EP0771285A1 - Heating element - Google Patents

Heating element

Info

Publication number
EP0771285A1
EP0771285A1 EP95925928A EP95925928A EP0771285A1 EP 0771285 A1 EP0771285 A1 EP 0771285A1 EP 95925928 A EP95925928 A EP 95925928A EP 95925928 A EP95925928 A EP 95925928A EP 0771285 A1 EP0771285 A1 EP 0771285A1
Authority
EP
European Patent Office
Prior art keywords
mat
heating element
propeller blade
blade according
propeller
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
EP95925928A
Other languages
German (de)
French (fr)
Inventor
Roy Frederick John Withyholt Cottage McCARTHY
Paul Desmond Barnfield
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Smiths Aerospace Gloucester Ltd
Original Assignee
Smiths Aerospace Gloucester Ltd
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 Smiths Aerospace Gloucester Ltd filed Critical Smiths Aerospace Gloucester Ltd
Publication of EP0771285A1 publication Critical patent/EP0771285A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • H05B3/34—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs
    • H05B3/36—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • 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
    • H05B2203/00—Aspects relating to Ohmic resistive heating covered by group H05B3/00
    • H05B2203/013—Heaters using resistive films or coatings
    • 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
    • H05B2203/00—Aspects relating to Ohmic resistive heating covered by group H05B3/00
    • H05B2203/017—Manufacturing methods or apparatus for heaters

