonding with the synthetic layer structure.
- the titanium foil has a thickness of 100 ⁇ m or less to achieve the object of the invention.
- the thickness of the titanium foil is 20 ⁇ m or less and in a most preferred embodiment the titanium foil has a thickness of about 10 ⁇ m.
- the light weight construction of the composite material is most preferably achieved without a significant deterioration of the shielding capacity against lightning strikes or the moisture barrier property of the titanium foil. Furthermore, this thickness of less than 20 ⁇ m for the titanium foil provides an optimum relationship between the mechanical requirements and the need for a light weight construction.
- the titanium foil is made out of a chemically pure (CP) titanium or 15,33,3,3 titanium or 6Al-4Va titanium. This provides a crystal structure of the titanium which does not change over the service life of the titanium foil and, therefore, provides an unchanged bondability between the synthetic layer and the titanium foil without any necessary further interlayer or processing of the materials.
- CP chemically pure
- 6Al-4Va titanium This provides a crystal structure of the titanium which does not change over the service life of the titanium foil and, therefore, provides an unchanged bondability between the synthetic layer and the titanium foil without any necessary further interlayer or processing of the materials.
- At least one of the fibre reinforced synthetic layers has a honeycomb structure. This provides a particularly strong structure, improves the light weight property of the material and offers remarkable insulation characteristics to the material due to the internal spaces created by the honeycomb cells and any coating layer applied thereto.
- the synthetic layer can be made out of any suitable material known to the skilled person.
- the synthetic layer contains a resin system, which is in a more preferred way reinforced by either graphite fibres or glass fibres or aramide fibres or combinations thereof.
- the synthetic layer according to the invention can contain a mixture of two or more resins, preferably epoxy resins, BMI or polyamide resins.
- resins preferably epoxy resins, BMI or polyamide resins.
- Such a material combination of resins on the one hand and titanium foil on the others offers a harmonized thermal expansion coefficient of the materials, so that a bonding between the composite material and its titanium foil on the outermost layer is not weakened, even if it is periodically subjected to sharp temperature changes.
- Carbon fibres, glass fibres and/or aramide fibres or other fibres such as polyamide, polyester or polyethylene fibres serve as reinforcing material for the synthetic layer or layers .
- epoxy, BMI and/or polyamide resins are used for composite materials suitable for the use in aircraft and polyamide, polyester and/or polystyrene resins are used for composite materials suitable for the production of boats.
- At least one intermediate layer consisting of an organic compound is disposed between the synthetic layer and the titanium foil.
- this organic compound comprises epoxy resin and/or phenolic and/or polyamide resin systems.
- this compound layer has a mass per unit area of 150 g/m 2 or less and a density of 1.2 to 1.8 g/m 3 .
- the surface of the titanium foil intended to be applied to the fibre reinforced synthetic layer is in advance prepared for adhesive bonding with the synthetic layer.
- the surface of the titanium foil not facing the fibre reinforced synthetic layer is prepared for paint adhesion.
- the preparation of the titanium foil's surfaces can preferably be performed mechanically and/or chemically.
- the mechanical preparation of one or more surfaces of the titanium foil are achieved by roughening the foil's surfaces, for instance by sandblasting.
- the chemical processing can be performed by etching or the like, to achieve a removal and/or an exchange of at least a part of the titanium oxides present in the surface of the titanium foil, wherein the exchange is effected by embedding other metal oxides in the vacancies created by the removal of the titanium oxides.
- This chemical removal and replacement of titanium oxide is for instance performed in the Solgel-treatment developed by the Boeing Company, Seattle, Washington (US) , which is for example disclosed in EP 1 367 146 A2.
- This preparation of one or more surfaces of the titanium foil before the adhesion onto the synthetic layer or before applying a paint layer onto the titanium foil improves the bonding between the distinct layers and the durability of the bonding during the service life of the composite materials according to the invention.
- the above explained composite material is used as a structural material for aircraft or boats.
- this composite material is in particular used for those components of an aircraft or boat, in which the burn- through barrier properties of the material are of particular importance .
