[특허]Conducting-fiber deicing systems and methods

The Boeing Company

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Conducting-fiber deicing systems and methods

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	H05B-003/10
미국특허분류(USC)	219/201; 219/548; 244/134.R; 428/220
출원번호	US-0248501 (2005-10-12)
발명자 / 주소	Kismarton,Max U.
출원인 / 주소	The Boeing Company
대리인 / 주소	Lee & Hayes, PLLC
인용정보	피인용 횟수 : 16 인용 특허 : 24

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Conducting-fiber deicing systems and methods. In one embodiment, an assembly includes a surface subject to an accumulation of ice, the surface at least partially including a heating portion having a layer of multi-directional electrically-conductive fibers formed between first and second non-electrically conductive layers. The layer of electrically-conductive fibers is coupled to a power supply member and is adapted to conduct an electrical current such that the layer of electrically-conductive fibers, and at least one of the first and second non-electri...

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What is claimed is: 1. An assembly, comprising: a non-planar surface subject to an accumulation of ice, the non-planar surface at least partially including a heating portion having a non-planar layer of multi-directional electrically-conductive fibers formed between first and second non-electrically conductive layers, the non-planar layer of electrically-conductive fibers being operatively coupled to a power supply member along a non-planar engagement area that spans across the non-planar layer of electrically-conductive fibers, the non-planar layer of electrically-conductive fibers being configured to conduct an electrical current such that the non-planar layer of electrically-conductive fibers and at least one of the first and second non-electrically conductive layers of the heating portion are raised to an elevated temperature to at least partially inhibit the accumulation of ice on the non-planar surface. 2. The assembly of claim 1, wherein the surface comprises a leading edge portion of an aerodynamically-shaped member. 3. The assembly of claim 1, wherein the surface comprises a leading edge portion of an aerodynamically-shaped member having a first portion and a second portion separated by a stagnation point, and wherein the heating portion extends at least partially along the first and second portions. 4. The assembly of claim 1, wherein the non-planar layer of electrically-conductive fibers comprises a concave layer that extends along a longitudinal direction, and wherein the non-planar engagement area comprises an approximately U-shaped cross-sectional portion of the longitudinally-extending concave layer. 5. The assembly of claim 4, wherein the layer of electrically-conductive fibers is further coupled to at least one grounding strip that spans across the layer of electrically-conductive fibers approximately parallel with the engagement area. 6. The assembly of claim 5, wherein the power supply member comprises a first braided conductive member and wherein the at least one grounding strip comprises a first grounding strip, the assembly further comprising a second grounding strip coupled to the layer of electrically-conductive fibers, the second grounding strip spanning across the layer of electrically-conductive fibers and being approximately parallel with the first grounding strip. 7. An assembly, comprising: an aerodynamically-shaped member having a leading edge portion including a non-planar outer surface subject to an accumulation of ice; and a deicing system operatively coupled to the aerodynamically-shaped member, the deicing system including a heating portion having a non-planar layer of multi-directional electrically-conductive fibers formed between first and second non-electrically conductive layers, the first non-electrically conductive layer at least one of forming a portion of the non-planar outer surface and being proximate to the non-planar outer surface, the non-planar layer of electrically-conductive fibers being operatively coupled to a power supply device along a non-planar engagement area that spans across the non-planar layer of electrically-conductive fibers, the non-planar layer of electrically-conductive fibers being configured to conduct an electrical current such that the non-planar layer of electrically-conductive fibers and the non-planar outer surface are raised to an elevated temperature to at least partially inhibit the accumulation of ice. 8. The assembly of claim 7, wherein the aerodynamically-shaped member comprises at least one of a rotor blade, a wing, a tail portion, and a control surface. 9. The assembly of claim 7, wherein the outer surface comprises a first portion and a second portion separated by a stagnation point, and wherein the heating portion extends at least partially along the first and second portions of the outer surface. 10. The assembly of claim 7, wherein the power supply member is coupled with a braided metal electrical cord to the engagement area. 11. The assembly of claim 7, wherein the power supply device comprises a plurality of conductive members operatively coupled to the layer of electrically-conductive fibers at a plurality of longitudinally spaced-apart engagement areas and defining a plurality of heating zones of the heating portion. 12. The assembly of claim 11, further comprising a controller operatively coupled to the plurality of conductive members and adapted to selectively provide independent electrical power to the plurality of heating zones. 13. The assembly of claim 12, wherein the plurality of heating zones are distributed along a longitudinal axis of the aerodynamically-shaped member, and wherein the controller is adapted to successively provide power to the plurality of heating zones from an outmost zone to an innermost zone. 14. An aircraft, comprising: a fuselage including a wing assembly and a tail assembly; a propulsion system operatively coupled to the fuselage; and wherein at least one of the fuselage and the propulsion system includes: an aerodynamically-shaped member having a leading edge portion including an outer surface subject to an accumulation of ice; and a deicing system operatively coupled to the aerodynamically-shaped member, the deicing system including a heating portion having a non-planar layer of multi-directional electrically-conductive fibers formed between first and second non-electrically conductive layers, the first non-electrically conductive layer at least one of forming a portion of the outer surface and being proximate to the outer surface, the non-planar layer of electrically-conductive fibers being operatively coupled to a power supply device along a non-planar engagement area that spans across the non-planar layer of electrically-conductive fibers the non-planar layer of electrically-conductive fibers being configured to conduct an electrical current such that the non-planar layer of electrically-conductive fibers and the outer surface are raised to an elevated temperature to at least partially inhibit the accumulation of ice. 15. The aircraft of claim 14, wherein the aerodynamically-shaped member comprises at least one of a rotor blade, a wing, a tail portion, and a control surface. 16. The aircraft of claim 14, wherein the non-planar layer of electrically-conductive fibers comprises a concave layer that extends along a longitudinal direction, and wherein the non-planar engagement area comprises an approximately U-shaped cross-sectional portion of the longitudinally-extending concave layer. 17. The aircraft of claim 14, wherein the power supply device comprises a plurality of conductive members operatively coupled to the layer of electrically-conductive fibers at a plurality of longitudinally spaced-apart engagement areas and defining a plurality of heating zones of the heating portion, and a controller operatively coupled to the plurality of conductive members and adapted to selectively provide electrical power to the plurality of heating zones. 18. A method of deicing a surface, comprising: providing a heating portion having a non-planar layer of multi-directional electrically-conductive fibers formed between first and second non-electrically conductive layers, the first non-electrically conductive layer at least one of forming a portion of the surface and being proximate to the surface; and providing an electrical current through the non-planar layer of electrically-conductive fibers to raise a temperature of the surface to at least partially inhibit an accumulation of ice, wherein providing an electrical current includes providing an electrical current through a non-planar engagement area that spans across the non-planar layer of electrically-conductive fibers. 19. The method of claim 18, wherein providing a heating portion includes providing a heating portion having a layer of multi-directional electrically-conductive fibers coupled to a plurality of conductive members at a plurality of longitudinally spaced-apart engagement areas and defining a plurality of heating zones of the heating portion, and wherein providing an electrical current through the layer of electrically-conductive fibers includes providing an electrical current through one or more of the plurality of heating zones. 20. The method of claim 19, wherein providing an electrical current through one or more of the plurality of heating zones includes successively providing an electrical current through each of the heating zones from an outermost zone to an innermost zone. 21. The method of claim 19, wherein the surface comprises a portion of a rotor blade of a rotary aircraft, the method further comprising rotating the rotor blade simultaneously with the providing the electrical current through one or more of the plurality of heating zones.

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Conducting-fiber deicing systems and methods

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