Definitions

  • the present invention relates to heating elements for propeller blades, a method of forming heating elements, and a method of fastening a heating element to apparatus such as a propeller blade.
  • the present invention in its first aspect provides a propeller blade having an electrically powered heating element, the heating element comprising a mat of fibres having surfaces which are electrically conductive.
  • the fibres can be electrically conductive throughout, and are preferably carbon fibres.
  • the fibres can be metal coated. The metal coating of the fibres is preferably of nickel.
  • the fibre mat has the advantage of being more damage tolerant compared with conventional zig-zagged wire heaters. Whereas a small hole in the region where wire is laid out leads to a break of the connection and total heating failure, a hole in a heating element according to the present invention merely results in a changed current path. This is a significant practical advantage in view of the relative likelihood of the front edges of propeller blades being damaged. Furthermore, holes can be intentionally cut in a fibre mat so as to adapt the distribution of heat which the mat provides.
  • Preferred heating elements according to the present invention also have the advantage that they can be made significantly thinner than the wire and rubber layers known in the prior art.
  • the preferred heating element can be fitted directly on a blade without such indentations and still have low air resistance.
  • the mat of the heating element can be made up of more than one mat portion.
  • the portions can be shaped to fit respective sides of a propeller blade adjacent the leading edge of the blade, or the mat or mat portions can be wrapped over the blade leading edge.
  • the mat or mat portions can cover substantially all of the blade surfaces, this being especially suitable for anti-icing rather than de-icing operation.
  • the mat portions can be connected in series or parallel, or could be continuous so as to constitute a single mat. Multiple mats or mat portions can be provided one over another, so as to form a composite. Furthermore, if a mat or mat portion becomes damaged, a repair can be made by simply fixing another mat or mat portion over the top of the first, so as to be electrically connected to the first.
  • the heating element can be adapted to produce an optimum heat distribution pattern.
  • the mat or mat portions of the heating element can be shaped so as to have variable resistivity along their length.
  • dimensions such as length, width, and thickness can be varied, and gaps or holes provided in mats or mat portions.
  • the heating element can include a resilient cover such as a polyurethane layer.
  • the present invention in its second aspect relates to a heating element comprising a fibre mat in which at least the surfaces of the fibres are electrically conductive, the mat being backed by a perforated backing, the mat being fixed to the backing by film adhesive.
  • the backing acts either to control the flow of adhesive to the mat and/or to absorb excess adhesive so as to provide a heating element with bonded layers in which the fibres of the mat have not become substantially separated by the adhesive.
  • the backing is preferably glass fibre filter paper.
  • Film adhesive is preferably a resin.
  • the heating element can be mounted on a propeller blade such that the perforated backing is towards the blade surface.
  • the perforated backing can then electrically insulate the fibre mat from the blade.
  • the perforated backing preferably provides strength and stability whilst allowing the heating element to be flexible for fitting to the surface of apparatus to be heated. In particular, it is suitable for fitting to an aircraft propeller blade.
  • the present invention in a third aspect is a method of producing a heating element by providing a fibre mat with a perforated backing, applying film adhesive to the surface of the fibre mat or backing, and curing to fuse the adhesive so as to bond the paper and mat.
  • the curing step preferably results in a heating element which is still flexible.
  • the resulting bonded element can then be applied to apparatus to be heated such as a propeller blade, and fixed thereto.
  • the present invention in its fourth aspect is a method of providing a heating element on an apparatus to be heated by applying a fibre mat with a perforated backing to the apparatus, at least a surface of the mat or a surface of backing being provided with a film adhesive, and curing to fuse the adhesive so as to bond the filter paper and fibre mat to each other and to the blade.
  • This can be done as a single curing step.
  • the curing can be done in two stages, first to bond the mat and paper, and secondly, to fix the resulting composite to the blade.
  • Figure 1 is a diagrammatic oblique view of a heating element applied to a propeller blade
  • Figure 2 is a diagrammatic oblique view of an alternative heating element
  • Figure 3 is a diagrammatic view illustrating the layered structure of the heating elements.
  • the heating element comprises two mats 1,2.
  • the mats 1,2 are made of nickel coated carbon fibre.
  • the mats 1,2 are fixed to the propeller blade 12 adjacent a leading edge 14. In alternative embodiments, multiple mats could be provided one over the other.
  • the blade root of the propeller 4 includes two studs 5,6.
  • the studs 5,6 can be connected directly to mats 1,2 as shown in Figure 1, or via connecting wires 7,8 as shown in Figure 2.
  • One stud 5 is positive, whilst the other stud 6 is negative.
  • power is supplied to the mats 1,2 via the studs 5,6 by way of bus bars 9,10 fastened to the mats 1,2.
  • the two mats 1,2 are connected together near the tip of the propeller blade 12 via a further bus bar 16.
  • Multiple mats 1,2 can be laid one over the other so as to provide additional heating. Alternatively, they could be replaced by a single continuous layer or composite of multiple continuous layers.
  • the geometry of the mats 1,2 can be optimised so as to provide a preferred heating pattern. In particular, holes can be made in the mat for this purpose.
  • the heating element consists of nickel coated carbon fibre mats 1,2 backed by glass fibre filter paper 18.
  • a fibre mat and filter paper backing are fastened together using a resin 20 such as a polyurethane resin.
  • the resin 20 is preferably applied to the outwardly directed surface of the filter paper, then the mat and filter paper are keyed together by curing the resin 20.
  • the perforations through the weave of the filter paper acts to soak up excess resin, avoiding excessive resin between the fibres of the fibre mat. Some resin soaks into the mat providing some protection and giving rise to a small reduction in resistivity as fibres move apart. The resulting composite is still flexible.
  • the composite is fitted onto a propeller blade 12 preferably with the filter paper 18 toward the blade 12.
  • the composite is further cured under applied pressure so as to fasten the heating element to the blade.
  • the pressure can be supplied by covering the composite with a flexible membrane so as to define an enclosed space then causing a vacuum in that space, so that the membrane presses the composite.
  • the present invention provides a simple yet robust heating element which can be produced and/or applied to apparatus to be heated in a simple and effective way.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Surface Heating Bodies (AREA)
  • Laminated Bodies (AREA)

Abstract

An electrically powered heating element (1, 2) for a propeller blade is made up of a mat of fibres having at least surfaces which are electrically conductive. The mat can have a perforated backing to which it is fixed by adhesive. Methods of producing the heating element and fixing the heating element to a propeller blade involve a curing step for bonding the mat and backing using the adhesive.