- the composite material serves as an electric shielding for electric or electronic components used in the aircraft or boat. Therefore, the composite material according to the invention is in particular preferred for the use of those parts of an aircraft or boat, in which these electronic or electric components are disposed adjacent to the composite material or are embedded in the composite material itself.
- This provides a use of the composite material according to the invention in which all advantages of the composite material according to the invention, i.e. the moisture barrier capacity, mechanical strengthening, protection from chemical attacks or from ultra-violet light, a diffusion of lightning strikes and the electronic shielding of the aircraft, the off-axis strength improvement of the structural components containing the composite material according to the invention, the simplification of a chemical or mechanical stripping of paint and the like are achieved together with a highly favoured application for a light weight construction of the aircraft or boats by using materials having an improved strength and toughness.
- all advantages of the composite material according to the invention i.e. the moisture barrier capacity, mechanical strengthening, protection from chemical attacks or from ultra-violet light, a diffusion of lightning strikes and the electronic shielding of the aircraft, the off-axis strength improvement of the structural components containing the composite material according to the invention, the simplification of a chemical or mechanical stripping of paint and the like are achieved together with a highly favoured application for a light weight construction of the aircraft or boats by using materials having an
- a method for producing the above-explained composite material comprising . the steps of providing at least one fibre reinforced synthetic layer and a titanium foil, wherein the surface of the titanium foil intended to be applied on the fibre reinforced synthetic layer is prepared for an adhesive bonding with this layer.
- the second surface of the titanium foil is prepared for a paint adhesion.
- This preparation of the second surface not facing the synthetic layer of the composite material according to the invention can be prepared either before or after applying the titanium foil onto the synthetic layer of the composite material.
- Fig. 1 shows a composite material according to a first embodiment of the invention
- Fig. 2 shows a composite material according to a second embodiment of the present invention.
- Fig. 1 shows an enlarged section of the composite material 1 according to the invention, which for clarity reasons is not necessarily drawn to scale.
- the composite material 1 comprises a fibre reinforced synthetic layer 2 and a titanium foil 3, wherein the fibre reinforced synthetic layer 2 has a honeycomb structure made out of any epoxy resin such as 8552 or M-50, available from Hexcel, Cycom 977, produced by Cytec, in which graphite fibres (not shown) are finely dispersed for a reinforcement of the honeycomb structure ' s material .
- the fibres contained in this resin to make a structural composite can be unidirectional or woven fabrics of Carbon, such as Toray, TohoTenax or others.
- the titanium foil according to this embodiment is a 10 ⁇ m thick foil made out of chemically pure titanium.
- a thin film of adhesive is interposed which is suitable to provide a strong and enduring bond between both components 2, 3 of the composite material 1.
- This adhesive is suitable to bond the titanium and its oxides of the foil 3 to the fibre reinforced synthetic layer 2.
- the adhesive is for instance FM-96 or FM-300 from Cytec or similar adhesives (EA 9696, EA 9695) available from Henkel, or AF 160 from 3M.
- an adhesion promoting primer is applied to the interface, such as BR-127, BR-6747 or BR-6757 of Cytec Engineered Materials or similar primers available from Henkel, 3M or J. D. Lincoln.
- the composite material 1 comprises a fibre reinforced synthetic layer 2 made out of an epoxy resin which is reinforced by finely dispersed glass fibres (not shown) , for instance E or S type glass fibres, available from Owens Corning, USA.
- the outermost layer 3 of the composite material 1 is constituted by a 20 ⁇ m thin titanium foil made out of 6Al-4Va titanium having a first surface 3a facing to the synthetic layer 2 and a second layer 3b onto which a paint (not shown) could be applied.
- the surface 3a was subjected to a Solgel-treatment by applying AC-130, available form Advanced Chemistry and Technology, Garden Grove, CA, USA onto this surface 3a to provide a better bonding to the intermediate layer 5 made out of an organic compound.
