NL1025744C2 - Laminate with metal layers, used for aerospace applications, contains electrical heating layer - Google Patents
Laminate with metal layers, used for aerospace applications, contains electrical heating layer Download PDFInfo
- Publication number
- NL1025744C2 NL1025744C2 NL1025744A NL1025744A NL1025744C2 NL 1025744 C2 NL1025744 C2 NL 1025744C2 NL 1025744 A NL1025744 A NL 1025744A NL 1025744 A NL1025744 A NL 1025744A NL 1025744 C2 NL1025744 C2 NL 1025744C2
- Authority
- NL
- Netherlands
- Prior art keywords
- layer
- layers
- laminate
- laminate according
- heating layer
- Prior art date
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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
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
-
- 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
- B32B15/04—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
- B32B15/092—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 comprising epoxy resins
-
- 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
- B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
-
- 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
- B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
- B32B17/02—Layered products essentially comprising sheet glass, or glass, slag, or like fibres in the form of fibres or filaments
- B32B17/04—Layered products essentially comprising sheet glass, or glass, slag, or like fibres in the form of fibres or filaments bonded with or embedded in a plastic substance
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/20—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
- H05B3/22—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater non-flexible
- H05B3/28—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater non-flexible heating conductor embedded in insulating material
-
- 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
- B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
- B32B2307/206—Insulating
-
- 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
- B32B2307/304—Insulating
-
- 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
- B32B2311/24—Aluminium
-
- 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
- B32B2363/00—Epoxy resins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
Abstract
Description
Laminaat met verwarmingselementLaminate with heating element
De uitvinding betreft een laminaat uit afwisselend metaallagen en zich tussen de metaallagen bevindende kunststof hechtlagen voor het vervaardigen van structuurdelen 5 zoals panelen, die toepasbaar zijn in de luchtvaart en/of de ruimtevaart. Dergelijke laminaten zijn bekend, en worden toegepast in panelen voor diverse onderdelen van de dragende vliegtuigconstructie. Voorbeeld zijn de huidpanelen voor de vliegtuigramp en de vleugelpanelen voor de vliegtuigvleugels.The invention relates to a laminate of alternating metal layers and plastic adhesive layers located between the metal layers for the manufacture of structural parts such as panels, which can be used in aviation and / or space travel. Such laminates are known and are used in panels for various parts of the bearing aircraft construction. Examples are the skin panels for the aircraft disaster and the wing panels for the aircraft wings.
Panelen die uit een laminaat bestaan bezitten grote voordelen in vergelijking met 10 volledig metalen panelen, zoals aluminium panelen. Allereerst is het gewicht van panelen uit een laminaat bij overigens gelijke sterkte en stijfheid lager dan die van volledig uit aluminium bestaande panelen. Verder is het vermoeiingsgedrag van dergelijke laminaten veel gunstiger. Eventuele scheurtjes in de metaallagen worden gestopt door de aangrenzende kunststoflagen, zodanig dat ook onder wisselende belastingen geen ver-15 dere scheurgroei zal optreden. Een ander voordeel van dergelijke laminaten ligt in de goede botsbestendigheid. Deze eigenschap is in het bijzonder van belang bij toepassing in de voorranden van de vleugels en de staart en van de huidpanelen van beweegbare vleugel- en staartdelen.Panels consisting of a laminate have great advantages in comparison with all-metal panels, such as aluminum panels. First of all, the weight of laminate panels with equal strength and rigidity is lower than that of panels made entirely of aluminum. Furthermore, the fatigue behavior of such laminates is much more favorable. Any cracks in the metal layers are stopped by the adjacent plastic layers, such that no further crack growth will occur even under varying loads. Another advantage of such laminates lies in the good crash resistance. This property is of particular importance when used in the front edges of the wings and tail and of the skin panels of movable wing and tail parts.
