US2205543A - Heating surface - Google Patents

Heating surface Download PDF

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US2205543A
US2205543A US172286A US17228637A US2205543A US 2205543 A US2205543 A US 2205543A US 172286 A US172286 A US 172286A US 17228637 A US17228637 A US 17228637A US 2205543 A US2205543 A US 2205543A
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layer
wing
current
strips
heating
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US172286A
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Rideau Jean Robert
Ducret Andre Maxime
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    • 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

Definitions

  • the present invention 4 has for an object the construction of defrosting surfaces for aeroplanes in which a continuous heating layer is disposed at the exterior surface of the part to be de- 8 frosted by applying at such exterior surface a continuous resistant layer capable of creating uniform spread out heat such as a resistant metallic sheet.
  • the resistant layers may be supported on an insulating support layer such as asbestos and in such case the metallic strips for leading the current may serve at the same time for fixing the heating layer upon such support.
  • the heating layer may be divided into various portions connected separately in such manner as to be independently fed with electricity.
  • FIG. 1 is a diagrammatic perspective view of a leading edge of a wing.
  • Figure 2 is a sectional View showing the variations in thickness of the conducting layer.
  • Figure 3 is a perspective view of a modification.
  • the places where deicing seems to be most needed are the leading edge of the Wings, ailerons spars and propellers, and the controls.
  • the process may also be applied to other parts, especially the trailing edge of the wings, ailerons, and spars; and to the upper part of the wings.
  • the invention can be applied to the leading edges of aeroplane wings in the following manner.
  • the wing is covered with fabricthe latter being preferably coated with an insulating paint or varnishsaid fabric is, itself, suilicient to assure adequate electrical insulation.
  • the surface should then be made as even as possible, in order, particularly, to prevent projecting parts-such as the heads of the rivets serving for the assembling of the plates-from adversely affecting the de-icing unit.
  • This result can be obtained by cementing strips of stout paper, or fabric, over the rows of rivets.
  • the parts to be de-iced may be thermally insulated from the metal mass of the wing, by means of an insulating covering of cork, felt, rubber, asbestos, fabric, paper cardboard, flbre,
  • 'I'hey may be electrically insulated by means of the aforesaid non-conductors, or by being covered with an electrical insulating material such as varnish, paint, paper asbestos fabric, etc.
  • Asbestos paper is preferred, as possessing both thermal and electrical properties.
  • Y 'I'he electric contacts with the heating layer are formed of metallised strips produced, for example, by spraying the asbestos paper, or the like, with a metal which is a good conductor, such as copper.
  • a metal which is a good conductor such as copper.
  • the edge of the heating layer is located between two metallised layers, one below and the other above.
  • Fig. 1 shows how the metallised strips may be arranged.
  • the longitudinal strips 2, bordering the heating layer l, are supplied with current by a series of connecting strips 3, which are also metallised and branch from a metallic current lead 4 which is also mounted on the asbestos paper (or fabric) covering the wing.
  • the current leads 4 are preferably constructed of thin flexible braided metal strips (aluminium, copper, tinned copper, etc.) laid parallel with the metallised contact strips.
  • An excellent method of mounting said braided strips on the asbestos paper consists in placing screening pieces on'either side of the strip, and then spraying the strip with metallic particles, which penetrate the interstices of the strip and adhere to the asbestos o n the one hand, and to thestrip on the other, and thus fix the two firmly together.
  • suitable stencils enable metallised connecting strips to be formed which ensure uniform distribution of current to the metallised contact strips.
  • the heating layer will preferably extend further over the upper surface of the wing than over the under surfacev of the latter.
  • the heating layer will preferably be constituted by a metallic layer produced by spraying, spreading or otherwise, a colloidal coating consisting of a resistance metal (preferably unoxidisable) suspended in a liquid solution.
  • a resistance metal preferably unoxidisable
  • resistance alloys such as constantin, nickel silver, nickel-chromium, copper-manganese, bismuth, etc. in a colloidal state, may be employed.
