초록

An anti-icing system includes a component surface having a composite structure including a composite layer, and at least one heating element formed within the composite layer, wherein the heating element is configured to provide a transfer of heat to the component surface.

대표청구항 ▼

1. An anti-icing system comprising: a non-metallic component member comprising: a non-metallic composite structure including a plurality of woven non-metallic composite layers;an outer surface and an interior surface, said outer surface exposed to icing conditions when said component member is insta

1. An anti-icing system comprising: a non-metallic component member comprising: a non-metallic composite structure including a plurality of woven non-metallic composite layers;an outer surface and an interior surface, said outer surface exposed to icing conditions when said component member is installed in use; anda leading tip, a first wall extending in an aft direction from said leading tip, and a second wall extending in the aft direction from said leading tip such that a cross-section of said component member is substantially U-shaped;a plurality of conductive heating elements positioned adjacent at least one composite layer of said plurality of non-metallic composite layers, said plurality of heating elements comprising an electrically conductive ribbon configured to provide a transfer of heat to said component member, wherein each of said plurality of heating elements extends axially in the aft direction from said leading tip along said first wall and along said second wall, each of said plurality of heating elements configured to conform to the substantially U-shaped cross-section of said component member; anda structural foam element coupled to said interior surface, said structural foam element configured to facilitate substantially preventing a loss of heat through said interior surface during said heat transfer, said structural foam element further configured to provide structural reinforcement to said component member. 2. An anti-icing system in accordance with claim 1, wherein said at least one composite layer comprises: a woven carbon-fiber matrix; andone of a thermoplastic bonding agent or a thermoset bonding agent;wherein said at least one heating element is positioned adjacent said at least one composite layer forming a unitary composite structure. 3. An anti-icing system in accordance with claim 1, wherein said at least one heating element is wound, woven, or distributed within said at least one composite layer. 4. An anti-icing system in accordance with claim 1, wherein said composite structure comprises a laminate structure including a plurality of layers, said at least one heating element received between said plurality of layers. 5. An anti-icing system in accordance with claim 1, further comprising a power source electrically coupled to said at least one heating element and configured to provide an electrical voltage across said at least one heating element. 6. An aircraft inlet cowl comprising: a non-metallic component member defining an air inlet duct, said non-metallic component member comprising: a non-metallic composite structure including a plurality of woven non-metallic composite layers;an outer surface and an interior surface, said outer surface exposed to icing conditions when said component member is installed in use; anda leading tip, an outer wall extending in an aft direction from said leading tip, and an inner wall extending in the aft direction from said leading tip such that a cross-section of said component member is substantially U-shaped; andan anti-icing system comprising: a plurality of conductive heating elements positioned adjacent at least one composite layer of said plurality of non-metallic composite layers, said plurality of heating elements comprising an electrically conductive ribbon configured to provide a transfer of heat to said component member, wherein each of said plurality of heating elements extends axially in the aft direction from said leading tip along said first wall and along said second wall, each of said plurality of heating elements configured to conform to the substantially U-shaped cross-section of said component member; anda structural foam element coupled to said interior surface, said structural foam element configured to facilitate substantially preventing a loss of heat through said interior surface during said heat transfer, said structural foam element further configured to provide structural reinforcement to said component member. 7. An aerodynamic surface in accordance with claim 6, wherein said at least one composite layer comprises: a woven carbon-fiber matrix; andone of a thermoplastic bonding agent or a thermoset bonding agent;wherein said at least one heating element is positioned adjacent said at least one composite layer forming a unitary composite structure. 8. An aerodynamic surface in accordance with claim 6, wherein said at least one heating element is wound, woven, or distributed within said at least one composite layer. 9. An aerodynamic surface in accordance with claim 6, wherein said composite structure comprises a laminate structure including a plurality of layers, said at least one heating element received between said plurality of layers. 10. An aerodynamic surface in accordance with claim 6, further comprising a power source electrically coupled to said at least one heating element and configured to provide an electrical voltage across said at least one heating element. 11. A method for substantially preventing accumulation of ice on an aerodynamic surface of a non-metallic composite structure, said method comprising: fabricating the non-metallic composite structure including a plurality of woven non-metallic composite layers, wherein the composite structure includes an outer surface and an interior surface, the outer surface being exposed to icing conditions when the composite structure is installed in use, and wherein the composite structure includes a leading tip, an outer wall extending in an aft direction from the leading tip, and an inner wall extending in the aft direction from the leading tip such that a cross-section of the composite structure is substantially U-shaped;positioning a plurality of conductive ribbon heating elements adjacent at least one composite layer of the a plurality of non-metallic composite layers, wherein positioning the plurality of heating elements includes axially orienting the plurality of heating elements such that each heating element extends in an aft direction from the leading tip along the inner wall and along the outer wall such that each of the plurality of heating elements is configured to conform to the substantially U-shaped cross-section of the composite structure;configuring the at least one heating element to provide a transfer of heat to the aerodynamic surface; andcoupling a structural foam element to the interior surface such that the structural foam element substantially reduces a loss of heat through the interior surface during the heat transfer, and such that the structural foam element provides structural reinforcement to the composite structure. 12. A method in accordance with claim 11, wherein fabricating a composite structure further comprises: forming a unitary composite structure by providing a woven carbon-fiber matrix, wherein the at least one heating element is positioned adjacent said at least one composite layer; andreinforcing the unitary composite structure using one of a thermoplastic bonding agent or a thermoset bonding agent. 13. A method in accordance with claim 11, wherein fabricating a composite structure further comprises fabricating a laminate structure including a plurality of layers, wherein the at least one heating element is received between the plurality of layers. 14. A method in accordance with claim 11, further comprises electrically coupling a power source to the at least one heating element, the power source configured to provide an electrical voltage across the at least one heating element.