| 摘要 |
A system 44 for ice protection of an aircraft component 46, such as a lip 42 of an engine nacelle 34, is adhesively bonded to a surface of the component. The system includes a heating element layer 48, at least one thermally conductive adhesive layer 52 that adhesively bonds a first side of the heating element layer to the component, an insulation layer 56, at least one thermally insulating adhesive layer 58 that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar 62 adapted to provide a connection between a power supply and the heating element layer and at least one temperature sensor 54. |