  • the unit composed of the heating layer and the strips supplying the current is advantageously protected by a coating of varnish providing an exterior electrical insulation. This may be black or of a brown shade, to facilitate the dissipation of heat.
  • the device de-icing the wing may be subdivided into two or more sectional units, adapted to be supplied with current in series, or parallel, or in combined series and parallel arrangement, to enable their de-icing function to be Varied.
  • a very ne mesh wire cloth will be used as a resistance conducting layer, for instance a wire cloth of 100 to 250 mesh per square centimeter.
  • the said wire cloth affords the advantage of securing a very uniform -heat distribution and of having a very high mechanical resistance.
  • the part of the wing-concerned with or a removable surface of corresponding form will first of all be covered by sizing a lagging material which should also be a good electric insulating material, such as cork in the form of a layer of 2 to 3 m/m, in thickness.
  • a thin and white asbestos paper which simultaneously constitutes a screen and a thermal insulation as well as an electric insulting material.
  • the current supply to the wire cloth will for instance be secured by welding flat conductors or braided strips of highly conducting metals at the longitudinal ends of said wire cloth.
  • the circulation of current in thc wire cloth will consequently proceed lengthwise with respect to the wing; a current lead 9 being provided near the cabin, the other lead l at the end of the wing.
  • the conductors 8 which provide th Q/f/distribution of current to the wing tips will be preferably secured parallel with the wire cloth strip, as is shown in Figure 3.
  • the said conductor will be sized onto the asbesto paper or onto the cork.
  • It may be ⁇ formed by an aluminium or tinned copper strip or a braided strip of tinned copper having a thickness of: :10 to 1 m/m. and a width of 2 to 10 centimeters for instance.
  • the unit thus constituted may be covered with a usual protecting varnish.
  • the width of the surface to be deiced not being regular in order to make up for the decrease in width of the wire cloth and the resulting increase in heating, it is advantageous to vary progressively the thickness, the character or the grade of the wire cloth. To this end different sorts of wire cloth will be welded endwise, the most resistant being laid towards the cabin.
  • the character and the size of the wire-cloth used vary according to the surfaces to be (ie-iced;
  • nickel, Monel metal, nickel silver and nickel chromium are perfectly convenient; their specific resistances being comprised between 10 and 120 microhms per cm./cm2.
  • the resistance conducting layer will be obtained by means of a very thin metal sheet, of one of the above mentioned metals.
  • the resistance conducting layer will be constituted by a continuous metal layer forming a thin l n obtained by projection by means of a pistol which sprays the particles of some metals being molten.
  • the collection of said particles over the surface to be de-iced forms an electric current conducting metal lm.
  • aluminium may be used, since its conductivity is considerably decreased by the strong oxidation of its particles during its projection.
  • the said thin metal film may also be obtained by a galvanoplastic process.
  • metals such as nickel-chromium, constantin, tin and the like may be used.
  • the in-and-out current leads will be preferably arranged so that the current, passes lengthwise through the resistance layer.
  • Thelelectro-thermic de-icing device forming, the object of the present invention ensures the melting of the superficial contacting layer of rime, and thus producing a liquid nlm which almost completely prevents the adhesion of the rime.
  • the thrusts exerted by the air then dislodge the rime covering the wing.
  • the rime covering the device forms an excellent heat insulation against the cooling action of the air. Given an adequate electrical combination, the subdivision of the heating units enables to utilise the whole as a de-icing device, with a greatly reduced consumption of current.
  • the above-described device when mounted on rigid supports (of metal, light-metal alloys, moulded materials, etc.) shaped to conform with the surface to be de-iced, may take the form of independent, portable standard panels, adapted to be mechanically attached to the part to be protected.
  • a heating and defrosting surface for airplanes comprising an insulating supporting layer applied upon the surface of the airplane to be' heated and defrosted, an electric conducting resistant layer in direct Contact with the atmosphere positioned upon said supporting layer and means for leading and passing an electric current through said resistant layer.
