WO2005087589A1 - Laminate with heating element - Google Patents

Laminate with heating element Download PDF

Info

Publication number
WO2005087589A1
WO2005087589A1 PCT/NL2005/000201 NL2005000201W WO2005087589A1 WO 2005087589 A1 WO2005087589 A1 WO 2005087589A1 NL 2005000201 W NL2005000201 W NL 2005000201W WO 2005087589 A1 WO2005087589 A1 WO 2005087589A1
Authority
WO
WIPO (PCT)
Prior art keywords
layer
laminate according
layers
metal layers
heating layer
Prior art date
Application number
PCT/NL2005/000201
Other languages
French (fr)
Inventor
Leonardus Johannes Bernard Peeters
Original Assignee
Stork Fokker Aesp B.V.
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 Stork Fokker Aesp B.V. filed Critical Stork Fokker Aesp B.V.
Publication of WO2005087589A1 publication Critical patent/WO2005087589A1/en

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
    • 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

Definitions

  • the invention relates to a laminate consisting of alternating metal layers and plastic adhesive layers located between the metal layers for the production of structural parts such as panels that can be used in aviation and/or aerospace.
  • Such laminates are known and are used in panels for various components of the load-bearing aircraft construction. Examples are the skin panels for the aircraft body and the wing panels for the aircraft wings.
  • Panels that consist of a laminate have substantial advantages compared with completely metal panels, such as aluminium panels.
  • the weight of panels consisting of a laminate having otherwise equal strength and rigidity is lower than that of panels consisting wholly of aluminium.
  • the fatigue characteristics of such laminates are much more advantageous. Any cracks in the metal layers are stopped by the adjacent plastic layers, such that no further crack growth will occur even under fluctuating loads.
  • Another advantage of such laminates lies in the good ability to withstand collisions. This characteristic is particularly important in the case of use in the leading edges of the wings and the tail and of the skin panels of moving wing and tail components.
  • the problem of icing can arise with certain panels of the aircraft construction.
  • ice growth at the leading edge of the wing is dangerous.
  • Such ice growth influences the flow of air over the wing, such that the load bearing capacity of the wing can decrease sharply.
  • the leading edge of the wings is frequently provided with anti-icing means. These can both prevent the formation of ice and also contribute to the removal of ice that has already grown.
  • panels that consist of laminates it is known to glue a heatable film on the leading edge.
  • the aim of the invention is, therefore, to provide a laminate that has a high structural rigidity and strength in combination with good collision or impact characteristics and that is provided with heating means that are protected against environmental influences. Said aim is achieved in that an electrical heating layer is provided between at least two metal layers, which heating layer is electrically insulated with respect to said metal layers.
  • the laminate according to the invention consists of alternating metal layers and plastic layers and consequently has good mechanical properties. Electrical heating means are also embedded in the interior of the laminate, preferably as close as possible to the outer layer. Electrical insulation of the heating means with respect to the adjacent metal layers can be obtained by means of two electrically insulating layers. These electrically insulating layers can also be the plastic adhesive layers, which, after all, already form part of the standard laminate.
  • a layer with thermal barrier characteristics for example, consisting of glass or epoxy, can be on the inside of the heatable layer.
  • the heating energy can consequently be directed mainly at the outer metal layer where icing can occur.
  • the heating layer can be implemented in various ways. According to a first possibility, this can comprise a resistance foil. According to an alternative embodiment, the heating layer can comprise a woven layer in which there are resistance wires.
  • the laminate can also be constructed in various ways, for example with plastic adhesive layers which each comprise at least one fibre-reinforced layer (FML), or with plastic adhesive layers which each comprise at least one layer of adhesive (AML).
  • the fibre-reinforced layers can comprise polymer fibres or ceramic fibres such as glass.
  • the layer of adhesive can comprise epoxy, PUR, PE, PEI or PMMA.
  • the heating layer can contain a heating element that is incorporated in such a layer of adhesive.
  • the metal layers preferably comprise aluminium, the thickness of which can be between, or can be equal to, 0.3 and 0.5 mm.
  • the thickness of the plastic layers can be between, or equal to, 0.1 and 0.3 mm.
  • the invention also relates to an external component for an aircraft or spacecraft.
  • the component concerned can be, for example, the leading edge for a wing or for the tail piece of an aircraft.
  • the invention also relates to components such as an inlet piece for a motor or an air feed. All such components are found in those regions of an aircraft or spacecraft that are directly exposed to air flows impinging thereon and that therefore are susceptible to icing. According to the invention, such components are provided with the laminate according to the invention.
  • the laminate can also be applied to a support consisting of a relatively thick sheet metal, such as aluminium.
  • the invention relates to the use of the laminate as described above for such an external component of an aircraft or spacecraft. It will be clear that many different conceivable variants in the stacking of the various layers are conceivable. That is to say metal layers, layers of adhesive, electrically insulating layers and heating layers.
  • M metal layer
  • E electrically insulating layer
  • a layer of adhesive T layer with thermal barrier characteristics, which optionally can comprise an adhesive
  • the examples can be represented as follows (the heating layer always being close to the outside): 1.
  • MFFMFFMFFEWEM M K M K M K W E M 5.
  • Figure 1 shows a section through the leading edge of a wing.
  • Figure 2 shows detail II from Figure 1 on an enlarged scale.
  • the leading edge of a wing which is indicated in its entirety by 10, is shown in cross-section.
  • the leading edge of a wing adjoins two panels 11,12 and is fixed thereto by means of fixing means known per se, which are not shown in more detail.
  • the leading edge of the wing consists of a curved laminate that is shown in section on a larger scale in Figure 2.
  • the laminate comprises metal layers, in particular aluminium layers 1, as well as plastic adhesive layers 2 located between the metal layers.
  • these plastic adhesive layers consist of fibre-reinforced plastic layers 3, 4, which are oriented at 90° with respect to one another (prepreg).
  • This can be, for example, an aluminium resistance foil, a woven layer with resistance wires incorporated therein, etc.
  • an electrical insulation layer 8 which, for example, can also be a fibre-reinforced plastic adhesive layer, between the heating layer 7 and the outer aluminium layer 1.
  • an insulation layer 9 can be provided on the inside of the heating layer 7.
  • a supplementary thermal insulation layer 9 is that the heat mainly reaches the outer aluminium layer 1, which is susceptible to icing.

