A heating element and conductive element system may include a heater conductive element and a heating element. The heater conductive element and the heating element may be integral components. The heater conductive element and the heating element may be discrete components. The heater conductive element may be configured for enhanced mechanical fatigue compared to typical conductive element.

A heating element and conductive element system may include a heater conductive element and a heating element. The heater conductive element and the heating element may be integral components. The heater conductive element and the heating element may be discrete components. The heater conductive element may be configured for enhanced mechanical fatigue compared to typical conductive element.

An assembly is provided for a structure. This assembly includes a composite skin and a thermal anti-icing system. The composite skin extends between an exterior surface and an interior surface. The thermal anti-icing system includes a susceptor and a waveguide. The susceptor and the waveguide are integrated into the composite skin between the exterior surface and the interior surface. The waveguide is configured to direct microwaves to the susceptor for melting and/or preventing ice accumulation on the exterior surface.

An assembly is provided for an aircraft structure. This aircraft structure assembly includes an acoustic panel and a thermal anti-icing system. The acoustic panel includes an exterior surface. The thermal anti-icing system includes a susceptor and a microwave system. The susceptor is configured with the acoustic panel. The microwave system is configured to direct microwaves to the susceptor for melting and/or preventing ice accumulation on the exterior surface.

An assembly is provided for an aircraft structure. This aircraft structure assembly includes an acoustic panel and a thermal anti-icing system. The acoustic panel includes an exterior surface. The thermal anti-icing system includes a susceptor and a microwave system. The susceptor is configured with the acoustic panel. The microwave system is configured to direct microwaves to the susceptor for melting and/or preventing ice accumulation on the exterior surface.

Configurations are described that provide uniform heat distribution of resistive heaters. These configurations allow successful anti-icing and deicing with relatively low applied power. One aspect involves the use of a thin film heater applied just underneath the topcoat to efficiently direct all heat to the surface, allowing anti-icing and de-icing with minimal power. This can be accomplished by employing a hybrid electrode interface, using a metal foil or metal braid that is attached to the aircraft surface with a structural adhesive that has been smoothed along the edges with metal-filled adhesive. Another aspect uses an array of heater cells created as a single sheet and a heat spreading material, provided underneath or overtop of the heater cells.

Configurations are described that provide uniform heat distribution of resistive heaters. These configurations allow successful anti-icing and deicing with relatively low applied power. One aspect involves the use of a thin film heater applied just underneath the topcoat to efficiently direct all heat to the surface, allowing anti-icing and de-icing with minimal power. This can be accomplished by employing a hybrid electrode interface, using a metal foil or metal braid that is attached to the aircraft surface with a structural adhesive that has been smoothed along the edges with metal-filled adhesive. Another aspect uses an array of heater cells created as a single sheet and a heat spreading material, provided underneath or overtop of the heater cells.

A method of making an adhesive for an ice protection assembly includes transferring Z-CNTs from a substrate carrier into the adhesive. De-bonding of the adhesive for ice protection assembly inspection or repair or repositioning at initial installation includes heating the Z-CNTs in the adhesive to soften the adhesive and allow for easy removal.

A method of making an adhesive for an ice protection assembly includes transferring Z-CNTs from a substrate carrier into the adhesive. De-bonding of the adhesive for ice protection assembly inspection or repair or repositioning at initial installation includes heating the Z-CNTs in the adhesive to soften the adhesive and allow for easy removal.

The present invention relates to an apparatus and method for detecting the presence of water or ice on a structure, for example on the surface of an aircraft. A plurality of heaters (202-214) are thermally coupled to a structure (for example on the back of a wing) (104) in order to detect the presence of water or ice on the structure. The heaters are arranged adjacent one another from a GC region of a leading edge (106) of the structure (that is exposable to an impinging airflow) and extending aft of the leading edge of the structure. The heaters, which may be controlled individually, are supplied power that is sufficient to heat the surface of the structure to substantially the same temperature. A controller senses the power required for the heaters to achieve the same surface temperature at the respective regions. By comparing the power consumed by a heater that is aft of the fore-most heater (214), and the power consumed by a heater fore of the aft-most heater (210), a determination of the presence of water or ice can be made if the power consumed by the heater that is aft of the fore- most heater is different to the power consumed by the heater that is fore of the aft-most heater.