US2464273A - Decing device for airfoils - Google Patents
Decing device for airfoils Download PDFInfo
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- US2464273A US2464273A US734141A US73414147A US2464273A US 2464273 A US2464273 A US 2464273A US 734141 A US734141 A US 734141A US 73414147 A US73414147 A US 73414147A US 2464273 A US2464273 A US 2464273A
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- cover
- airfoil
- shoe
- resistance
- current
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- 238000005299 abrasion Methods 0.000 description 15
- 229910052751 metal Inorganic materials 0.000 description 12
- 239000002184 metal Substances 0.000 description 12
- 239000004568 cement Substances 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 239000004020 conductor Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229910001369 Brass Inorganic materials 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 239000010951 brass Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 101100039010 Caenorhabditis elegans dis-3 gene Proteins 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- 229910000737 Duralumin Inorganic materials 0.000 description 1
- 229910000792 Monel Inorganic materials 0.000 description 1
- 230000001154 acute effect Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 238000010616 electrical installation Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910001120 nichrome Inorganic materials 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000003449 preventive effect Effects 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229920003002 synthetic resin Polymers 0.000 description 1
- 239000000057 synthetic resin Substances 0.000 description 1
Images
Classifications
-
- 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
- This invention relates to an electrical device for de-icing airfoils.
- One object of the present invention is to combine abrasion resistant means with de-icing means on an airfoil edge or surface whereby both may exert beneficial effects simultaneously and in combination.
- Another object is to so connect the abrasion resistant means and the electrical resistor so that an even distribution of current and a substantially uniform voltage drop takes place over the length of these elements.
- Another object is to provide an electrical installation that will function well on a low voltage or high voltage current supply.
- Another object is to provide a structure that is suitable for use to provide very sharp leading edges on airfoils and may be applied to existing constructions.
- Fig. l is a side elevation of a metal propeller blade or airplane wing showing my de-icing device mounted adjacent the leading edge;
- Fig. 2 is an enlarged cross section of the blade or wing taken along the line 22 of that figure.
- Fig. 3 is also an enlarged cross section of a blade or wing having thereon my device and showing a modified form thereof. This modification is especially adapted to extremely high speed operation.
- the body of the blade which may be made of forged Duralumin metal, steel, or other high strength, low-resistance material.
- II is a cover of low electrical resistance abrasion-resistant metal which may be copper, brass, stainless steel, Monel or terne-plate with the outer surface preferably chromium plated.
- the length of the cover I l is slightly short, on both ends thereof, of the length of high-resistance electrical conductor I2 such as Nichrome metal or conductive rubber which covers the leading edge as shown in Fig. 2.
- the conductor I2 is preferably in the form of a U-shaped shoe, the inner surface of which conforms substantially to the leading edge of the airfoil that is to be de-iced.
- the length of the conductor I 2 is such that it will supply sufficient heat over that part of the propeller upon which ice is prone to form. Its temperature, when heated, should be such that it will at least fully counteract the adhesive action or quality of the ice when the propeller is rotated at high speed. Centrifugal or translational force is depended upon to throw the ice oil the blade after the adhesion of the ice has been overcome.
- Electrical energy is supplied to the elements II and I2 as follows: Current is supplied to each blade I0 through leads I3 and I 4. Any suitable means for supplying such energy may be used, for example, an electrical generator (not shown) which is connected to the leads I 3 and I4 through slip rings (not shown) which are well known in the art and are illustrated in Patent No. 2,402,770.
- Lead I3 is connected to the inner end of strip I3.
- Lead i4 is grounded to the propeller blade I0 near or at the shank thereof. The current path is therefore such that a crosswise flow takes place along low-resistance cover I I and across high-resistance strip or shoc- I2 to the blade I0, to the shank thereof.
- the strip II acts as a distributor or a manifold, and that the highly-resistant part of the current path is very short. It will also be apparent that the high-resistance shoe i2 is fully protected from ice-abrasion by the strip II.
- the current-distributing abrasion-resistant cover II is slightly shorter than the high resistance shoe l2, so that dirt lodging on the ends cannot electrically bridge cover H to the blade, thus constituting a short circuit.
- the strip H and the shoe I2 may be attached to each other by conductive adhesives. These are specially prepared rubber-containing cements having a high proportion of carbon particles. The brand name of one such cement is 314 made by Ault and Wiborg Company, Cincinnati, Ohio. The exact composition of these substances is not known, but they are believed to be self vulcanizing rubber cements containing a high proportion .of gas carbon. Such a cement is dis- 3 closed in Patent No. 2,406,367, column 4, lines 17 to 29 inclusive. Other suitable means of attachment well known in the art may also be used such as synthetic resin screws.