Abstract

A laminate consisting of alternating metal layers (1) and plastic adhesive layers (2) located between the metal layers (1) for the production of structural parts such as panels that can be used in aviation and/or aerospace is characterised in that an electrical heating layer (7) is provided between at least two metal layers (1), which heating layer (7) is electrically insulated with respect to said metal layers. The heating layer is incorporated between two electrically insulating layers (8).

Description

Laminate with heating element
The invention relates to a laminate consisting of alternating metal layers and plastic adhesive layers located between the metal layers for the production of structural parts such as panels that can be used in aviation and/or aerospace. Such laminates are known and are used in panels for various components of the load-bearing aircraft construction. Examples are the skin panels for the aircraft body and the wing panels for the aircraft wings. Panels that consist of a laminate have substantial advantages compared with completely metal panels, such as aluminium panels. First of all, the weight of panels consisting of a laminate having otherwise equal strength and rigidity is lower than that of panels consisting wholly of aluminium. Furthermore, the fatigue characteristics of such laminates are much more advantageous. Any cracks in the metal layers are stopped by the adjacent plastic layers, such that no further crack growth will occur even under fluctuating loads. Another advantage of such laminates lies in the good ability to withstand collisions. This characteristic is particularly important in the case of use in the leading edges of the wings and the tail and of the skin panels of moving wing and tail components. The problem of icing can arise with certain panels of the aircraft construction. In particular, ice growth at the leading edge of the wing is dangerous. Such ice growth influences the flow of air over the wing, such that the load bearing capacity of the wing can decrease sharply. In order to counteract this phenomenon, the leading edge of the wings is frequently provided with anti-icing means. These can both prevent the formation of ice and also contribute to the removal of ice that has already grown. In the case of panels that consist of laminates it is known to glue a heatable film on the leading edge. An example of this technique is given in WO-A 03038841. A further example is disclosed in WO-A 0108463. With this technique an electrically insulating layer and then a heatable graphite film are glued onto a panel that consists of a fibre- reinforced plastic. According to an alternative embodiment, the graphite film can also be embedded in the fibre-reinforced plastic laminate. A thermally conducting layer, which is close to or in contact with the graphite film, is applied to the outside of the composite. A disadvantage of these known heatable laminates is that the heatable and/or the thermally conducting layer that is on the outer surface produces additional resistance. This leads to a higher fuel consumption. The aim of the invention is, therefore, to provide a laminate that has a high structural rigidity and strength in combination with good collision or impact characteristics and that is provided with heating means that are protected against environmental influences. Said aim is achieved in that an electrical heating layer is provided between at least two metal layers, which heating layer is electrically insulated with respect to said metal layers. The laminate according to the invention consists of alternating metal layers and plastic layers and consequently has good mechanical properties. Electrical heating means are also embedded in the interior of the laminate, preferably as close as possible to the outer layer. Electrical insulation of the heating means with respect to the adjacent metal layers can be obtained by means of two electrically insulating layers. These electrically insulating layers can also be the plastic adhesive layers, which, after all, already form part of the standard laminate. A layer with thermal barrier characteristics, for example, consisting of glass or epoxy, can be on the inside of the heatable layer. The heating energy can consequently be directed mainly at the outer metal layer where icing can occur. The heating layer can be implemented in various ways. According to a first possibility, this can comprise a resistance foil. According to an alternative embodiment, the heating layer can comprise a woven layer in which there are resistance wires. The