Bij bepaalde panelen van de vliegtuigconstructie kan zich het probleem van ijsaf-20 zetting voordoen. Vooral ijsaangroei op de voorrand van de vleugel is gevaarlijk. Een dergelijke ijsaangroei beïnvloedt de luchtstroming langs de vleugel, zodanig dat het het draagvermogen van de vleugel sterk terug kan lopen. Teneinde dit verschijnsel tegen te gaan, wordt de voorrand van de vleugels vaak voorzien van ijsbestrijdingsmiddelen. Deze kunnen zowel het ontstaan van ijs verhinderen, als ook bijdragen tot het doen 25 verdwijnen van reeds aangegroeid ijs. Bekend is om bij panelen die uit laminaten bestaan een verwarmbare folie op de voorrand te lijmen. Een voorbeeld van deze techniek is gegeven in WO-A-03038841. Een verder voorbeeld is bekend uit WO-A-0108463. Daarbij wordt op een paneel dat bestaat uit een vezelversterkt kunststof laminaat een elektrisch isolerende laag en vervolgens een verwarmbare grafietfolie gelijmd. Volgens 30 een alternatieve uitvoering kan de grafietfolie ook worden ingebed in het vezelversterk-te kunststof laminaat. Op de buitenzijde van de composiet wordt een warmtegeleidende laag aan gebracht, die zich bevindt dichtbij of tegen de grafietfolie.With certain panels of the aircraft construction, the problem of icing may occur. Ice growth on the front edge of the wing in particular is dangerous. Such ice build-up influences the air flow along the wing, such that it can greatly reduce the bearing capacity of the wing. In order to counteract this phenomenon, the front edge of the wings is often provided with ice-fighting agents. These can both prevent the formation of ice and also contribute to the disappearance of already grown ice. For panels consisting of laminates, it is known to glue a heatable film on the front edge. An example of this technique is given in WO-A-03038841. A further example is known from WO-A-0108463. An electrically insulating layer and subsequently a heatable graphite foil are glued to a panel consisting of a fiber-reinforced plastic laminate. According to an alternative embodiment, the graphite foil can also be embedded in the fiber-reinforced plastic laminate. A thermally conductive layer is applied to the outside of the composite, which layer is located close to or against the graphite foil.
1025744 11025744 1
I 2 II 2 I
I Nadeel van deze bekende verwarmbare laminaten is dat de verwarmbare en/of de IA drawback of these known heatable laminates is that the heatable and / or the I
I warmtegeleidende laag die zich aan het buitenoppervlak bevindt, extra weerstand ople- II thermally conductive layer located on the outer surface provides extra resistance
I vert. Dit leidt tot een hoger brandstofverbruik. II vert. This leads to a higher fuel consumption. I
I Doel van de uitvinding is daarom een laminaat te verschaffen dat een hoge struc- IThe object of the invention is therefore to provide a laminate that has a high structure
I 5 turele stijfheid en sterkte bezit in combinatie met goede bots- of impacteigenschappen, II have structural stiffness and strength in combination with good impact or impact properties, I
I en dat is voorzien van een verwarmingsmiddel dat beschermd is tegen omgevingsin- II and which is provided with a heating means that is protected against environmental conditions
I vloeden. Dat doel wordt bereikt doordat tussen tenminste twee metaallagen een elek- II flooded. This object is achieved in that an electrical connection between at least two metal layers
I trisch verwarmingslaag is voorzien, welke verwarmingslaag elektrisch is geïsoleerd ten IA heating layer is provided, which heating layer is electrically insulated
I opzichte van die metaallagen. II compared to those metal layers. I
I 10 Het laminaat volgens de uitvinding bestaat uit afwisselende metaallagen en IThe laminate according to the invention consists of alternating metal layers and I
I kunststoflagen, en bezit daardoor goede mechanische eigenschappen. Tevens is in het II plastic layers, and therefore has good mechanical properties. Also in the I
I inwendige van het laminaat, bij voorkeur zo dicht mogelijk bij de buitenste laag, een II interior of the laminate, preferably as close as possible to the outer layer, a I