  • a heating and defrosting surface for airplanes comprising an insulating supporting layer applied upon the surface of the airplane to be heated and defrosted, a sprayed metallic resistant layer in direct contact with the atmosphere positioned upon said supporting layer and means for leading and. passing an electric current through said resistant layer.
  • a heating and defrosting surface for airplanes comprising an insulating supporting layer applied upon the surface of the airplane to be heated and defrosted, a carbon resistant layer in direct contact with the atmosphere positioned upon said supporting layer and means for leading and passing an electric current through said resistant layer.
  • a heating and defrosting surface for airplanes comprising an insulating supporting layer applied upon the surface of the airplane to be heated and defosted, a thin wire cloth resistant layer in ⁇ direct contact with the atmosphere postioned upon said supporting layer and means for leading and passing an electric current through said resistant layer.

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

Description

June 25, 1940. J. R RlDEAU ET AL I HEATING SURFACE Filed Nov. 1. 1937 Patented June 25, 1940 I UNITED STATES PATENT OFFICE France l Application November 1, 1 937, Serial No. 172,288
In France November 8, 1936 4 Claims.
The present invention 4has for an object the construction of defrosting surfaces for aeroplanes in which a continuous heating layer is disposed at the exterior surface of the part to be de- 8 frosted by applying at such exterior surface a continuous resistant layer capable of creating uniform spread out heat such as a resistant metallic sheet.
The application of a current to such metallic l sheets may be made by means of metallic strips which may be obtained for example by any metallic process. y
Preferably the resistant layers may be supported on an insulating support layer such as asbestos and in such case the metallic strips for leading the current may serve at the same time for fixing the heating layer upon such support.
The heating layer may be divided into various portions connected separately in such manner as to be independently fed with electricity.
By way of example, and to facilitate comprehension of the present description, special forms of' application of the invention will now be described with reference to the accompanying draw- Figure 1 is a diagrammatic perspective view of a leading edge of a wing.
Figure 2 is a sectional View showing the variations in thickness of the conducting layer.
Figure 3 is a perspective view of a modification.
In the case of aeroplanes, the places where deicing seems to be most needed are the leading edge of the Wings, ailerons spars and propellers, and the controls. The process may also be applied to other parts, especially the trailing edge of the wings, ailerons, and spars; and to the upper part of the wings.
The invention can be applied to the leading edges of aeroplane wings in the following manner.
If the wing is covered with fabricthe latter being preferably coated with an insulating paint or varnishsaid fabric is, itself, suilicient to assure adequate electrical insulation.
In the case of a metal Wing, the surface should then be made as even as possible, in order, particularly, to prevent projecting parts-such as the heads of the rivets serving for the assembling of the plates-from adversely affecting the de-icing unit. This result can be obtained by cementing strips of stout paper, or fabric, over the rows of rivets.
The parts to be de-iced may be thermally insulated from the metal mass of the wing, by means of an insulating covering of cork, felt, rubber, asbestos, fabric, paper cardboard, flbre,
etc. 'I'hey may be electrically insulated by means of the aforesaid non-conductors, or by being covered with an electrical insulating material such as varnish, paint, paper asbestos fabric, etc.
Asbestos paper is preferred, as possessing both thermal and electrical properties.
Y 'I'he electric contacts with the heating layer are formed of metallised strips produced, for example, by spraying the asbestos paper, or the like, with a metal which is a good conductor, such as copper. To ensure perfect contact between said metallised strips and the heating layer, it is advisable, in the first place, to provide a metallised strip of asbestos paper on the zone bordering the heating layer, and then apply the carbon layer so as to coVer-at least partiallythe said metallised strip, and finally to apply a second metallised strip, covering the same surface as the first. In this way, the edge of the heating layer is located between two metallised layers, one below and the other above.
Fig. 1 shows how the metallised strips may be arranged.
The longitudinal strips 2, bordering the heating layer l, are supplied with current by a series of connecting strips 3, which are also metallised and branch from a metallic current lead 4 which is also mounted on the asbestos paper (or fabric) covering the wing.
The current leads 4 are preferably constructed of thin flexible braided metal strips (aluminium, copper, tinned copper, etc.) laid parallel with the metallised contact strips.