Landscapes
- Laminated Bodies (AREA)
Abstract
The invention relates to a composite material, comprising a laminate structure containing at least one fibre reinforced synthetic layer and a titanium foil constituting an outermost layer of the composite material, wherein the titanium foil has a thickness of 100 µm or less. Furthermore, the invention relates to a method for producing such a composite material, comprising the steps of providing at least one fibre reinforced synthetic layer, providing a titanium foil having a first surface prepared for adhesive bonding with the synthetic layer, and applying the thus prepared surface of the titanium foil onto the fibre reinforced synthetic layer. Finally, it relates to the use of this composite material as structural material for aircraft or boats.
Description
Titanium Barrier
Field of the invention
The invention relates to a composite material comprising a laminate structure containing at least one fibre reinforced synthetic layer, which is in particular used as a structural material for aircraft and boats. Furthermore, the invention relates to a method of producing such a composite material.
Background of the invention
Many industrial applications require materials which posses a combination of high strength, low weight and damage resistance. In order to meet these needs, light metals or laminate structures containing one or more synthetic layers, especially fibre reinforced synthetic layers have been developed.
The use of composite materials containing fibre reinforced synthetic layers require a number of properties to be met by this material. Firstly, the laminate structures have to be protected from water, atmospheric moisture and chemical ingression. Secondly, these structures have to be protected from mechanical damage and from deterioration by ultra-violet light. To meet these requirements, the composite materials in question are commonly coated with an adhesive film or an especially formulated resin to protect its surface. However, to provide a moisture sealing of the composite material being suitable to withstand the combination of mechanical attacks and sharp temperature differences, it has been found in
practice that such coatings do not provide satisfactory- results .
Therefore, other sealing methods, for instance methods involving applying a thin thermoplastic film or an aluminium foil, have been put in practice. However, these methods present a number of drawbacks. On the one hand, thermoplastic films are difficult to bond permanently to the composite and are easily damaged by mechanical attacks. Furthermore, these thermoplastic films do not present a vapor barrier having sufficient sealing properties. Moreover, in particular when used as a structural component for aircraft, thermoplastics do not offer a protection against lightning strikes. Finally, these thermoplastic films are relatively heavy. On the other hand, although aluminium foils present a sufficient water and vapor barrier and are easy to bond to the composite, they are easy to damage and, most particularly, corrosive with Carbon. Furthermore, there is a mismatch between the thermal coefficient of expansion and the modulus of elasticity between the aluminium and the composite material.
However, due to the fact that composite surfaces which are not covered are easily damaged, first by abrasion of the composite against the metal tooling during cool-down in manufacturing, then through handling in the shop, then in preparation for painting, and finally in the service by mechanical abrasion and other environmental conditions, a strong requirement for a suitable covering of the composite material exists.
Additionally, it has to be considered that composites are made from epoxy or other resin which degrade through ultra-violet light exposure when not protected with ultra-violet resistant paint. Also, these composite materials are quite difficult to
paint. In general, these composite materials are black, which is difficult to cover. Furthermore, any surface preparation for painting is difficult without damaging the composite structure. Paint does not adhere well to some composite surfaces when exposed to rain erosion and other attacks. Finally, it is often necessary to strip the paint from the composite materials, even when used as structural material for aircraft, and both chemical and mechanical removal techniques run the risk of damage to the structure .
Object of the invention
It was, therefore, an object of the invention to provide a composite structure, which does not present the drawbacks known from the prior art. It is another object of the invention to provide a material being suitable for use in aircraft, boats and other structure, which is light and strong, offers long durability even when exposed to variable and extreme climatic conditions. It is yet another object of the invention to provide a composite material having a moisture barrier property against atmospheric humidity and water, and which offers a shielding capacity against lightning strikes.
These objects are solved by the composite material comprising the features of claim 1, the use of this composite material according to claim 14 and by the method according to claim 18. Preferred embodiments of the invention are to be found in the respective relating claims .
According to a first aspect of the invention, is provided a composite material comprising a laminate structure containing at least one fibre reinforced synthetic layer and a titanium foil constituting an outermost layer of the composite material.
According to the invention, this titanium foil has a thickness of 100 μm or less.
By providing a titanium foil on the outermost part of the composite material, the metal meshes or fabrics often used to protect the composite parts against lightning strikes are rendered unnecessary, since the titanium foil according to the invention can provide the same function. Furthermore, any electrical or electronical equipment to be protected from interference is also protected by the titanium foil.