I elektrisch verwarmingsmiddel ingebed. De elektrische isolatie van het verwarmings- II electric heating means embedded. The electrical insulation of the heating I
I middel ten opzichte van de naburige metaallagen kan worden verkregen door middel IThe agent relative to the neighboring metal layers can be obtained by agent I
I 15 van twee elektrisch isolerende lagen. Deze elektrisch isolerende lagen kunnen ook de I15 of two electrically insulating layers. These electrically insulating layers can also be the I
I kunststof hechtlagen zijn, die toch al deel uitmaakt van het standaard laminaat. II are plastic bonding layers, which is already part of the standard laminate. I
I Aan de binnenzijde van de verwarmbare laag kan zich een laag met thermische IOn the inside of the heatable layer, a layer with thermal I
I barrière-eigenschappen bevinden. De verwarmingsenergie kan daardoor hoofdzakelijk II barrier properties. The heating energy can therefore mainly be I
I gericht worden op de buitenste metaallaag waar zich ijsafzetting kan voordoen. II should be aimed at the outermost metal layer where ice deposits can occur. I
I 20 De verwarmingslaag kan op verschillende manieren zijn uitgevoerd. Volgens een IThe heating layer can be designed in various ways. According to an I
I eerste mogelijkheid kan deze een weerstandsfolie omvatten. Volgens een alternatieve IIn the first possibility, it may comprise a resistive film. According to an alternative I
I uitvoering kan de verwarmingslaag een geweven laag omvatten waarin zich weer- IIn the embodiment, the heating layer may comprise a woven layer in which is again present
I standsdraden bevinden. II stand wires. I
I Het laminaat kan eveneens op verschillende manieren zijn uitgevoerd, bijvoor- IThe laminate can also be designed in various ways, for example
I 25 beeld met kunststof hechtlagen die elk tenminste een vezelversterkte laag omvatten IImage with plastic adhesive layers, each comprising at least one fiber-reinforced layer
I (FML), of met kunststof hechtlagen die elk tenminste een lijmlaag omvatten (AML). II (FML), or with plastic adhesive layers, each comprising at least one adhesive layer (AML). I
I De metaallagen omvatten bij voorkeur aluminium. IThe metal layers preferably comprise aluminum. I
I Vervolgens zal de uitvinding nader worden toegelicht aan de hand van een in de IThe invention will be explained in more detail below with reference to an I
I figuren weergegeven uitvoeringsvoorbeeld. IExemplary embodiment shown in the figures. I
I 30 Figuur 1 toont een doorsnede door een vleugelvoorrand. IFigure 1 shows a section through a wing leading edge. I
I Figuur 2 toont op vergrote schaal detail Π van figuur 1. IFigure 2 shows detail Π of Figure 1 on an enlarged scale. I
I In figuur 1 is in dwarsdoosnede de in zijn geheel met 10 aangeduide vleugelvoor- IIn Fig. 1, the wing front indicated in its entirety by 10 is shown in cross-section
I rand weergegeven. Deze vleugelvoorrand sluit aan op een tweetal panelen 11,12, en is II border shown. This wing leading edge connects to two panels 11, 12, and is I
I 1025744 ! II 1025744! I
3 daaraan bevestigd door middel van op zich bekende, verder niet weergegeven bevestigingsmiddelen. De vleugelvoorrand bestaat uit een gebogen laminaat dat in doorsnede op grotere schaal is weergegeven in figuur 2.3 attached thereto by means of per se known fixing means (not further shown). The wing leading edge consists of a curved laminate that is shown in section on a larger scale in Figure 2.
Het laminaat omvat metaallagen, in het bijzonder aluminiumlagen 1 alsmede zich 5 tussen de metaallagen bevindende kunststof hechtlagen 2. Deze kunststof hechtlagen bestaan in het weergegeven uitvoeringsvoorbeeld uit vezel versterkte kunststoflagen 3, 4, die onder 90° ten opzichte van elkaar zijn georiënteerd (prepreg).The laminate comprises metal layers, in particular aluminum layers 1, and plastic adhesive layers 2 located between the metal layers. In the exemplary embodiment shown, these plastic adhesive layers consist of fiber-reinforced plastic layers 3, 4 which are oriented at 90 ° relative to each other (prepreg) .
