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 system for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component, the system comprising:
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 incorporated into the system.
2. The system according to claim 1 , wherein the insulation layer has a width and thickness and at least one of the width and thickness is not constant.
3. The system according to claim 2 , wherein the thickness of the insulation layer is varied.
4. The system according to claim 1 , wherein the density of the insulation layer is varied.
5. The system according to claim 1 , wherein the watt density varies in the heating element layer.
6. The system according to claim 1 , wherein the system comprises at least first and second zones that each comprise the heating element layer, the at least one thermally conductive adhesive layer, the insulation layer, the at least one thermally insulating adhesive layer, and the at least one temperature sensor, and the first and second zones are configured to provide either an anti-icing or a de-icing function independently of each other.
7. The system according to claim 1 , wherein the heating element layer is a graphite-based electrically resistive element.
8. The system according to claim 7 , wherein the heating element layer has carbon nano-tube additives.
9. The system according to claim 1 , wherein the heating element layer, the at least one thermally conductive adhesive layer, the insulation layer, the at least one thermally insulating adhesive layer, and the at least one temperature sensor are in the form of at least two strips.
10. The system according to claim 9 , wherein the strips are formed into an interleaved serpentine shape.
11. The system according to claim 9 , wherein each of the strips is independently attached to a power supply.
12. The system according to claim 1 , wherein the component is part of an aircraft.
13. The system according to claim 12 , wherein the component is a nacelle inlet lip.