laminate can also be constructed in various ways, for example with plastic adhesive layers which each comprise at least one fibre-reinforced layer (FML), or with plastic adhesive layers which each comprise at least one layer of adhesive (AML). The fibre-reinforced layers can comprise polymer fibres or ceramic fibres such as glass. The layer of adhesive can comprise epoxy, PUR, PE, PEI or PMMA. The heating layer can contain a heating element that is incorporated in such a layer of adhesive. The metal layers preferably comprise aluminium, the thickness of which can be between, or can be equal to, 0.3 and 0.5 mm. The thickness of the plastic layers can be between, or equal to, 0.1 and 0.3 mm. The invention also relates to an external component for an aircraft or spacecraft. The component concerned can be, for example, the leading edge for a wing or for the tail piece of an aircraft. The invention also relates to components such as an inlet piece for a motor or an air feed. All such components are found in those regions of an aircraft or spacecraft that are directly exposed to air flows impinging thereon and that therefore are susceptible to icing. According to the invention, such components are provided with the laminate according to the invention. In addition, the laminate can also be applied to a support consisting of a relatively thick sheet metal, such as aluminium. Finally, the invention relates to the use of the laminate as described above for such an external component of an aircraft or spacecraft. It will be clear that many different conceivable variants in the stacking of the various layers are conceivable. That is to say metal layers, layers of adhesive, electrically insulating layers and heating layers. The following stacks are mentioned as non-limiting examples, on the basis of the following letters: M = metal layer K = plastic layer F = fibre layer impregnated with plastic FF = adjacent fibre layers impregnated with plastic, optionally with different fibre orientation E = electrically insulating layer, optionally a layer of adhesive T = layer with thermal barrier characteristics, which optionally can comprise an adhesive E/T = layer with combined electrical properties and thermal insulation properties, which optionally can comprise an adhesive W = heating layer. The examples can be represented as follows (the heating layer always being close to the outside): 1. MKMKMKEWEM 2. MFMFMFEWEM 3. MFFMFFMFFEWEM 4. M K M K M K W E M 5. M F M F M F W E M 6. M FF M FF M FF W E M 7. M FF M FF M FF E W E M 8. M FF M FF M F E W E F M 9. MFFMFFMFWFM 10. MKMKTMKWEM 11. MFMFTMFWEM 12. MKMKMKTEWEM 13. MKMKMKE/TWEM 14. MKMKME/TWEM 15. MKMKMKWKM 17. MFFMFFMFFWKM. The invention will be explained in more detail below with reference to an illustrative embodiment shown in the figures. Figure 1 shows a section through the leading edge of a wing. Figure 2 shows detail II from Figure 1 on an enlarged scale. In Figure 1 the leading edge of a wing, which is indicated in its entirety by 10, is shown in cross-section. This leading edge of a wing adjoins two panels 11,12 and is fixed thereto by means of fixing means known per se, which are not shown in more detail. The leading edge of the wing consists of a curved laminate that is shown in section on a larger scale in Figure 2. The laminate comprises metal layers, in particular aluminium layers 1, as well as plastic adhesive layers 2 located between the metal layers. In the illustrative embodiment shown, these plastic adhesive layers consist of fibre-reinforced plastic layers 3, 4, which are oriented at 90° with respect to one another (prepreg). When the laminate shown in the figure is used in a panel for an aircraft, for example the leading end of a wing, one of the aluminium layers is on the outside 5, whilst the other aluminium layer 1 is located on the inside 6. A heating layer 7 is arranged close to the aluminium layer 1 that is on the outside.
This can be, for example, an aluminium resistance foil, a woven layer with resistance wires incorporated therein, etc. There is an electrical insulation layer 8, which, for example, can also be a fibre-reinforced plastic adhesive layer, between the heating layer 7 and the outer aluminium layer 1. Finally, an insulation layer 9 can be provided on the inside of the heating layer 7.
This is not actually necessary because the adjacent plastic adhesive layer 2 already has an electrically insulating effect. However, the advantage of a supplementary thermal insulation layer 9 is that the heat mainly reaches the outer aluminium layer 1, which is susceptible to icing.