Bij het toepassen van het in de figuur weergegeven laminaat in een paneel voor een vliegtuig, bijvoorbeeld de voorhand van een vleugel, komt één der aluminiumlagen 10 aan de buitenzijde 5 te liggen, terwijl de andere aluminiumlaag 1 zich aan de binnenzijde 6 bevindt.When applying the laminate shown in the figure in a panel for an aircraft, for example the front of a wing, one of the aluminum layers 10 comes to lie on the outside 5, while the other aluminum layer 1 is on the inside 6.
Nabij de aluminiumlaag 1 die zich aan de buitenzijde bevindt, is een verwar-mingslaag 7 aangebracht. Dat kan bijvoorbeeld een aluminiumweerstandsfolie zijn, een geweven laag met daarin verwerkte weerstandsdraden enzovoorts. Tussen de verwar-15 mingslaag 7 en de buitenste aluminiumlaag 1 bevindt zich een elektrische isolatielaag 8, die bijvoorbeeld ook een vezelversterkte kunststof hechtlaag kan zijn.Near the aluminum layer 1 which is located on the outside, a heating layer 7 is provided. This can be, for example, an aluminum resistance foil, a woven layer with processed resistance wires and so on. Between the heating layer 7 and the outer aluminum layer 1 there is an electrical insulation layer 8, which may also be, for example, a fiber-reinforced plastic adhesive layer.
Tenslotte kan aan de binnenzijde van de verwarmingslaag 7 een isolatielaag 9 zijn voorzien. Noodzakelijk is dat niet omdat de aangrenzende kunststof hechtlaag 2 al elektrisch isolerende werking bezit. Het voordeel van een aanvullende thermische isola-20 tielaag 9 is echter dat de warmte vooral terecht komt bij de buitenste aluminiumlaag 1, die gevoelig is voor ijsafzetting.Finally, an insulating layer 9 can be provided on the inside of the heating layer 7. This is not necessary because the adjacent plastic adhesive layer 2 already has an electrically insulating effect. The advantage of an additional thermal insulation layer 9, however, is that the heat ends up mainly with the outer aluminum layer 1, which is sensitive to ice deposits.
10257441025744
Claims (12)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
NL1025744A NL1025744C2 (en) | 2004-03-16 | 2004-03-16 | Laminate with metal layers, used for aerospace applications, contains electrical heating layer |
PCT/NL2005/000201 WO2005087589A1 (en) | 2004-03-16 | 2005-03-16 | Laminate with heating element |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
NL1025744 | 2004-03-16 | ||
NL1025744A NL1025744C2 (en) | 2004-03-16 | 2004-03-16 | Laminate with metal layers, used for aerospace applications, contains electrical heating layer |
Publications (2)
Publication Number | Publication Date |
---|---|
NL1025744A1 NL1025744A1 (en) | 2004-05-27 |
NL1025744C2 true NL1025744C2 (en) | 2005-01-18 |
Family
ID=32822970
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
NL1025744A NL1025744C2 (en) | 2004-03-16 | 2004-03-16 | Laminate with metal layers, used for aerospace applications, contains electrical heating layer |
Country Status (2)
Country | Link |
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NL (1) | NL1025744C2 (en) |
WO (1) | WO2005087589A1 (en) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102005060958A1 (en) * | 2005-12-20 | 2007-06-21 | Airbus Deutschland Gmbh | Aircraft structure protection, against damage from birds in flight, is an outer skin of glass fiber reinforced aluminum with a hollow zone to allow skin distortion through an impact |
FR2898868B1 (en) * | 2006-03-24 | 2008-12-12 | Aircelle Sa | STRUCTURE FOR AIR ENTRANCE LAUNCHER WITH ELECTRIC DEFROSTING |
