Aircraft ice protection system and method
A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor.
1. A method of protecting a component on an aircraft from ice formation, the method comprising:
forming a heating element layer;
attaching an electrical bus bar to the heating element layer;
encapsulating the heating element layer, at least one thermal sensor, and the electrical bus bar to form a laminated structure, wherein a first thermally conductive adhesive layer is disposed at a first side of the laminated structure and a first thermally insulating adhesive layer is disposed at a second side of the laminated structure;
curing the laminated structure;
attaching an insulation layer to the second side of the laminated structure with a second thermally insulating adhesive layer;
attaching the laminated structure to the component with a second thermally conductive adhesive layer; and then
curing the laminated structure and insulation layer to yield a heating element architecture that is bonded to the component.
2. The method according to claim 1 , further comprising the step of cutting the laminated structure and insulation layer into more than one strip prior to curing to the component.
3. The method according to claim 2 , further comprising the step of forming the strips into a serpentine shape.
4. The method according to claim 2 , further comprising the step of independently connecting each strip to a power supply.
5. The method according to claim 1 , wherein the steps of claim 1 are repeated to form multiple independent zones each comprising a laminated structure.
6. The method according to claim 2 , wherein the component is a nacelle of the aircraft and the method further comprises operating the aircraft and removing ice buildup from an inlet lip of the nacelle with the heating element architecture.
7. The method according to claim 2 , wherein the component is a nacelle of the aircraft and the method further comprises operating the aircraft and preventing ice buildup on an inlet lip of the nacelle with the heating element architecture.