Description

HEATING ELEMENT
The present invention relates to heating elements for propeller blades, a method of forming heating elements, and a method of fastening a heating element to apparatus such as a propeller blade.
The need to prevent the build-up of ice on an aircraft in flight has been exercising aeronautical engineers for many years. It is particularly important to prevent ice building up on aircraft propellers. If allowed to form on a propeller, ice does not form uniformly causing the propeller to become unbalanced. This leads to vibrations as the propeller rotates, resulting in possible gear box failures and other dangers. Furthermore, the build-up of ice on a propeller causes loss of thrust, so the performance of the aircraft is affected adversely. Ice can be shed, causing damage to other parts of the aircraft.
Many techniques to avoid the build-up of ice have been tried over the years, including mechanical, electrical, thermal, and vibratory methods. None has proved entirely satisfactory. One disadvantage is that the extra equipment required for de-icing tends to increase the bulk of a propeller blade causing aerodynamic inefficiency. Other disadvantages are a tendency for the de-icing equipment to wear, fatigue and become damaged.
Also, conventional de-icing equipment is often difficult to repair on the aircraft whilst in service. It is known to provide propeller blades with heating elements along their front edges where a heating element consists of a long wire which is laid out in a zig-zag configuration over the area to be heated. The wire is then covered with a rubber layer. Such a known heating element is easily damaged, as a single break in the wire is sufficient to make the heating element inoperable. Furthermore, the wire and rubber layer gives the front edge of the blade a raised profile causing reduced efficiency.
The present invention is defined in the claims to which reference should now be made. Preferred features are referred to in the sub claims.
The present invention in its first aspect provides a propeller blade having an electrically powered heating element, the heating element comprising a mat of fibres having surfaces which are electrically conductive. The fibres can be electrically conductive throughout, and are preferably carbon fibres. The fibres can be metal coated. The metal coating of the fibres is preferably of nickel.
The fibre mat has the advantage of being more damage tolerant compared with conventional zig-zagged wire heaters. Whereas a small hole in the region where wire is laid out leads to a break of the connection and total heating failure, a hole in a heating element according to the present invention merely results in a changed current path. This is a significant practical advantage in view of the relative likelihood of the front edges of propeller blades being damaged. Furthermore, holes can be intentionally cut in a fibre mat so as to adapt the distribution of heat which the mat provides.
Preferred heating elements according to the present invention also have the advantage that they can be made significantly thinner than the wire and rubber layers known in the prior art. Thus, whereas the known solution requires blades to be formed with indentations into which the layers fit, the preferred heating element can be fitted directly on a blade without such indentations and still have low air resistance.
The mat of the heating element can be made up of more than one mat portion. The portions can be shaped to fit respective sides of a propeller blade adjacent the leading edge of the blade, or the mat or mat portions can be wrapped over the blade leading edge. Alternatively, the mat or mat portions can cover substantially all of the blade surfaces, this being especially suitable for anti-icing rather than de-icing operation. The mat portions can be connected in series or parallel, or could be continuous so as to constitute a single mat. Multiple mats or mat portions can be provided one over another, so as to form a composite. Furthermore, if a mat or mat portion becomes damaged, a repair can be made by simply fixing another mat or mat portion over the top of the first, so as to be electrically connected to the first.
The heating element can be adapted to produce an optimum heat distribution pattern. The mat or mat portions of the heating element can be shaped so as to have variable resistivity along their length. To vary the heating pattern, dimensions such as length, width, and thickness can be varied, and gaps or holes provided in mats or mat portions.
The heating element can include a resilient cover such as a polyurethane layer.
The present invention in its second aspect relates to a heating element comprising a fibre mat in which at least the surfaces of the fibres are electrically conductive, the mat being backed by a perforated backing, the mat being fixed to the backing by film adhesive. The backing acts either to control the flow of adhesive to the mat and/or to absorb excess adhesive so as to provide a heating element with bonded layers in which the fibres of the mat have not become substantially separated by the adhesive. The backing is preferably glass fibre filter paper. Film adhesive is preferably a resin.