- the shoe l2 may be attached to the leading edge of the blade id as described or the surfaces of the strips may be placed in direct contact and held together by electrically insulated screws or the like.
- a de-icer in the form of a sharp edge for a wing or propeller is shown adhesively or mechanically attached to the leading edge of a conventional propeller or wing 40.
- a bus-bar l5 Centrally embedded in the de-icer is a bus-bar l5 which is preferably of triangular section and of light metal, preferably aluminum. It is supplied with current by a lead ll.
- a triangular-sectioned sheath iii of conductive rubber Surrounding the bus-bar I5 is a triangular-sectioned sheath iii of conductive rubber. Such rubber has sufficient resistance to generate enough heat, when supplied with an appropriate current, to keep the temperature of a leading edge above freezing, even at high speeds of movement.
- the composition of such a rubber is given in Patent No.
- the rubber resistance element 56 is enclosed by a metallic cover II of copper, brass, steel, lVionel or the like. It is included in the electric circuit by means of a lead 58.
- the conductive circuit therefore traverses the bus-bar E5, the sheath it, the cover H and the airfoil l0. airfoil l there extend a plurality of conductive screws l9 which act both as electrically conducting and mechanical fastening devices.
- the modified de-icer shown in Fig. 3 is also supplied with electricity through slip rings.
- the leads ill and it may be recessed into the trailing edge of the airfoil in the case of its use on a propeller and into the leading edge, in the case of the wing.
- Current should be directed into the de-icer on wings in advance of ice formation rather than after the ice has formed. That is not to say that the deicer will not rid the airfoil of ice after the latter has formed, but rather that the results are more satisfactory on wings when the de-icer is used v as a preventive rather than a cure.
- a de--icer comprising an outer thin sharpedged cover of abrasion-resistant metal of high electrical conductivity, an inner shoe of high resistance material slightly longer than said cover, said elements being in contact throughout the length of the cover and connections including both of said elements in an electric circuit whereby to pass current between said cover in said shoe substantially throughout the length of the cover to heat the shoe substantially throughout its length.
- an extensive shoe of electrically high resistant material said shoe conforming on its one side to the contour of the leading edge of an airfoil, an abrasionresistant cover of a metal of low electrical resistance extending over and conforming substantially in shape to said shoe, said cover and said shoe being conductively and adhesively joined together, and means for supplying said cover with electric current whereby to provide a substantially even flow of current and consequent heating cur- Between the cover l and the rent supply to said shoe substantially throughout its length.
- an electrically conductive airfoil a U-shaped shoe of high electrical resistance attached over that portion of the leading edge of said airfoil upon which ice is most prone to form, an abrasion-resistant cover of low electrical resistance attached to the leading edge of the airfoil over said U-shaped shoe and an electrical circuit, one lead of which is attached to said abrasion-resistant strip and another lead of which is grounded to the conductive airfoil whereby to keep said airfoil substantially free of ice when it is rotated at high speed under icing conditions.
- a metallic airfoil an electric circuit one arm of which is grounded thereto, a high-resistance shoe mounted on the leading edge of said airfoil, a current distributing, abrasionresistant cover mounted over said shoe, and another arm of said electric circuit attached to said cover, said arm being of opposite polarity, whereby passage of current takes place largely along the abrasion resistant cover and across the high resistance shoe to the airfoil, so that the adhesion of ice to the leading edge of said airfoil is substantially prevented when the airfoil is moving at high speed.
- a de-icer capable of being attached to a conventional metal airfoil on the leading edge thereof which comprises in combination, a central bus-bar, a sheath of conductive rubber about said bus-bar, said sheath having a substantially triangular shape, one side of which conforms to the shape of the leading edge of the airfoil to which it is to be attached, an acute angled cover of abrasion-resistant metal of high electrical conductivity coextensive with said bus-bar and said rubber sheath, and means for supplying electric current to said bus-bar and said cover.