US9004407B2 (en) | 2008-12-24 | 2015-04-14 | Middle River Aircraft Systems | Anti-icing system and method for preventing ice accumulation |
US9006119B2 (en) | 2009-10-01 | 2015-04-14 | A.L.D. Advanced Logistics Development Ltd. | Composite material, a structural element comprised of the composite material, an airplane wing spar and their methods of production |
FR2961484B1 (en) * | 2010-06-18 | 2013-01-04 | Snecma | AIR INLET HANDLE FOR TURBOREACTOR NACELLE |
US9522512B2 (en) | 2010-08-17 | 2016-12-20 | The Boeing Company | Methods for making composite structures having composite-to-metal joints |
US8993084B2 (en) | 2010-08-17 | 2015-03-31 | The Boeing Company | Multi-layer metallic structure and composite-to-metal joint methods |
DE102012002132A1 (en) | 2012-02-03 | 2013-08-08 | Airbus Operations Gmbh | Anti-icing system for an aircraft and method of operating an anti-icing system |
JP6690910B2 (en) * | 2014-10-09 | 2020-04-28 | ザ・ボーイング・カンパニーThe Boeing Company | COMPOSITE MATERIAL STRUCTURE HAVING JOINT OF COMPOSITE MATERIAL AND METAL, AND MANUFACTURING METHOD THEREOF |
US11952130B2 (en) | 2020-03-27 | 2024-04-09 | Airbus Operations Gmbh | Structural component for an aircraft with integrated heating layer and structural battery |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1230668A (en) * | 1958-04-24 | 1960-09-19 | Goodrich Co B F | Process and apparatus for the manufacture of heating laminates, applicable in particular to aircraft de-icing elements |
FR1428560A (en) * | 1965-01-04 | 1966-02-18 | New laminated hotplate | |
EP0459216A2 (en) * | 1990-06-01 | 1991-12-04 | The B.F. Goodrich Company | Electrical heater de-icer |
US5951800A (en) * | 1992-11-18 | 1999-09-14 | Mcdonnell Douglas Corp. | Fiber/metal laminate splice |
WO2001008463A2 (en) | 1999-07-30 | 2001-02-08 | Northcoast Technologies | Aircraft de-icing system |
WO2001017850A1 (en) * | 1999-09-10 | 2001-03-15 | Bfgoodrich Company | Aircraft heated floor panel |
WO2002094565A1 (en) * | 2001-05-21 | 2002-11-28 | Fokker Aerostructures B.V. | Method for producing a shaped laminate |
WO2003038841A1 (en) | 2001-10-17 | 2003-05-08 | Rung-Rannow Joerg | Heating film consisting of a plurality of layers and method for producing the same |
-
2004
- 2004-03-16 NL NL1025744A patent/NL1025744C2/en not_active IP Right Cessation
-
2005
- 2005-03-16 WO PCT/NL2005/000201 patent/WO2005087589A1/en active Application Filing
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1230668A (en) * | 1958-04-24 | 1960-09-19 | Goodrich Co B F | Process and apparatus for the manufacture of heating laminates, applicable in particular to aircraft de-icing elements |
FR1428560A (en) * | 1965-01-04 | 1966-02-18 | New laminated hotplate | |
EP0459216A2 (en) * | 1990-06-01 | 1991-12-04 | The B.F. Goodrich Company | Electrical heater de-icer |
US5951800A (en) * | 1992-11-18 | 1999-09-14 | Mcdonnell Douglas Corp. | Fiber/metal laminate splice |
WO2001008463A2 (en) | 1999-07-30 | 2001-02-08 | Northcoast Technologies | Aircraft de-icing system |
WO2001017850A1 (en) * | 1999-09-10 | 2001-03-15 | Bfgoodrich Company | Aircraft heated floor panel |
WO2002094565A1 (en) * | 2001-05-21 | 2002-11-28 | Fokker Aerostructures B.V. | Method for producing a shaped laminate |
WO2003038841A1 (en) | 2001-10-17 | 2003-05-08 | Rung-Rannow Joerg | Heating film consisting of a plurality of layers and method for producing the same |
Also Published As
Publication number | Publication date |
---|---|
NL1025744A1 (en) | 2004-05-27 |
WO2005087589A1 (en) | 2005-09-22 |
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