The heating element can be mounted on a propeller blade such that the perforated backing is towards the blade surface. The perforated backing can then electrically insulate the fibre mat from the blade.
The perforated backing preferably provides strength and stability whilst allowing the heating element to be flexible for fitting to the surface of apparatus to be heated. In particular, it is suitable for fitting to an aircraft propeller blade.
The present invention in a third aspect is a method of producing a heating element by providing a fibre mat with a perforated backing, applying film adhesive to the surface of the fibre mat or backing, and curing to fuse the adhesive so as to bond the paper and mat. The curing step preferably results in a heating element which is still flexible. The resulting bonded element can then be applied to apparatus to be heated such as a propeller blade, and fixed thereto.
The present invention in its fourth aspect is a method of providing a heating element on an apparatus to be heated by applying a fibre mat with a perforated backing to the apparatus, at least a surface of the mat or a surface of backing being provided with a film adhesive, and curing to fuse the adhesive so as to bond the filter paper and fibre mat to each other and to the blade. This can be done as a single curing step. Alternatively, the curing can be done in two stages, first to bond the mat and paper, and secondly, to fix the resulting composite to the blade.
A preferred embodiment of the present invention will now be described by way of example, and with reference to the drawings in which:
Figure 1 is a diagrammatic oblique view of a heating element applied to a propeller blade; Figure 2 is a diagrammatic oblique view of an alternative heating element; and
Figure 3 is a diagrammatic view illustrating the layered structure of the heating elements.
As shown in Figure 1, the heating element comprises two mats 1,2. The mats 1,2 are made of nickel coated carbon fibre. The mats 1,2 are fixed to the propeller blade 12 adjacent a leading edge 14. In alternative embodiments, multiple mats could be provided one over the other. The blade root of the propeller 4 includes two studs 5,6. The studs 5,6 can be connected directly to mats 1,2 as shown in Figure 1, or via connecting wires 7,8 as shown in Figure 2. One stud 5 is positive, whilst the other stud 6 is negative. To provide heat, power is supplied to the mats 1,2 via the studs 5,6 by way of bus bars 9,10 fastened to the mats 1,2. The two mats 1,2 are connected together near the tip of the propeller blade 12 via a further bus bar 16.
Multiple mats 1,2 can be laid one over the other so as to provide additional heating. Alternatively, they could be replaced by a single continuous layer or composite of multiple continuous layers.
The geometry of the mats 1,2 can be optimised so as to provide a preferred heating pattern. In particular, holes can be made in the mat for this purpose. The heating element consists of nickel coated carbon fibre mats 1,2 backed by glass fibre filter paper 18. A fibre mat and filter paper backing are fastened together using a resin 20 such as a polyurethane resin. The resin 20 is preferably applied to the outwardly directed surface of the filter paper, then the mat and filter paper are keyed together by curing the resin 20. Basically, the perforations through the weave of the filter paper acts to soak up excess resin, avoiding excessive resin between the fibres of the fibre mat. Some resin soaks into the mat providing some protection and giving rise to a small reduction in resistivity as fibres move apart. The resulting composite is still flexible.
The layers of the preferred heating element before curing are shown in Figure 3. Upon curing, the resin layer 20 fuses, seeping through the filter paper 18 so as to bond the filter paper 18 to a mat 1,2.
The composite is fitted onto a propeller blade 12 preferably with the filter paper 18 toward the blade 12. The composite is further cured under applied pressure so as to fasten the heating element to the blade. The pressure can be supplied by covering the composite with a flexible membrane so as to define an enclosed space then causing a vacuum in that space, so that the membrane presses the composite.
An alternative approach is to apply the filter paper to the blade then a fibre mat, then resin layer, over the top. Another option is to apply a resin layer to the blade then cover, first with the fibre mat, then the filter paper. In both cases, the order of applying the filter paper and fibre mat could be swapped around. Using any of these various approaches, a single curing step is sufficient to produce a blade with a heating element bonded to the blade and ready for use.
The present invention provides a simple yet robust heating element which can be produced and/or applied to apparatus to be heated in a simple and effective way.

