WO2007048426A1 - Barrière en titane - Google Patents

Barrière en titane Download PDF

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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
Application number
PCT/EP2005/011481
Other languages
English (en)
Inventor
Tom Batot Frazier
Original Assignee
Tom Batot Frazier
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Tom Batot Frazier filed Critical Tom Batot Frazier
Priority to PCT/EP2005/011481 priority Critical patent/WO2007048426A1/fr
Publication of WO2007048426A1 publication Critical patent/WO2007048426A1/fr

Links

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.

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  • Laminated Bodies (AREA)

Abstract

L'invention concerne un matériau composite, comprenant une structure stratifiée contenant au moins une couche synthétique renforcée avec des fibres et une feuille de titane constituant la couche la plus à l'extérieur du matériau composite, ladite feuille de titane ayant une épaisseur inférieure ou égale à 100 µm. En outre, l'invention concerne un procédé servant à produire un tel matériau composite, comprenant les étapes consistant à obtenir au moins une couche synthétique renforcée avec des fibres, obtenir une feuille de titane ayant une première surface préparée pour l'assemblage par collage avec la couche synthétique et appliquer la surface ainsi préparée de la feuille de titane sur la couche synthétique renforcée avec des fibres. Enfin, l'invention concerne l'utilisation de ce matériau composite comme matériau de structure pour des aéronefs ou des bateaux.
PCT/EP2005/011481 2005-10-26 2005-10-26 Barrière en titane WO2007048426A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/EP2005/011481 WO2007048426A1 (fr) 2005-10-26 2005-10-26 Barrière en titane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2005/011481 WO2007048426A1 (fr) 2005-10-26 2005-10-26 Barrière en titane

Publications (1)

Publication Number Publication Date
WO2007048426A1 true WO2007048426A1 (fr) 2007-05-03

Family

ID=36608563

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2005/011481 WO2007048426A1 (fr) 2005-10-26 2005-10-26 Barrière en titane

Country Status (1)

Country Link
WO (1) WO2007048426A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8503153B2 (en) 2009-04-17 2013-08-06 3M Innovative Properties Company Lightning protection sheet with patterned discriminator
DE102012003731A1 (de) 2012-02-28 2013-08-29 Deutsches Zentrum für Luft- und Raumfahrt e.V. Halbzeug für die Herstellung eines Faserverbund-Metallhybridlaminats und Verfahren zur Herstellung eines derartigen Halbzeuges
US8922970B2 (en) 2009-04-17 2014-12-30 3M Innovative Properties Company Lightning protection sheet with patterned conductor

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0416432A2 (fr) * 1989-09-04 1991-03-13 Kabushiki Kaisha Fukurotani Seisakusho Tige en film de métal et fibres de charbon, et procédé de fabrication
EP0743174A2 (fr) * 1995-05-17 1996-11-20 Ykk Corporation Produit multicouche en forme de plaques et cadre de lame fabriqué à partir de celle-ci
EP0783960A2 (fr) * 1996-01-11 1997-07-16 The Boeing Company Laminés hybrides titane-polymère
EP1104693A1 (fr) * 1999-04-08 2001-06-06 Showa Co., Ltd. Materiau composite au titane
EP1454737A1 (fr) * 2003-03-04 2004-09-08 Fuji Jukogyo Kabushiki Kaisha Matériau composite et procédé de sa fabrication

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0416432A2 (fr) * 1989-09-04 1991-03-13 Kabushiki Kaisha Fukurotani Seisakusho Tige en film de métal et fibres de charbon, et procédé de fabrication
EP0743174A2 (fr) * 1995-05-17 1996-11-20 Ykk Corporation Produit multicouche en forme de plaques et cadre de lame fabriqué à partir de celle-ci
EP0783960A2 (fr) * 1996-01-11 1997-07-16 The Boeing Company Laminés hybrides titane-polymère
EP1104693A1 (fr) * 1999-04-08 2001-06-06 Showa Co., Ltd. Materiau composite au titane
EP1454737A1 (fr) * 2003-03-04 2004-09-08 Fuji Jukogyo Kabushiki Kaisha Matériau composite et procédé de sa fabrication

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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 (de) 2012-02-28 2013-08-29 Deutsches Zentrum für Luft- und Raumfahrt e.V. Halbzeug für die Herstellung eines Faserverbund-Metallhybridlaminats und Verfahren zur Herstellung eines derartigen Halbzeuges

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