Abstract: An ice protection system for an aircraft component includes a plurality of heaters. The aircraft component has at least two section and a junction area. At least one of the heaters is an H-shape carbon allotrope heater designed to apply heat to the junction area and prevent ice accumulation in the junction area.

Abstract: A system for controlling a multi-zone resistive heater. The system includes a first zone of the multi-zone resistive heater formed from a material having a negative temperature coefficient of resistivity (TCR) and configured to receive a first power to generate thermal energy. The system further includes a second zone of the multi-zone resistive heater formed from the material having the negative TCR, separated from the first zone by a gap, and configured to receive a second power to generate the thermal energy.

Abstract: 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.

Abstract: 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.

Abstract: A system for controlling a multi-zone resistive heater. The system includes a first zone of the multi-zone resistive heater formed from a material having a negative temperature coefficient of resistivity (TCR) and configured to receive a first power to generate thermal energy. The system further includes a second zone of the multi-zone resistive heater formed from the material having the negative TCR, separated from the first zone by a gap, and configured to receive a second power to generate the thermal energy.

Abstract: 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.

Abstract: An aircraft may include a fuselage and a wing extending away from the fuselage to a wing tip. The wing may have a leading edge portion, a suction side portion, and a pressure side portion. A thermoelectric element may be coupled to an inner surface of the wing. A chemical adhesive may be disposed on a thermoelectric inner surface. A structural rib may be adhesively bonded to the thermoelectric element by curing the chemical adhesive. The structural rib may be mechanically fastened to a suction side of the wing and to a pressure side of the wing.

Abstract: An ice protection system for an aircraft component includes a plurality of heaters. The aircraft component has at least two section and a junction area. At least one of the heaters is an H-shape carbon allotrope heater designed to apply heat to the junction area and prevent ice accumulation in the junction area.