An excellent method of mounting said braided strips on the asbestos paper consists in placing screening pieces on'either side of the strip, and then spraying the strip with metallic particles, which penetrate the interstices of the strip and adhere to the asbestos o n the one hand, and to thestrip on the other, and thus fix the two firmly together.
At the same time, suitable stencils enable metallised connecting strips to be formed which ensure uniform distribution of current to the metallised contact strips.
'Ihis arrangement enables an excellent distribution of the current to be attained, without the Wing being pierced at any, point of its surface.
The heating layer will preferably extend further over the upper surface of the wing than over the under surfacev of the latter.
The heating layer will preferably be constituted by a metallic layer produced by spraying, spreading or otherwise, a colloidal coating consisting of a resistance metal (preferably unoxidisable) suspended in a liquid solution. For this purpose, resistance alloys, such as constantin, nickel silver, nickel-chromium, copper-manganese, bismuth, etc. in a colloidal state, may be employed.
Finally, the unit composed of the heating layer and the strips supplying the current is advantageously protected by a coating of varnish providing an exterior electrical insulation. This may be black or of a brown shade, to facilitate the dissipation of heat.
The device de-icing the wing may be subdivided into two or more sectional units, adapted to be supplied with current in series, or parallel, or in combined series and parallel arrangement, to enable their de-icing function to be Varied.
According to another embodiment of the present invention (see Figure 3) a very ne mesh wire cloth will be used as a resistance conducting layer, for instance a wire cloth of 100 to 250 mesh per square centimeter. The said wire cloth affords the advantage of securing a very uniform -heat distribution and of having a very high mechanical resistance.
In the particular case of the leading edge of an aircraft wing, the part of the wing-concerned with or a removable surface of corresponding form will first of all be covered by sizing a lagging material which should also be a good electric insulating material, such as cork in the form of a layer of 2 to 3 m/m, in thickness.
Upon said cork is subsequently sized a thin and white asbestos paper which simultaneously constitutes a screen and a thermal insulation as well as an electric insulting material.
If the leading edge is of uniform p-role over all its length between the cabin and the tip of the wing, as shown in Figure 3 a wire cloth l having a width corresponding to the iced surface is cemented (to this end a caseine base cement is advantageously applied).
The current supply to the wire cloth will for instance be secured by welding flat conductors or braided strips of highly conducting metals at the longitudinal ends of said wire cloth. The circulation of current in thc wire cloth will consequently proceed lengthwise with respect to the wing; a current lead 9 being provided near the cabin, the other lead l at the end of the wing. In order to avoid the wing being pierced' the conductors 8 which provide th Q/f/distribution of current to the wing tips will be preferably secured parallel with the wire cloth strip, as is shown in Figure 3. The said conductor will be sized onto the asbesto paper or onto the cork.
It may be `formed by an aluminium or tinned copper strip or a braided strip of tinned copper having a thickness of: :10 to 1 m/m. and a width of 2 to 10 centimeters for instance.
The unit thus constituted may be covered with a usual protecting varnish.
When the profile of the wing is not regular, i. e. when its section is decreasing from the cabin up to its tip, the width of the surface to be deiced not being regular, in order to make up for the decrease in width of the wire cloth and the resulting increase in heating, it is advantageous to vary progressively the thickness, the character or the grade of the wire cloth. To this end different sorts of wire cloth will be welded endwise, the most resistant being laid towards the cabin.
The character and the size of the wire-cloth used vary according to the surfaces to be (ie-iced;
in many cases, nickel, Monel metal, nickel silver and nickel chromium are perfectly convenient; their specific resistances being comprised between 10 and 120 microhms per cm./cm2.
According to another embodiment the resistance conducting layer will be obtained by means of a very thin metal sheet, of one of the above mentioned metals.
According to another embodiment, the resistance conducting layer will be constituted by a continuous metal layer forming a thin l n obtained by projection by means of a pistol which sprays the particles of some metals being molten. The collection of said particles over the surface to be de-iced forms an electric current conducting metal lm. For instance aluminium may be used, since its conductivity is considerably decreased by the strong oxidation of its particles during its projection.