- an airfoil a triangular edge of electrically conductive rubber conductively cemented to the leading edge thereof, a triangular bus-bar embedded symmetrically within said conductive rubber edge, a thin wedge-shaped strip of abrasion-resistant electrically conductive metal enclosing said conductive rubber edge and said bus-bar and attached by its ends to said airfoil, and electrical leads each extending to said wedgevshaped metal strip and to said bus-bar.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Elimination Of Static Electricity (AREA)
Description
March 15, 1949. M. TANCHEL DEICING DEVICE FOR AIRFOILS Filed March 12, 1947 INVENTOR. v MFAV/A M/VK /EA BY V Patented Mar. 15, 1949 UNITED STATES PATENT OFFICE 8 Claims.
(Granted under the act of March 3, 1883, as amended April 30, 1928; 370 0. G. 757) The invention described herein may be manufactured and used by or for the Government for governmental purposes without payment to me of any royalty thereon.
This invention relates to an electrical device for de-icing airfoils.
In the past, trouble has been encountered when propellers or the leading edges of wings were provided with electrical de-icing equipment. The rapid abrasion which occurs under such conditions of use soon made the de-icers inoperative. Other troubles encountered were due to uneven distribution of heat, which in turn was due to uneven distribution of current through the resistance elements. For example, it was attempted to use conductive rubber strips of considerable length and to supply current to such strips by connecting high voltage leads to the ends of the strips. Poor distribution of electrical conductivity resulted from such construction and the heat distribution was consequently very uneven. The resistance of the conductive rubber did not stay constant when it was exposed to the weather directly. This was due partially to the fact that prior attempts used low resistance conductive rubber which had a high carbon content. One object of the present invention is to combine abrasion resistant means with de-icing means on an airfoil edge or surface whereby both may exert beneficial effects simultaneously and in combination.
Another object is to so connect the abrasion resistant means and the electrical resistor so that an even distribution of current and a substantially uniform voltage drop takes place over the length of these elements.
Another object is to provide an electrical installation that will function well on a low voltage or high voltage current supply.
Another object is to provide a structure that is suitable for use to provide very sharp leading edges on airfoils and may be applied to existing constructions.
In the drawings:
Fig. l is a side elevation of a metal propeller blade or airplane wing showing my de-icing device mounted adjacent the leading edge;
Fig. 2 is an enlarged cross section of the blade or wing taken along the line 22 of that figure; and
Fig. 3 is also an enlarged cross section of a blade or wing having thereon my device and showing a modified form thereof. This modification is especially adapted to extremely high speed operation.
While the above forms .of the invention will be described as applied to a propeller blade, .it is to be noted that an airplane wing or any other airfoil surface exposed to possible icing can be substituted for the blade. Only those adaptations which skilled airplane mechanics can make will 2 be necessary to shift the invention from the use on a blade to use on a wing or tail surface.
In is the body of the blade, which may be made of forged Duralumin metal, steel, or other high strength, low-resistance material. II is a cover of low electrical resistance abrasion-resistant metal which may be copper, brass, stainless steel, Monel or terne-plate with the outer surface preferably chromium plated. The length of the cover I l is slightly short, on both ends thereof, of the length of high-resistance electrical conductor I2 such as Nichrome metal or conductive rubber which covers the leading edge as shown in Fig. 2. The conductor I2 is preferably in the form of a U-shaped shoe, the inner surface of which conforms substantially to the leading edge of the airfoil that is to be de-iced. The length of the conductor I 2 is such that it will supply sufficient heat over that part of the propeller upon which ice is prone to form. Its temperature, when heated, should be such that it will at least fully counteract the adhesive action or quality of the ice when the propeller is rotated at high speed. Centrifugal or translational force is depended upon to throw the ice oil the blade after the adhesion of the ice has been overcome.
Electrical energy is supplied to the elements II and I2 as follows: Current is supplied to each blade I0 through leads I3 and I 4. Any suitable means for supplying such energy may be used, for example, an electrical generator (not shown) which is connected to the leads I 3 and I4 through slip rings (not shown) which are well known in the art and are illustrated in Patent No. 2,402,770. Lead I3 is connected to the inner end of strip I3. Lead i4 is grounded to the propeller blade I0 near or at the shank thereof. The current path is therefore such that a crosswise flow takes place along low-resistance cover I I and across high-resistance strip or shoc- I2 to the blade I0, to the shank thereof. It will be apparent then that the strip II acts as a distributor or a manifold, and that the highly-resistant part of the current path is very short. It will also be apparent that the high-resistance shoe i2 is fully protected from ice-abrasion by the strip II. The current-distributing abrasion-resistant cover II is slightly shorter than the high resistance shoe l2, so that dirt lodging on the ends cannot electrically bridge cover H to the blade, thus constituting a short circuit.