Furthermore, external and internal composite parts can be easily burned through, but the titanium foil according to the invention does also provide an adequate fire barrier. Moreover, the titanium foil applied to the outermost layer can enhance the decorative appearance of the composite material. Since the titanium used for the production of the foil can contain white pigments, the paintability of the material is surprisingly improved.
One more surprising effect of the composite material according to the invention is that by application of the titanium foil in relation to the synthetic layer, the composite material according to the invention can provide an off-axis mechanical reinforcement, since composite materials generally have better properties like strength, toughness and the like in a first direction than in a second direction being substantially perpendicular to this first direction. This dependency of the mechanical property on the orientation of the composite material can at least partially be overcome by a suitable orientation of the titanium foil applied to the surface of the synthetic layer.
Furthermore, the composite material and the titanium foil can be produced by using conventional machines and processes. Most surprisingly, the thin gauge of the foil according to the invention will allow the conformity of the material to some compound contours. In this regard, the narrow width of the foil will also allow an overlapping and conformity to the contour of adjacent structural components or materials.
According to a second aspect of the invention a composite material is provided for the use as structural material for aircraft or boats. In this application, the composite material according to the invention also serves as a burn-through barrier and/or as an electric shielding for electronic or electric components embedded in the composite material.
According to a third aspect of the invention, a method is provided for producing a composite material, comprising the steps of providing at least one fibre reinforced synthetic layer and providing a titanium foil, wherein the first surface of the titanium foil facing the synthetic layer on which the titanium foil is to be applied is prepared for an adhesive bonding with the synthetic layer structure. According to the invention, the titanium foil has a thickness of 100 μm or less to achieve the object of the invention. However, in a preferred embodiment of the invention, the thickness of the titanium foil is 20 μm or less and in a most preferred embodiment the titanium foil has a thickness of about 10 μm.
By using such a titanium foil having a minimal thickness, the light weight construction of the composite material is most preferably achieved without a significant deterioration of the shielding capacity against lightning strikes or the moisture
barrier property of the titanium foil. Furthermore, this thickness of less than 20 μm for the titanium foil provides an optimum relationship between the mechanical requirements and the need for a light weight construction.
In a further preferred embodiment of the invention, the titanium foil is made out of a chemically pure (CP) titanium or 15,33,3,3 titanium or 6Al-4Va titanium. This provides a crystal structure of the titanium which does not change over the service life of the titanium foil and, therefore, provides an unchanged bondability between the synthetic layer and the titanium foil without any necessary further interlayer or processing of the materials.
In yet another preferred embodiment according to the invention at least one of the fibre reinforced synthetic layers has a honeycomb structure. This provides a particularly strong structure, improves the light weight property of the material and offers remarkable insulation characteristics to the material due to the internal spaces created by the honeycomb cells and any coating layer applied thereto.
In the composite material according to the invention, the synthetic layer can be made out of any suitable material known to the skilled person. However, in a preferred embodiment of the invention the synthetic layer contains a resin system, which is in a more preferred way reinforced by either graphite fibres or glass fibres or aramide fibres or combinations thereof.
Furthermore, the synthetic layer according to the invention can contain a mixture of two or more resins, preferably epoxy resins, BMI or polyamide resins. Such a material combination of
resins on the one hand and titanium foil on the others offers a harmonized thermal expansion coefficient of the materials, so that a bonding between the composite material and its titanium foil on the outermost layer is not weakened, even if it is periodically subjected to sharp temperature changes. This also applies to material combinations, wherein according to a further preferred embodiment of the invention Carbon fibres, glass fibres and/or aramide fibres or other fibres such as polyamide, polyester or polyethylene fibres serve as reinforcing material for the synthetic layer or layers .
In a further preferred embodiment of the invention, epoxy, BMI and/or polyamide resins are used for composite materials suitable for the use in aircraft and polyamide, polyester and/or polystyrene resins are used for composite materials suitable for the production of boats.