The said thin metal film may also be obtained by a galvanoplastic process. For forming the lm also metals such as nickel-chromium, constantin, tin and the like may be used.
In the case of a heating layer formed of metal of relatively high conductivity, the in-and-out current leads will be preferably arranged so that the current, passes lengthwise through the resistance layer.
Thelelectro-thermic de-icing device forming, the object of the present invention ensures the melting of the superficial contacting layer of rime, and thus producing a liquid nlm which almost completely prevents the adhesion of the rime. The thrusts exerted by the air then dislodge the rime covering the wing. The rime covering the device forms an excellent heat insulation against the cooling action of the air. Given an adequate electrical combination, the subdivision of the heating units enables to utilise the whole as a de-icing device, with a greatly reduced consumption of current.
According to another embodiment of the invention, the above-described device, when mounted on rigid supports (of metal, light-metal alloys, moulded materials, etc.) shaped to conform with the surface to be de-iced, may take the form of independent, portable standard panels, adapted to be mechanically attached to the part to be protected.
Having now particularly described and ascertained the nature of our invention and in what manner the same is to be performed, we declare that what we claim is:
1. A heating and defrosting surface for airplanes comprising an insulating supporting layer applied upon the surface of the airplane to be' heated and defrosted, an electric conducting resistant layer in direct Contact with the atmosphere positioned upon said supporting layer and means for leading and passing an electric current through said resistant layer.
2. A heating and defrosting surface for airplanes comprising an insulating supporting layer applied upon the surface of the airplane to be heated and defrosted, a sprayed metallic resistant layer in direct contact with the atmosphere positioned upon said supporting layer and means for leading and. passing an electric current through said resistant layer.
3. A heating and defrosting surface for airplanes comprising an insulating supporting layer applied upon the surface of the airplane to be heated and defrosted, a carbon resistant layer in direct contact with the atmosphere positioned upon said supporting layer and means for leading and passing an electric current through said resistant layer.
4. A heating and defrosting surface for airplanes comprising an insulating supporting layer applied upon the surface of the airplane to be heated and defosted, a thin wire cloth resistant layer in `direct contact with the atmosphere postioned upon said supporting layer and means for leading and passing an electric current through said resistant layer.
JEAN ROBERT RIDEAU. ANDR MAXIME DUCRET.
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Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2454874A (en) * 1943-04-23 1948-11-30 Goodrich Co B F Covering for preventing ice formation on aircraft
US2489643A (en) * 1943-10-18 1949-11-29 Goodrich Co B F Heating and pressing apparatus
US2496279A (en) * 1945-02-10 1950-02-07 Safeway Heat Elements Inc Flexible electric heater for deicing airfoils
US2503457A (en) * 1947-04-04 1950-04-11 Curtiss Wright Corp Propeller blade deicing shoe
US2523566A (en) * 1945-02-12 1950-09-26 Blue Ridge Glass Corp Glass electrical heating panel
US2552075A (en) * 1944-08-05 1951-05-08 Catherine Van Daam Heating device for airplanes
US2557983A (en) * 1949-03-22 1951-06-26 Pittsburgh Plate Glass Co Transparent electroconductive article