The strip H and the shoe I2 may be attached to each other by conductive adhesives. These are specially prepared rubber-containing cements having a high proportion of carbon particles. The brand name of one such cement is 314 made by Ault and Wiborg Company, Cincinnati, Ohio. The exact composition of these substances is not known, but they are believed to be self vulcanizing rubber cements containing a high proportion .of gas carbon. Such a cement is dis- 3 closed in Patent No. 2,406,367, column 4, lines 17 to 29 inclusive. Other suitable means of attachment well known in the art may also be used such as synthetic resin screws. The shoe l2 may be attached to the leading edge of the blade id as described or the surfaces of the strips may be placed in direct contact and held together by electrically insulated screws or the like.
In Fig. 3, a de-icer in the form of a sharp edge for a wing or propeller is shown adhesively or mechanically attached to the leading edge of a conventional propeller or wing 40. Centrally embedded in the de-icer is a bus-bar l5 which is preferably of triangular section and of light metal, preferably aluminum. It is supplied with current by a lead ll. Surrounding the bus-bar I5 is a triangular-sectioned sheath iii of conductive rubber. Such rubber has sufficient resistance to generate enough heat, when supplied with an appropriate current, to keep the temperature of a leading edge above freezing, even at high speeds of movement. The composition of such a rubber is given in Patent No. 2,406,567, column 3, line 65 to column 4, line 2. The rubber resistance element 56 is enclosed by a metallic cover II of copper, brass, steel, lVionel or the like. It is included in the electric circuit by means of a lead 58. The conductive circuit therefore traverses the bus-bar E5, the sheath it, the cover H and the airfoil l0. airfoil l there extend a plurality of conductive screws l9 which act both as electrically conducting and mechanical fastening devices.
In operation, the modified de-icer shown in Fig. 3 is also supplied with electricity through slip rings. In this form, the leads ill and it may be recessed into the trailing edge of the airfoil in the case of its use on a propeller and into the leading edge, in the case of the wing. Current should be directed into the de-icer on wings in advance of ice formation rather than after the ice has formed. That is not to say that the deicer will not rid the airfoil of ice after the latter has formed, but rather that the results are more satisfactory on wings when the de-icer is used v as a preventive rather than a cure. In the case of propellers, the opposite is true since after a buildup of ice on the leading edge the, ice layer acts as heat-insulation against the air. Therefore, less heat is needed to melt the inner surface of the ice and permit centrifugal force to get it off than to prevent it from forming.
What I claim is:
l. A de--icer comprising an outer thin sharpedged cover of abrasion-resistant metal of high electrical conductivity, an inner shoe of high resistance material slightly longer than said cover, said elements being in contact throughout the length of the cover and connections including both of said elements in an electric circuit whereby to pass current between said cover in said shoe substantially throughout the length of the cover to heat the shoe substantially throughout its length.
2. In combination in a de-icer, an extensive shoe of electrically high resistant material, said shoe conforming on its one side to the contour of the leading edge of an airfoil, an abrasionresistant cover of a metal of low electrical resistance extending over and conforming substantially in shape to said shoe, said cover and said shoe being conductively and adhesively joined together, and means for supplying said cover with electric current whereby to provide a substantially even flow of current and consequent heating cur- Between the cover l and the rent supply to said shoe substantially throughout its length.
3. In combination, an electrically conductive airfoil, a U-shaped shoe of high electrical resistance attached over that portion of the leading edge of said airfoil upon which ice is most prone to form, an abrasion-resistant cover of low electrical resistance attached to the leading edge of the airfoil over said U-shaped shoe and an electrical circuit, one lead of which is attached to said abrasion-resistant strip and another lead of which is grounded to the conductive airfoil whereby to keep said airfoil substantially free of ice when it is rotated at high speed under icing conditions.
4. The combination set forth in claim 3 in which the abrasion-resistant cover is made of electrically conductive metal of low resistance.
5. In combination, a metallic airfoil, an electric circuit one arm of which is grounded thereto, a high-resistance shoe mounted on the leading edge of said airfoil, a current distributing, abrasionresistant cover mounted over said shoe, and another arm of said electric circuit attached to said cover, said arm being of opposite polarity, whereby passage of current takes place largely along the abrasion resistant cover and across the high resistance shoe to the airfoil, so that the adhesion of ice to the leading edge of said airfoil is substantially prevented when the airfoil is moving at high speed.
