An angle of attack sensor includes a vane assembly and a multi-piece faceplate adjacent the vane assembly. The faceplate includes a heated chassis defining a pocket and a mounting plate positioned adjacent the heated chassis and having an opening. The vane assembly has a portion that is positioned in the pocket of the heated chassis and extends through the opening of the mounting plate.

An angle of attack sensor includes a vane assembly and a multi-piece faceplate adjacent the vane assembly. The faceplate includes a heated chassis defining a pocket and a mounting plate positioned adjacent the heated chassis and having an opening. The vane assembly has a portion that is positioned in the pocket of the heated chassis and extends through the opening of the mounting plate.

An angle of attack sensor includes a vane assembly and a multi-piece faceplate adjacent the vane assembly. The faceplate includes a heated chassis defining a pocket and a mounting plate positioned adjacent the heated chassis and having an opening. The vane assembly has a portion that is positioned in the pocket of the heated chassis and extends through the opening of the mounting plate.

An aircraft wing may comprise an airfoil having deicing zone, an anti-icing zone, and an ice runback control zone. An aircraft wing may comprise an electro-thermal ice protection system disposed in the aircraft wing. The electro-thermal ice protection system may be disposed along the deicing, anti-icing, and ice runback control zones of the airfoil to improve aerodynamic performance of the aircraft and reduce ice formation along the wings of the aircraft.

An aircraft wing may comprise an airfoil having deicing zone, an anti-icing zone, and an ice runback control zone. An aircraft wing may comprise an electro-thermal ice protection system disposed in the aircraft wing. The electro-thermal ice protection system may be disposed along the deicing, anti-icing, and ice runback control zones of the airfoil to improve aerodynamic performance of the aircraft and reduce ice formation along the wings of the aircraft.

An air date probe includes a strut assembly extending from a base, and a tube assembly coupled to the strut assembly. One or both of the strut assembly and the tube assembly comprises a self-regulating thin film heating arrangement. The self-regulating thin film heating arrangement includes at least one circuit including a positive temperature coefficient (PTC) heating element connected in series with a negative temperature coefficient (NTC) heating element.

A method for operating a frost treatment system including a first heating mat, covering a first zone and an intermediate zone of a second zone, operating alternately at a first energy level adjusted to maintain a first positive temperature on the first zone and a negative temperature on at least a part of the intermediate zone and at a second energy level adjusted to generate a positive temperature on the intermediate zone, a second heating mat covering the second zone apart from the intermediate zone and ensuring the defrosting function for the zone. This solution makes it possible to reduce the energy consumption of the first heating mat by reducing the energy level at which it is powered for most of the time. Also, an outer wall of an aircraft is provided including at least one frost treatment system operating according to this method.

A method for operating a frost treatment system including a first heating mat, covering a first zone and an intermediate zone of a second zone, operating alternately at a first energy level adjusted to maintain a first positive temperature on the first zone and a negative temperature on at least a part of the intermediate zone and at a second energy level adjusted to generate a positive temperature on the intermediate zone, a second heating mat covering the second zone apart from the intermediate zone and ensuring the defrosting function for the zone. This solution makes it possible to reduce the energy consumption of the first heating mat by reducing the energy level at which it is powered for most of the time. Also, an outer wall of an aircraft is provided including at least one frost treatment system operating according to this method.

An ice protection system and method capable of anti-icing and de-icing aerodynamic structures and surfaces is provided comprising a Resistive Heat Coat (RHC) controller and a heating device. The RHC controller comprises a RHC power circuit topology having a processor and a buck converter. The RHC controller further comprises a RHC control algorithm. The heating device comprises a plurality of resistive heating elements, such as CNT-based resistive heaters. The ice protection systems and methods disclosed can achieve an efficiency of 98% or greater while employing a direct current (DC) power supply and “hard switching” with a switching frequency of at least 500 kHz.

An ice protection system and method capable of anti-icing and de-icing aerodynamic structures and surfaces is provided comprising a Resistive Heat Coat (RHC) controller and a heating device. The RHC controller comprises a RHC power circuit topology having a processor and a buck converter. The RHC controller further comprises a RHC control algorithm. The heating device comprises a plurality of resistive heating elements, such as CNT-based resistive heaters. The ice protection systems and methods disclosed can achieve an efficiency of 98% or greater while employing a direct current (DC) power supply and “hard switching” with a switching frequency of at least 500 kHz.