In yet another preferred embodiment of the invention, at least one intermediate layer consisting of an organic compound is disposed between the synthetic layer and the titanium foil. In a more preferred embodiment of the invention, this organic compound comprises epoxy resin and/or phenolic and/or polyamide resin systems. In a highly preferred embodiment of the invention, this compound layer has a mass per unit area of 150 g/m2 or less and a density of 1.2 to 1.8 g/m3.
In a further preferred embodiment of the invention, the surface of the titanium foil intended to be applied to the fibre reinforced synthetic layer is in advance prepared for adhesive bonding with the synthetic layer. In yet another preferred embodiment of the invention, the surface of the titanium foil not facing the fibre reinforced synthetic layer is prepared for paint adhesion. The preparation of the titanium foil's surfaces
can preferably be performed mechanically and/or chemically. In a highly preferred embodiment of the invention, the mechanical preparation of one or more surfaces of the titanium foil are achieved by roughening the foil's surfaces, for instance by sandblasting. The chemical processing can be performed by etching or the like, to achieve a removal and/or an exchange of at least a part of the titanium oxides present in the surface of the titanium foil, wherein the exchange is effected by embedding other metal oxides in the vacancies created by the removal of the titanium oxides. This chemical removal and replacement of titanium oxide is for instance performed in the Solgel-treatment developed by the Boeing Company, Seattle, Washington (US) , which is for example disclosed in EP 1 367 146 A2. This preparation of one or more surfaces of the titanium foil before the adhesion onto the synthetic layer or before applying a paint layer onto the titanium foil improves the bonding between the distinct layers and the durability of the bonding during the service life of the composite materials according to the invention.
According to a second aspect of the invention, the above explained composite material is used as a structural material for aircraft or boats. In a more preferred embodiment of the invention, this composite material is in particular used for those components of an aircraft or boat, in which the burn- through barrier properties of the material are of particular importance .
In yet another preferred embodiment of the invention, the composite material serves as an electric shielding for electric or electronic components used in the aircraft or boat. Therefore, the composite material according to the invention is in particular preferred for the use of those parts of an
aircraft or boat, in which these electronic or electric components are disposed adjacent to the composite material or are embedded in the composite material itself.
This provides a use of the composite material according to the invention in which all advantages of the composite material according to the invention, i.e. the moisture barrier capacity, mechanical strengthening, protection from chemical attacks or from ultra-violet light, a diffusion of lightning strikes and the electronic shielding of the aircraft, the off-axis strength improvement of the structural components containing the composite material according to the invention, the simplification of a chemical or mechanical stripping of paint and the like are achieved together with a highly favoured application for a light weight construction of the aircraft or boats by using materials having an improved strength and toughness.
According to a third aspect of the invention it is provided a method for producing the above-explained composite material, comprising . the steps of providing at least one fibre reinforced synthetic layer and a titanium foil, wherein the surface of the titanium foil intended to be applied on the fibre reinforced synthetic layer is prepared for an adhesive bonding with this layer. In a more preferred embodiment of the method according to the invention also the second surface of the titanium foil is prepared for a paint adhesion. This preparation of the second surface not facing the synthetic layer of the composite material according to the invention can be prepared either before or after applying the titanium foil onto the synthetic layer of the composite material.
By using the method according to the invention a composite material is provided having improved bonding properties between the one or more layers of synthetic material and the titanium foil constituting the outermost layer of the composite material. This improved bonding preferably also applies to the bonding between the titanium foil and a paint covering the composite material.
The invention will now be explained in more detail referring to the accompanying figures showing exemplary preferred embodiments of the invention not being suitable to limit the scope of the invention which is pointed out in the set of appending claims .
Brief description of the drawings
Fig. 1 shows a composite material according to a first embodiment of the invention, and
Fig. 2 shows a composite material according to a second embodiment of the present invention.