6. The combination according to claim 5 in which the current-distributing, abrasion-resistant cover is slightly shorter than the high-resistance cover and is arranged over the latter to leave small margins of the high-resistant cover projecting beyond the current-distributing abrasion-resistant strip.
7. A de-icer capable of being attached to a conventional metal airfoil on the leading edge thereof which comprises in combination, a central bus-bar, a sheath of conductive rubber about said bus-bar, said sheath having a substantially triangular shape, one side of which conforms to the shape of the leading edge of the airfoil to which it is to be attached, an acute angled cover of abrasion-resistant metal of high electrical conductivity coextensive with said bus-bar and said rubber sheath, and means for supplying electric current to said bus-bar and said cover.
3. In combination, an airfoil, a triangular edge of electrically conductive rubber conductively cemented to the leading edge thereof, a triangular bus-bar embedded symmetrically within said conductive rubber edge, a thin wedge-shaped strip of abrasion-resistant electrically conductive metal enclosing said conductive rubber edge and said bus-bar and attached by its ends to said airfoil, and electrical leads each extending to said wedgevshaped metal strip and to said bus-bar.
MELVIN TANCHEL.
' file of this patent:
UNITED STATES PATENTS Number Name Date 1,846,468 Benson Feb. 23, 1932 2,055,099 Gentile Sept. 22, 1936 2,297,540 Driscoll Sept. 29, 1942 2,309,682 Van Daam Feb. 2, 1943 2,393,100 Gallay Jan. 15, 1946 2,402,770 Poekel June 25, 1946 2,406,367 Griflith et a1. Aug. 27, 1946 2,423,945 Osipow et a1 July 15, 1947
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US734141A US2464273A (en) | 1947-03-12 | 1947-03-12 | Decing device for airfoils |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US734141A US2464273A (en) | 1947-03-12 | 1947-03-12 | Decing device for airfoils |
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US2464273A true US2464273A (en) | 1949-03-15 |
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US734141A Expired - Lifetime US2464273A (en) | 1947-03-12 | 1947-03-12 | Decing device for airfoils |
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Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2643206A (en) * | 1949-09-28 | 1953-06-23 | Wingfoot Corp | Package for shipping and storing a conductive rubber heating element and method of making same |
US2680185A (en) * | 1953-04-17 | 1954-06-01 | Anthony X Basile | Heater gasket |
US2695146A (en) * | 1951-06-21 | 1954-11-23 | Gen Motors Corp | Aircraft propeller blade with deicing means |
US2757273A (en) * | 1952-12-12 | 1956-07-31 | Goodyear Tire & Rubber | De-icer |
US2762897A (en) * | 1951-06-28 | 1956-09-11 | Lockheed Aircraft Corp | De-icing means for aircraft and the like |
US2992317A (en) * | 1957-10-14 | 1961-07-11 | Goodrich Co B F | Electrically heated ice-removal apparatus |
US5934617A (en) * | 1997-09-22 | 1999-08-10 | Northcoast Technologies | De-ice and anti-ice system and method for aircraft surfaces |
US6237874B1 (en) | 1997-09-22 | 2001-05-29 | Northcoast Technologies | Zoned aircraft de-icing system and method |
US6279856B1 (en) | 1997-09-22 | 2001-08-28 | Northcoast Technologies | Aircraft de-icing system |
US20110296811A1 (en) * | 2010-06-03 | 2011-12-08 | Rolls-Royce Plc | Heat transfer arrangement for fluid-washed surfaces |
US20150114945A1 (en) * | 2013-10-30 | 2015-04-30 | Goodrich Corporation | Electrical interconnects for ice protection systems |
US20210284345A1 (en) * | 2020-03-16 | 2021-09-16 | Ratier-Figeac Sas | Deicer aerodynamic integration |
US20210309376A1 (en) * | 2020-04-07 | 2021-10-07 | Goodrich Corporation | Integrated busbar heater for ice protection systems |
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US1846468A (en) * | 1930-08-29 | 1932-02-23 | James A Benson | Aeroplane propeller |
US2055099A (en) * | 1934-06-06 | 1936-09-22 | Virginio J Gentile | Permanent waving sachet |