Claims

Claims
1. Laminate consisting of alternating metal layers (1) and plastic adhesive layers (2) located between the metal layers (1) for the production of structural parts such as panels that can be used in aviation and/or aerospace, characterised in that an electrical heating layer (7) is provided between at least two metal layers (1), which heating layer is electrically insulated with respect to said metal layers (1).
2. Laminate according to Claim 1, wherein the heating layer (7) is incorporated between two electrically insulating layers (8, 9).
3. Laminate according to Claim 2, wherein at least one of the electrically insulating layers is a plastic adhesive layer (2).
4. Laminate according to one of the preceding claims, wherein a layer with thermal barrier characteristics (9) is provided.
5. Laminate according to Claim 4, wherein the layer (9) with thermal barrier characteristics is also electrically insulating.
6. Laminate according to Claim 4 or 5, wherein the layer with thermal barrier characteristics (9) comprises glass or epoxy.
7. Laminate according to one of the preceding claims, wherein the heating layer (7) is between an outer metal layer (1) and the metal layer (1) immediately following said outer metal layer.
8. Laminate according to Claim 7, wherein there is a layer (9) with thermal barrier characteristics between the heating layer (7) and the following metal layer (1).
9. Laminate according to one of the preceding claims, wherein the heating layer (7) comprises a resistance foil.
10. Laminate according to one of the preceding claims, wherein the heating layer (7) comprises a woven layer in which resistance wires are present.
11. Laminate according to one of the preceding claims, wherein the heating layer (7) comprises a copper, aluminium or carbon mat or wire with a thickness of 0.05 to
0.2 mm.
12. Laminate according to one of the according to preceding claims, wherein the plastic adhesive layers (2) each comprise at least one fibre-reinforced layer (FML).
13. Laminate according to Claim 12, wherein the fibre-reinforced layer comprises polymer fibres or ceramic fibres, such as glass.
14. Laminate according to one of the preceding claims, wherein the plastic adhesive layers (2) each at least comprise one layer of adhesive (AML).
15. Laminate according to Claim 14, wherein the layer of adhesive comprises epoxy, PUR, PE, PEI or PMMA.
16. Laminate according to one of the preceding claims, wherein the metal layers (1) comprise aluminium.
17. Laminate according to one of the following (sic) claims, wherein the thickness of the metal layers (1) is between, or is equal to, 0.3 and 0.5 mm.
18. Laminate according to one of the preceding claims, wherein the thickness of the plastic layers is between, or is equal to, 0.1 and 0.3 mm.
19. Laminate according to one of the preceding claims, wherein the heating layer (7) comprises a heating element that is incorporated in a layer of adhesive.
20. External component for an aircraft or spacecraft, such as a leading edge for a wing or tail piece and the like, an inlet piece for a motor or air feed and the like, comprising a laminate according to one of the preceding claims consisting of alternating metal layers (1) and plastic adhesive layers (2) located between the metal layers (1), characterised in that an electrical heating layer (7) is provided between at least two metal layers (1), which heating layer is electrically insulated with respect to said metal layers (1).
21. Component according to Claim 20, having a support consisting of relatively thick sheet metal, for example aluminium, wherein the laminate is fixed to the support.
22. Use of a laminate according to one of Claims 1 - 19 for an external component of an aircraft or spacecraft, such as a leading edge for a wing or tail piece and the like, an inlet for a motor or air feed and the like.
PCT/NL2005/000201 2004-03-16 2005-03-16 Laminate with heating element WO2005087589A1 (en)