Best mode for employing the invention
Fig. 1 shows an enlarged section of the composite material 1 according to the invention, which for clarity reasons is not necessarily drawn to scale. The composite material 1 comprises a fibre reinforced synthetic layer 2 and a titanium foil 3, wherein the fibre reinforced synthetic layer 2 has a honeycomb structure made out of any epoxy resin such as 8552 or M-50, available from Hexcel, Cycom 977, produced by Cytec, in which graphite fibres (not shown) are finely dispersed for a reinforcement of the honeycomb structure ' s material . The fibres
contained in this resin to make a structural composite can be unidirectional or woven fabrics of Carbon, such as Toray, TohoTenax or others. The titanium foil according to this embodiment is a 10 μm thick foil made out of chemically pure titanium. At the interface 4 between the synthetic layer 2 and the titanium foil 3 a thin film of adhesive is interposed which is suitable to provide a strong and enduring bond between both components 2, 3 of the composite material 1. This adhesive is suitable to bond the titanium and its oxides of the foil 3 to the fibre reinforced synthetic layer 2. The adhesive is for instance FM-96 or FM-300 from Cytec or similar adhesives (EA 9696, EA 9695) available from Henkel, or AF 160 from 3M. Furthermore, an adhesion promoting primer is applied to the interface, such as BR-127, BR-6747 or BR-6757 of Cytec Engineered Materials or similar primers available from Henkel, 3M or J. D. Lincoln.
In Fig. 2, a second embodiment of the composite material 1 according to the invention is shown, which is also not necessarily drawn to scale. The composite material 1 comprises a fibre reinforced synthetic layer 2 made out of an epoxy resin which is reinforced by finely dispersed glass fibres (not shown) , for instance E or S type glass fibres, available from Owens Corning, USA. The outermost layer 3 of the composite material 1 is constituted by a 20 μm thin titanium foil made out of 6Al-4Va titanium having a first surface 3a facing to the synthetic layer 2 and a second layer 3b onto which a paint (not shown) could be applied. The surface 3a was subjected to a Solgel-treatment by applying AC-130, available form Advanced Chemistry and Technology, Garden Grove, CA, USA onto this surface 3a to provide a better bonding to the intermediate layer 5 made out of an organic compound.
Claims
1. Composite material, comprising a laminate structure containing at least one fibre reinforced synthetic layer and a titanium foil constituting an outermost layer of the composite material, wherein the titanium foil has a thickness of 100 μm or less.
2. Composite material according to claim 1, characterized in that the titanium foil has a thickness of 20μm or less, preferably about lOμm.
3. Composite material according to one of the preceding claims, characterized in that the titanium foil is made out of chemical pure (CP) titanium, 15,3,3,3 titanium or 6Al-4Va titanium.
4. Composite material according to one of the preceding claims, characterized in that at least one of the fibre reinforced synthetic layers has a honeycomb structure.
5. Composite material according to one of the preceding claims, characterized in that the fibre reinforced synthetic layer comprises fibre reinforced resins.
6. Composite material according to any one of the preceding claims, characterized in that the fibre reinforced synthetic layer comprises Carbon, glass or aramide fibres.
7. Composite material according to one of the preceding claims, characterized in that at least one intermediate layer consisting of an organic compound is disposed between the synthetic layer and the titanium foil.
8. Composite material according to claim 7, characterized in that the organic compound comprises epoxy resin and/or phenolic resin and/or polyamide resin systems.
9. Composite material according to claims 7 or 8, characterized in that the mass per unit area of the intermediate layer is 150 g/m2 or less.
10. Composite material according to one of the preceding claims 7 - 9, characterized in that the density of the intermediate layer is in the range of 1.2 - 1.8 g/cm3.
11. Composite material according to one of the preceding claims, characterized in that the surface of the titanium foil facing the fibre reinforced synthetic layer is prepared for adhesive bonding with the synthetic layer.
12. Composite material according to one of the preceding claims, characterized in that the surface of the titanium foil not facing the fibre reinforced synthetic layer is prepared for paint adhesion.
13. Composite material according to one of the preceding claims, characterized in that the surface or the surfaces of the titanium foil are prepared mechanically, preferably by roughening, for instance by sandblasting, and/or chemically, preferably by the removal and/or an exchange of at least a part of the titanium oxides present in the surface of the titanium foil by other metal oxides.
