Anti-icing system and method for preventing ice accumulation

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;
• and
• a 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;
• and
• an 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;
• and
• a 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.

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;
• and
• coupling 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.