Claims

1. A propeller blade having an electrically powered heating element, the heating element comprising a mat of fibres having surfaces which are electrically conductive.
2. A propeller blade according to claim 1, in which the fibres are electrically conductive throughout.
3. A propeller blade according to claim 1 or claim 2, in which the fibres are carbon fibres.
4. A propeller blade according to any preceding claim, in which the fibres are metal coated.
5. A propeller blade according to claim 4, in which the metal coating of the fibres is of nickel.
6. A propeller blade according to any preceding claim, in which the mat has holes cut therein to adapt the distribution of heat which the mat provides in use.
7. A propeller according to any preceding claim, in which the mat is shaped to fit sides of the propeller blade adjacent the leading edge of the blade.
8. A propeller blade according to any preceding claim, in which the mat is wrapped over the blade leading edge.
9. A propeller blade according to any preceding claim, in which the mat covers substantially all of the blade surfaces.
10. A propeller blade according to any preceding claim, in which multiple mats are provided one over another so as to form a composite.
11. A propeller blade according to any preceding claim, in which if the mat is damaged, a repair is made by fixing another mat over the top so as to be electrically connected thereto.
12. A propeller according to any preceding claim, in which the mat is dimensioned to provide a predetermined heating pattern.
13. A propeller blade according to claim 12, in which the mat is shaped so as to have variable resistivity along its length to provide the predetermined heating pattern.
14. A propeller blade according to any preceding claim, in which the mat has gaps or holes to provide a predetermined heating pattern.
15. A propeller blade according to any preceding claim, in which the mat of the heating element is made up of more than one mat portion.
16. A propeller blade according to claim 16, in which the portions are shaped to fit respective sides of a propeller blade adjacent the leading edge of the blade.
17. A propeller blade according to claim 15 or claim 16, in which the mat portions are wrapped over the blade leading edge.
18. A propeller blade according to any of claims 15 to 17, in which the mat portions can together cover substantially all of the blade surfaces.
19. A propeller blade according to any of claims 15 to 18, in which the mat portions can be connected in series or parallel.
20. A propeller blade according to any of claims 15 to 19, in which multiple mat portions are provided one over another, so as to form a composite.
21. A propeller blade according to any of claims 15 to 20, in which if a mat or mat portion becomes damaged, a repair is made by simply fixing another mat or mat portion over the top of the first, so as to be electrically connected to the first.
22. A propeller blade according to any of claims 15 to 21, in which at least one mat portion is dimensioned to provide a predetermined heating pattern.
23. A propeller blade according to claim 22, in which at least one mat portion is shaped to have variable resistivity along its length to provide the predetermined heating pattern.
24. A propeller blade according to any of claims 15 to 23, in which at least one mat portion has gaps or holes to provide a predetermined heating pattern.
25. A propeller blade according to any preceding claim, in which the heating element includes a resilient cover.
26. A propeller blade according to claim 25, in which the resilient layer comprises a polyurethane layer.
27. A heating element comprising a fibre mat in which at least the surface of the fibres are electrically conductive, the mat being backed by a perforated backing, the mat being fixed to the backing by film adhesive.
28. A heating element according to claim 27, in which the backing acts either to control the flow of adhesive to the mat and/or to absorb excess adhesive so as to provide a heating element with bonded layers in which the fibres of the mat have not become substantially separated by the adhesive.
29. A heating element according to claim 27 or claim 28, in which the backing is glass fibre filter paper.
30. A heating element according to any of claims 27 to 29, in which the film adhesive is preferably a resin.
31. A heating element according to any of claims 27 to 30 mounted on an apparatus to be heated such that the perforated backing is towards the apparatus surface.
32. A heating element according to claim 31, in which the perforated backing electrically insulates the fibre mat from the apparatus.
33. A heating element according to claim 31 or claim 32, in which the apparatus is an aircraft propeller blade.
34. A method of producing a heating element by providing a fibre mat with a perforated backing, applying film adhesive to the surface of the fibre mat or backing, and curing to fuse the adhesive so as to bond the paper and mat.
35. A method of producing a heating element according to claim 34, in which the curing step preferably results in a heating element which is flexible.
36. A method of providing apparatus to be heated with a heating element including the method of producing a heating element according to claim 34 or claim 35, and fixing the resulting bonded element to the apparatus to be heated.
37. A method of providing a heating element on an apparatus to be heated by applying a fibre mat with a perforated backing to the apparatus, at least a surface of the mat or a surface of backing being provided with a film adhesive, and curing to fuse the adhesive so as to bond the filter paper and fibre mat to each other and to the apparatus.
38. A method of providing a heating element on an apparatus according to claim 37, in which curing is done as a single curing step.
39. A method of providing a heating element on an apparatus according to claim 37, in which the curing can be done in two stages, first to bond the mat and paper, and secondly, to fix the resulting composite to the blade.
EP95925928A 1994-07-21 1995-07-19 Heating element Withdrawn EP0771285A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB9414744A GB2291575A (en) 1994-07-21 1994-07-21 Heating element for aircraft surface.
GB9414744 1994-07-21
PCT/GB1995/001713 WO1996003316A1 (en) 1994-07-21 1995-07-19 Heating element

Publications (1)

Publication Number Publication Date
EP0771285A1 true EP0771285A1 (en) 1997-05-07

Family

ID=10758688

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95925928A Withdrawn EP0771285A1 (en) 1994-07-21 1995-07-19 Heating element

Country Status (3)