14. Use of the composite material according to one of the preceding claims as structural material for aircraft or boats .
15. Use according to claim 14, characterized in that the composite material serves as a burn through barrier in the aircraft .
16. Use according to one of the claims 14 and 15, characterized in that the composite material serves as an electric shield for electronic components embedded in the composite material.
17. Use according to one of the claims 14 to 16, characterized in that the composite material serves as a protection against lightning strike.
18. Method for producing a composite material according to any one of the claims 1 - 13, comprising the steps of providing at least one fibre reinforced synthetic layer, providing a titanium foil having a first surface prepared for adhesive bonding with the synthetic layer and applying the thus prepared surface of the titanium foil onto the fibre reinforced synthetic layer.
19. Method according to claim 18, characterized in that it further comprises the step of preparing a second surface of the titanium foil for paint adhesion.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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PCT/EP2005/011481 WO2007048426A1 (en) | 2005-10-26 | 2005-10-26 | Titanium barrier |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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PCT/EP2005/011481 WO2007048426A1 (en) | 2005-10-26 | 2005-10-26 | Titanium barrier |
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WO2007048426A1 true WO2007048426A1 (en) | 2007-05-03 |
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PCT/EP2005/011481 WO2007048426A1 (en) | 2005-10-26 | 2005-10-26 | Titanium barrier |
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US8503153B2 (en) | 2009-04-17 | 2013-08-06 | 3M Innovative Properties Company | Lightning protection sheet with patterned discriminator |
DE102012003731A1 (en) | 2012-02-28 | 2013-08-29 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Semi-finished product for the production of a fiber composite metal hybrid laminate and method for producing such a semifinished product |
US8922970B2 (en) | 2009-04-17 | 2014-12-30 | 3M Innovative Properties Company | Lightning protection sheet with patterned conductor |
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EP0416432A2 (en) * | 1989-09-04 | 1991-03-13 | Kabushiki Kaisha Fukurotani Seisakusho | A shaft body made of metal film and carbon fibers and method for manufacturing the same |
EP0743174A2 (en) * | 1995-05-17 | 1996-11-20 | Ykk Corporation | Laminated plate material and loom harness frame manufactured therefrom |
EP0783960A2 (en) * | 1996-01-11 | 1997-07-16 | The Boeing Company | Titanium-polymer hybrid laminates |
EP1104693A1 (en) * | 1999-04-08 | 2001-06-06 | Showa Co., Ltd. | Titanium composite material |
EP1454737A1 (en) * | 2003-03-04 | 2004-09-08 | Fuji Jukogyo Kabushiki Kaisha | Composite material and method of manufacturing the same |
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EP0416432A2 (en) * | 1989-09-04 | 1991-03-13 | Kabushiki Kaisha Fukurotani Seisakusho | A shaft body made of metal film and carbon fibers and method for manufacturing the same |
EP0743174A2 (en) * | 1995-05-17 | 1996-11-20 | Ykk Corporation | Laminated plate material and loom harness frame manufactured therefrom |
EP0783960A2 (en) * | 1996-01-11 | 1997-07-16 | The Boeing Company | Titanium-polymer hybrid laminates |
EP1104693A1 (en) * | 1999-04-08 | 2001-06-06 | Showa Co., Ltd. | Titanium composite material |
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Publication number | Priority date | Publication date | Assignee | Title |
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US8503153B2 (en) | 2009-04-17 | 2013-08-06 | 3M Innovative Properties Company | Lightning protection sheet with patterned discriminator |
US8760838B2 (en) | 2009-04-17 | 2014-06-24 | 3M Innovative Properties Company | Lightning protection sheet with patterned discriminator |
US8922970B2 (en) | 2009-04-17 | 2014-12-30 | 3M Innovative Properties Company | Lightning protection sheet with patterned conductor |
US9516727B2 (en) | 2009-04-17 | 2016-12-06 | 3M Innovative Properties Company | Lightning protection sheet with patterned discriminator |
DE102012003731A1 (en) | 2012-02-28 | 2013-08-29 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Semi-finished product for the production of a fiber composite metal hybrid laminate and method for producing such a semifinished product |
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