Applications Claiming Priority (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
NL1025744 2004-03-16

Publications (1)

Publication Number Publication Date
WO2005087589A1 true WO2005087589A1 (en) 2005-09-22

Family

ID=32822970

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/NL2005/000201 WO2005087589A1 (en) 2004-03-16 2005-03-16 Laminate with heating element

Country Status (2)

Country Link
NL (1) NL1025744C2 (en)
WO (1) WO2005087589A1 (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007071398A1 (en) * 2005-12-20 2007-06-28 Airbus Deutschland Gmbh Protection device
FR2898868A1 (en) * 2006-03-24 2007-09-28 Aircelle Sa Lip structure for air intake nozzle of jet engine, has heating electric element connected to power supply, where heating electric element is situated between internal skin and external skin of structure
WO2010074942A1 (en) 2008-12-24 2010-07-01 Mra Systems, Inc. Anti-icing system and method for preventing ice accumulation
WO2011157953A1 (en) * 2010-06-18 2011-12-22 Snecma Air inlet duct for a turbojet nacelle
EP2591476A2 (en) * 2010-07-11 2013-05-15 Advanced Logistics Development Ltd. A composite material, a structural element comprised of the composite material, an airplane wing spar and their methods of production
US9267715B2 (en) 2012-02-03 2016-02-23 Airbus Operations Gmbh Icing protection system for an aircraft and method for operating an icing protection system
EP3006189A1 (en) * 2014-10-09 2016-04-13 The Boeing Company Composite structures having composite-to-metal joints and methods for making the same
US9522512B2 (en) 2010-08-17 2016-12-20 The Boeing Company Methods for making composite structures having composite-to-metal joints
US10112373B2 (en) 2010-08-17 2018-10-30 The Boeing Company Multi-layer metallic structure and composite-to-metal joint methods
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)

* Cited by examiner, † Cited by third party
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

Patent Citations (8)

* Cited by examiner, † Cited by third party
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