US2590944A (en) * 1949-01-03 1952-04-01 Napier & Son Ltd Electrical heating apparatus
US2622828A (en) * 1949-04-11 1952-12-23 Rotax Ltd Aircraft deicing means
US2627012A (en) * 1949-06-21 1953-01-27 Napier & Son Ltd Heating of surfaces by laminated foil resistance elements with timed connecting means
US2631219A (en) * 1949-05-06 1953-03-10 Charles T Suchy Electrical heating element
US2669646A (en) * 1950-01-20 1954-02-16 Goodyear Tire & Rubber Electrically conductive material
US2685634A (en) * 1952-04-29 1954-08-03 Bohn Aluminium & Brass Corp Refrigeration unit with defrost heater
US2690890A (en) * 1949-02-25 1954-10-05 Wind Turbine Company Deicing system for airfoil structures
US2699303A (en) * 1947-10-24 1955-01-11 Rotol Ltd Means for electrically heating the spinners of airscrews
US2715668A (en) * 1952-10-23 1955-08-16 Electrofilm Inc Electrically conductive film panel heaters
US2762897A (en) * 1951-06-28 1956-09-11 Lockheed Aircraft Corp De-icing means for aircraft and the like
US2777930A (en) * 1954-04-28 1957-01-15 Nathanson Max Heating unit
US2791668A (en) * 1951-08-21 1957-05-07 Napier & Son Ltd Electrically heated de-icing or antifreezing apparatus
US2799764A (en) * 1953-10-15 1957-07-16 Edward F Chandler Panel heating device
US2835777A (en) * 1956-06-28 1958-05-20 Gen Motors Corp Heated steering wheel
US2843713A (en) * 1954-08-04 1958-07-15 Libbey Owens Ford Glass Co Electrically heated articles
US2879367A (en) * 1955-04-25 1959-03-24 Douglas K Mclean Food package
US2977450A (en) * 1957-12-16 1961-03-28 Libbey Owens Ford Glass Co Transparent electrically conducting films
US3007026A (en) * 1948-10-21 1961-10-31 George V Woodling Electrical heating devices
US3535930A (en) * 1966-07-26 1970-10-27 Rosemount Eng Co Ltd Aerodynamic components mounted externally on an aircraft
US20060272340A1 (en) * 2002-02-11 2006-12-07 Victor Petrenko Pulse electrothermal and heat-storage ice detachment apparatus and methods
US20070045282A1 (en) * 2002-02-11 2007-03-01 The Trustees Of Dartmouth College Systems and methods for modifying an ice-to-object interface
WO2008060696A2 (en) * 2006-05-22 2008-05-22 The Trustees Of Dartmouth College Pulse electrothermal deicing of complex shapes
US20080196429A1 (en) * 2002-02-11 2008-08-21 The Trustees Of Dartmouth College Pulse Electrothermal And Heat-Storage Ice Detachment Apparatus And Method
US20080223842A1 (en) * 2002-02-11 2008-09-18 The Trustees Of Dartmouth College Systems And Methods For Windshield Deicing
US20080258009A1 (en) * 2007-03-30 2008-10-23 Airbus Espana, S.L.. Leading edge for aircraft made of reinforced composite material
US20090199569A1 (en) * 2004-06-22 2009-08-13 Victor Petrenko Pulse systems and methods for detaching ice
US20090235681A1 (en) * 2002-02-11 2009-09-24 The Trustees Of Dartmouth College Pulse Electrothermal Mold Release Icemaker For Refrigerator Having Interlock Closure And Baffle For Safety
US20090235682A1 (en) * 2002-02-11 2009-09-24 The Trustees Of Dartmouth College Pulse Electrothermal Mold Release Icemaker With Safety Baffles For Refrigerator
US20110132588A1 (en) * 2009-11-23 2011-06-09 Icecode, Llc System and Method for Energy-Saving Inductive Heating of Evaporators and Other Heat-Exchangers
US8424324B2 (en) 2008-11-05 2013-04-23 The Trustees Of Dartmouth College Refrigerant evaporators with pulse-electrothermal defrosting
US20180178917A1 (en) * 2016-12-27 2018-06-28 Airbus Operations S.A.S. Structure for propulsive aircraft assembly, associated propulsive system and assembly
EP3409588A1 (en) * 2017-05-30 2018-12-05 Bell Helicopter Textron Inc. Electrical bus arrangement for ice protection systems