Country Link
EP (1) EP0771285A1 (en)
GB (1) GB2291575A (en)
WO (1) WO1996003316A1 (en)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2756253B1 (en) * 1996-11-27 1999-01-29 Eurocopter France RESISTIVE ELEMENTS FOR HEATING AN AERODYNAMIC PROFILE, AND DEVICE FOR HEATING AN AERODYNAMIC PROFILE INCORPORATING SUCH ELEMENTS
FR2756254B1 (en) * 1996-11-27 1999-01-29 Eurocopter France DEVICE FOR HEATING AN AERODYNAMIC PROFILE
DE10151298A1 (en) * 2001-10-17 2003-04-30 Joerg Runge-Rannow Multi-layer heating film and process for its production
US6753513B2 (en) * 2002-03-19 2004-06-22 Hamilton Sundstrand Propeller de-icing system
MX2007014660A (en) * 2005-05-27 2008-03-07 Bell Helicopter Textron Inc Strained capable conductive/resistive composite hybrid heater for thermal anti-ice device.
GB2433185B (en) * 2005-12-06 2011-08-10 Hotfoot Heated Membranes Ltd Heating element
US9793672B2 (en) 2011-03-16 2017-10-17 Gkn Aerospace Services Structures Corp. Composite laminate having a flexible circuit bridge and method of manufacture thereof
FR3068195B1 (en) 2017-06-27 2019-07-19 Airbus Helicopters METHOD FOR MANUFACTURING A ROTATING SAILING ROTATING EQUIPMENT WITH A DEFROSTER, SAID ROTATING EQUIPMENT AND A DRONE PROVIDED WITH SAID ROTATING EQUIPMENT
EP3708496B1 (en) * 2019-03-15 2023-11-29 Ratier-Figeac SAS Blade de-icing
US11427336B2 (en) * 2020-03-25 2022-08-30 Goodrich Corporation High strain tolerant chord-wise ice protection layout
GB2607884B (en) * 2021-06-11 2023-11-15 Ubiq Aerospace As System and method for deicing of a carbon composite propeller

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2707317A1 (en) * 1977-02-19 1978-08-24 Licentia Gmbh Resistance heating element for aircraft wings and helicopter blades - consists of mat of carbon or boron fibres and glass fibres
FR2356336A1 (en) * 1976-06-25 1978-01-20 Licentia Gmbh Resistance heating element for aircraft wings and helicopter blades - consists of mat of carbon or boron fibres and glass fibres
DE2628731C3 (en) * 1976-06-25 1981-03-26 Licentia Patent-Verwaltungs-Gmbh, 60596 Frankfurt Electric resistance heating element
GB2121745A (en) * 1982-06-17 1984-01-04 Westland Plc Aircraft de-icing apparatus
US4764665A (en) * 1985-07-02 1988-08-16 Material Concepts, Inc. Electrically heated gloves
ES2054494T3 (en) * 1990-01-24 1994-08-01 Hastings Otis ELECTRICALLY CONDUCTIVE LAMINATE FOR THE CONTROL OF SURFACE TEMPERATURE.

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9603316A1 *

Also Published As

Publication number Publication date
GB9414744D0 (en) 1994-09-07
GB2291575A (en) 1996-01-24
WO1996003316A1 (en) 1996-02-08

Similar Documents

Publication Publication Date Title
US5947418A (en) Device for heating an aerofoil
CA2290386C (en) Device and method for heating and deicing wind energy turbine blades
US6137083A (en) Device for heating an aerofoil
EP2330034A2 (en) Ice protection heater for an aircraft component
US6338455B1 (en) Heating device with resistive elements for an aerodynamic profile
JPH0747400B2 (en) Wing structure defroster
EP2528815B1 (en) Electrothermal heater mat
US5971323A (en) Resistive elements for heating an aerofoil, and device for heating an aerofoil incorporating such elements
EP3409588B1 (en) Electrical bus arrangement for ice protection systems
EP2528817B1 (en) Electrical apparatus for an electrothermal ice protection system
EP3450320B1 (en) Tailored rotor-blade ice-protection system
US5131812A (en) Aircraft engine propulsor blade deicing
US8807483B2 (en) Electrothermal heater mat
EP0771285A1 (en) Heating element
US3218436A (en) Electrical aircraft heater
WO2011092481A1 (en) Electrothermal heater
EP2528816B1 (en) Heater mat comprising dielectric component with electrical connection
US5144113A (en) Electrically heated deicer for aircraft blades
EP3407678A1 (en) Method of making complex carbon nanotube sheets
EP2868575B1 (en) Rotor blade with electrical interconnects
GB2121745A (en) Aircraft de-icing apparatus
US7064302B2 (en) Electrical connection for a resistor element made of electrically-conductive fibers
EP3869035B1 (en) Blade for a rotor of a wind turbine and manufacturing method thereof

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19970131

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): FR

17Q First examination report despatched

Effective date: 19970923

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 19980204