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007071398A1 (en) * 2005-12-20 2007-06-28 Airbus Deutschland Gmbh Protection device
FR2898868A1 (en) * 2006-03-24 2007-09-28 Aircelle Sa Lip structure for air intake nozzle of jet engine, has heating electric element connected to power supply, where heating electric element is situated between internal skin and external skin of structure
WO2007110494A1 (en) * 2006-03-24 2007-10-04 Aircelle Structure for an air inlet lip of an electric de-icing pod comprising an acoustic attenuation zone
US8240982B2 (en) 2006-03-24 2012-08-14 Aircelle Structure for an air inlet lip of an electric de-icing pod comprising an acoustic attenuation zone
WO2010074942A1 (en) 2008-12-24 2010-07-01 Mra Systems, Inc. Anti-icing system and method for preventing ice accumulation
JP2012513934A (en) * 2008-12-24 2012-06-21 エムアールエイ・システムズ・インコーポレイテッド Anti-icing system and method for preventing ice accumulation
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
WO2011157953A1 (en) * 2010-06-18 2011-12-22 Snecma Air inlet duct for a turbojet nacelle
FR2961484A1 (en) * 2010-06-18 2011-12-23 Snecma AIR INLET HANDLE FOR TURBOREACTOR NACELLE
GB2494843A (en) * 2010-06-18 2013-03-20 Snecma Air inlet duct for a turbojet nacelle
EP2591476A4 (en) * 2010-07-11 2014-11-19 Advanced Logistics Dev Ltd A composite material, a structural element comprised of the composite material, an airplane wing spar and their methods of production
EP2591476A2 (en) * 2010-07-11 2013-05-15 Advanced Logistics Development Ltd. A composite material, a structural element comprised of the composite material, an airplane wing spar and their methods of production
US9522512B2 (en) 2010-08-17 2016-12-20 The Boeing Company Methods for making composite structures having composite-to-metal joints
US9919507B2 (en) 2010-08-17 2018-03-20 The Boeing Company Process for inhibiting galvanic corrosion of an aluminum structure connected, without using a splice plate, to a composite structure having a fiber including graphite
US10112373B2 (en) 2010-08-17 2018-10-30 The Boeing Company Multi-layer metallic structure and composite-to-metal joint methods
US11084269B2 (en) 2010-08-17 2021-08-10 The Boeing Company Multi-layer metallic structure and composite-to-metal joint methods
US9267715B2 (en) 2012-02-03 2016-02-23 Airbus Operations Gmbh Icing protection system for an aircraft and method for operating an icing protection system
EP3006189A1 (en) * 2014-10-09 2016-04-13 The Boeing Company Composite structures having composite-to-metal joints and methods for making the same
CN105501428A (en) * 2014-10-09 2016-04-20 波音公司 Composite structure having composite-to-metal joints and method for making same
CN105501428B (en) * 2014-10-09 2020-06-30 波音公司 Composite structure with composite-to-metal joint and method of making the same
US11952130B2 (en) 2020-03-27 2024-04-09 Airbus Operations Gmbh Structural component for an aircraft with integrated heating layer and structural battery

Also Published As

Publication number Publication date
NL1025744A1 (en) 2004-05-27
NL1025744C2 (en) 2005-01-18

Similar Documents

Publication Publication Date Title
WO2005087589A1 (en) Laminate with heating element
US9751612B2 (en) Multifunctional composite material including a viscoelastic interlayer
EP3339013B1 (en) Heated floor panels with thermally conductive and electrically insulating fabric
EP2523854B1 (en) Multifunctional de-icing/anti-icing system
EP3297395B1 (en) Thermally conductive, electrically insulating protection layer for de-icing heaters
US10343372B2 (en) Composite article having multifunctional properties and method for its manufacture
EP2419326B1 (en) Lightning protection sheet with patterned discriminator
US20190135442A1 (en) Heating Device and Method for Manufacturing Same
US11338933B2 (en) Acoustic honeycomb panel with integrated electrical heater
US10960966B2 (en) Cabin structural component, method for producing a cabin structural component, cabin assembly and transport vehicle
US20120292439A1 (en) Article with de-icing/anti-icing function
US11130559B2 (en) Heated panels with ballistic structures
EP3342702B1 (en) Erosion strip integrated with carbon allotrope-based deicing/anti-icing elements
JP2000356358A (en) Plate structural member of floor surface plate particularly for aircraft
CN103569364A (en) Electric heater for integration into an aircraft acoustic panel
CA3048075A1 (en) Advanced composite heated floor panel
US20130122245A1 (en) Embedded conductor honeycomb core and sandwich panel incorporating same
EP3407678A1 (en) Method of making complex carbon nanotube sheets
CA3040698A1 (en) Structural component for an aircraft
EP3297394B1 (en) Nano alumina fabric protection ply for de-icers
US9072184B2 (en) Carbon fiber spacecraft panel with integral metallic foil power return
EP4108572B1 (en) Aircraft feature with heating system formed of laser-induced graphene
EP3725669A1 (en) Edge damage tolerant heated and unheated composite panels with rotated honeycomb edge pieces
CN114056544A (en) Skin structure for a wing, aircraft with a skin structure and method for mounting a skin structure

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SM SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): BW GH GM KE LS MW MZ NA SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LT LU MC NL PL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
DPEN Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed from 20040101)
NENP Non-entry into the national phase

Ref country code: DE

WWW Wipo information: withdrawn in national office

Country of ref document: DE

122 Ep: pct application non-entry in european phase