US20200032670A1 (en) * 2018-07-24 2020-01-30 United Technologies Corporation Systems and methods for fan blade de-icing

Cited By (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2454874A (en) * 1943-04-23 1948-11-30 Goodrich Co B F Covering for preventing ice formation on aircraft
US2489643A (en) * 1943-10-18 1949-11-29 Goodrich Co B F Heating and pressing apparatus
US2552075A (en) * 1944-08-05 1951-05-08 Catherine Van Daam Heating device for airplanes
US2496279A (en) * 1945-02-10 1950-02-07 Safeway Heat Elements Inc Flexible electric heater for deicing airfoils
US2523566A (en) * 1945-02-12 1950-09-26 Blue Ridge Glass Corp Glass electrical heating panel
US2503457A (en) * 1947-04-04 1950-04-11 Curtiss Wright Corp Propeller blade deicing shoe
US2699303A (en) * 1947-10-24 1955-01-11 Rotol Ltd Means for electrically heating the spinners of airscrews
US3007026A (en) * 1948-10-21 1961-10-31 George V Woodling Electrical heating devices
US2590944A (en) * 1949-01-03 1952-04-01 Napier & Son Ltd Electrical heating apparatus
US2690890A (en) * 1949-02-25 1954-10-05 Wind Turbine Company Deicing system for airfoil structures
US2557983A (en) * 1949-03-22 1951-06-26 Pittsburgh Plate Glass Co Transparent electroconductive article
US2622828A (en) * 1949-04-11 1952-12-23 Rotax Ltd Aircraft deicing means
US2631219A (en) * 1949-05-06 1953-03-10 Charles T Suchy Electrical heating element
US2627012A (en) * 1949-06-21 1953-01-27 Napier & Son Ltd Heating of surfaces by laminated foil resistance elements with timed connecting means
US2669646A (en) * 1950-01-20 1954-02-16 Goodyear Tire & Rubber Electrically conductive material
US2762897A (en) * 1951-06-28 1956-09-11 Lockheed Aircraft Corp De-icing means for aircraft and the like
US2791668A (en) * 1951-08-21 1957-05-07 Napier & Son Ltd Electrically heated de-icing or antifreezing apparatus
US2685634A (en) * 1952-04-29 1954-08-03 Bohn Aluminium & Brass Corp Refrigeration unit with defrost heater
US2715668A (en) * 1952-10-23 1955-08-16 Electrofilm Inc Electrically conductive film panel heaters
US2799764A (en) * 1953-10-15 1957-07-16 Edward F Chandler Panel heating device
US2777930A (en) * 1954-04-28 1957-01-15 Nathanson Max Heating unit
US2843713A (en) * 1954-08-04 1958-07-15 Libbey Owens Ford Glass Co Electrically heated articles
US2879367A (en) * 1955-04-25 1959-03-24 Douglas K Mclean Food package
US2835777A (en) * 1956-06-28 1958-05-20 Gen Motors Corp Heated steering wheel
US2977450A (en) * 1957-12-16 1961-03-28 Libbey Owens Ford Glass Co Transparent electrically conducting films
US3535930A (en) * 1966-07-26 1970-10-27 Rosemount Eng Co Ltd Aerodynamic components mounted externally on an aircraft
US7638735B2 (en) 2002-02-11 2009-12-29 The Trustees Of Dartmouth College Pulse electrothermal and heat-storage ice detachment apparatus and methods
US20090235682A1 (en) * 2002-02-11 2009-09-24 The Trustees Of Dartmouth College Pulse Electrothermal Mold Release Icemaker With Safety Baffles For Refrigerator
US8405002B2 (en) 2002-02-11 2013-03-26 The Trustees Of Dartmouth College Pulse electrothermal mold release icemaker with safety baffles for refrigerator
US20080196429A1 (en) * 2002-02-11 2008-08-21 The Trustees Of Dartmouth College Pulse Electrothermal And Heat-Storage Ice Detachment Apparatus And Method
US20060272340A1 (en) * 2002-02-11 2006-12-07 Victor Petrenko Pulse electrothermal and heat-storage ice detachment apparatus and methods
US20080223842A1 (en) * 2002-02-11 2008-09-18 The Trustees Of Dartmouth College Systems And Methods For Windshield Deicing
US7629558B2 (en) 2002-02-11 2009-12-08 The Trustees Of Dartmouth College Systems and methods for modifying an ice-to-object interface
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