US2297540A (en) * | 1941-06-05 | 1942-09-29 | Edward A Driscoll | Prevention of ice formation |
US2309682A (en) * | 1939-06-27 | 1943-02-02 | Gerrit Van Daam | Means for heating wings of airplanes |
US2393100A (en) * | 1943-08-06 | 1946-01-15 | Honorary Advisory Council Sci | Production of laminated structures |
US2402770A (en) * | 1943-08-21 | 1946-06-25 | Curtiss Wright Corp | Anti-icing means for aircraft propellers |
US2406367A (en) * | 1944-11-10 | 1946-08-27 | Honorary Advisory Council Sci | Prevention and removal of ice or frost on aircraft parts |
US2423945A (en) * | 1944-11-03 | 1947-07-15 | Technical Products Company | Electrolytic steam pad for ironing boards |
-
1947
- 1947-03-12 US US734141A patent/US2464273A/en not_active Expired - Lifetime
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Publication number | Priority date | Publication date | Assignee | Title |
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US1846468A (en) * | 1930-08-29 | 1932-02-23 | James A Benson | Aeroplane propeller |
US2055099A (en) * | 1934-06-06 | 1936-09-22 | Virginio J Gentile | Permanent waving sachet |
US2309682A (en) * | 1939-06-27 | 1943-02-02 | Gerrit Van Daam | Means for heating wings of airplanes |
US2297540A (en) * | 1941-06-05 | 1942-09-29 | Edward A Driscoll | Prevention of ice formation |
US2393100A (en) * | 1943-08-06 | 1946-01-15 | Honorary Advisory Council Sci | Production of laminated structures |
US2402770A (en) * | 1943-08-21 | 1946-06-25 | Curtiss Wright Corp | Anti-icing means for aircraft propellers |
US2423945A (en) * | 1944-11-03 | 1947-07-15 | Technical Products Company | Electrolytic steam pad for ironing boards |
US2406367A (en) * | 1944-11-10 | 1946-08-27 | Honorary Advisory Council Sci | Prevention and removal of ice or frost on aircraft parts |
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2643206A (en) * | 1949-09-28 | 1953-06-23 | Wingfoot Corp | Package for shipping and storing a conductive rubber heating element and method of making same |
US2695146A (en) * | 1951-06-21 | 1954-11-23 | Gen Motors Corp | Aircraft propeller blade with deicing means |
US2762897A (en) * | 1951-06-28 | 1956-09-11 | Lockheed Aircraft Corp | De-icing means for aircraft and the like |
US2757273A (en) * | 1952-12-12 | 1956-07-31 | Goodyear Tire & Rubber | De-icer |
US2680185A (en) * | 1953-04-17 | 1954-06-01 | Anthony X Basile | Heater gasket |
US2992317A (en) * | 1957-10-14 | 1961-07-11 | Goodrich Co B F | Electrically heated ice-removal apparatus |
US6237874B1 (en) | 1997-09-22 | 2001-05-29 | Northcoast Technologies | Zoned aircraft de-icing system and method |
US6194685B1 (en) | 1997-09-22 | 2001-02-27 | Northcoast Technologies | De-ice and anti-ice system and method for aircraft surfaces |
US5934617A (en) * | 1997-09-22 | 1999-08-10 | Northcoast Technologies | De-ice and anti-ice system and method for aircraft surfaces |
US6279856B1 (en) | 1997-09-22 | 2001-08-28 | Northcoast Technologies | Aircraft de-icing system |
US6330986B1 (en) | 1997-09-22 | 2001-12-18 | Northcoast Technologies | Aircraft de-icing system |
US20110296811A1 (en) * | 2010-06-03 | 2011-12-08 | Rolls-Royce Plc | Heat transfer arrangement for fluid-washed surfaces |
US8915058B2 (en) * | 2010-06-03 | 2014-12-23 | Rolls-Royce Plc | Heat transfer arrangement for fluid-washed surfaces |
US20150114945A1 (en) * | 2013-10-30 | 2015-04-30 | Goodrich Corporation | Electrical interconnects for ice protection systems |
US9868536B2 (en) * | 2013-10-30 | 2018-01-16 | Goodrich Corporation | Electrical interconnects for ice protection systems |
US20210284345A1 (en) * | 2020-03-16 | 2021-09-16 | Ratier-Figeac Sas | Deicer aerodynamic integration |
EP3882131A1 (en) * | 2020-03-16 | 2021-09-22 | Ratier-Figeac SAS | Improvement deicer aerodynamic integration |
US20210309376A1 (en) * | 2020-04-07 | 2021-10-07 | Goodrich Corporation | Integrated busbar heater for ice protection systems |
US11975850B2 (en) * | 2020-04-07 | 2024-05-07 | Goodrich Corporation | Integrated busbar heater for ice protection systems |
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