Examples described herein provide a computer-implemented method that includes receiving static data about an aircraft. The method further includes receiving dynamic data about flight conditions for a flight of the aircraft. The method further includes determining, based on the static data and the dynamic data, an amount of air pressure and a volumetric air flow to apply from an electric pump to a deicing device. The method further includes controlling the electric pump to cause the electric pump to apply the amount of air pressure and the volumetric air flow to the deicing device.

Examples described herein provide a computer-implemented method that includes receiving static data about an aircraft. The method further includes receiving dynamic data about flight conditions for a flight of the aircraft. The method further includes determining, based on the static data and the dynamic data, an amount of air pressure and a volumetric air flow to apply from an electric pump to a deicing device. The method further includes controlling the electric pump to cause the electric pump to apply the amount of air pressure and the volumetric air flow to the deicing device.

A static plate heating arrangement includes a faceplate including a port extending from an exterior surface of the faceplate to an interior surface of the faceplate, a fixed resistance heater in thermal communication with the interior surface and surrounding the port, and a self-regulating heater in thermal communication with the interior surface and surrounding the fixed resistance heater. The fixed resistance heater and the self-regulating heater are electrically connected in series.

A static plate heating arrangement includes a faceplate including a port extending from an exterior surface of the faceplate to an interior surface of the faceplate, a fixed resistance heater in thermal communication with the interior surface and surrounding the port, and a self-regulating heater in thermal communication with the interior surface and surrounding the fixed resistance heater. The fixed resistance heater and the self-regulating heater are electrically connected in series.

Aircraft headlight includes at least one light source; and a light transmissive cover, at least partially covering the at least one light source. The light transmissive cover includes a first layer made of a first material; a second layer made of a second material, which differs from the first material; and at least one electric heating wire for heating the light transmissive cover by passing an electric current through the electric heating wire. The at least one electric heating wire is embedded into the first layer.

An airfoil (200) comprises a skin (210), comprising an external surface (212) and an internal surface (214). The skin (210) has a controlled region (216). The airfoil (200) also comprises an interior space (208), formed by the skin (210). The airfoil (200) additionally comprises a hybrid acoustic induction-heating system (202), configured to impede formation of ice on the external surface (212). The hybrid acoustic induction-heating system (202) comprises an induction coil (230) and a control system (250). At least a portion (236) of the induction coil (230) is sufficiently close to the internal surface (214) to produce an eddy current (280) within the controlled region (216) when an alternating electrical current (234) is flowing in the induction coil (230). The control system (250) is configured to generate inductive heat and acoustic pressure in the controlled region (216) by supplying the alternating electrical current (234) to the induction coil (230) based, at least in part, on an ambient temperature of a layer of fluid (218) flowing over the external surface (212).

An airfoil (200) comprises a skin (210), comprising an external surface (212) and an internal surface (214). The skin (210) has a controlled region (216). The airfoil (200) also comprises an interior space (208), formed by the skin (210). The airfoil (200) additionally comprises a hybrid acoustic induction-heating system (202), configured to impede formation of ice on the external surface (212). The hybrid acoustic induction-heating system (202) comprises an induction coil (230) and a control system (250). At least a portion (236) of the induction coil (230) is sufficiently close to the internal surface (214) to produce an eddy current (280) within the controlled region (216) when an alternating electrical current (234) is flowing in the induction coil (230). The control system (250) is configured to generate inductive heat and acoustic pressure in the controlled region (216) by supplying the alternating electrical current (234) to the induction coil (230) based, at least in part, on an ambient temperature of a layer of fluid (218) flowing over the external surface (212).

A method (400) of impeding formation of ice on an exterior surface (104, 204, 304) of airfoil (100, 200, 300) is disclosed. The method (400) comprises detecting (402) first ambient conditions known to cause the ice to form on exterior surface (104, 204, 304). The method (400) also comprises supplying (404) inductive heat and acoustic pressure to exterior surface (104, 204, 304) when the first ambient conditions are detected. The method (400) additionally comprises detecting (406) second ambient conditions known to impede the ice from forming on exterior surface (104, 204, 304). The method (400) further comprises discontinuing (408) to supply the inductive heat and the acoustic pressure to exterior surface (104, 204, 304) when the second ambient conditions are detected.

A method (400) of impeding formation of ice on an exterior surface (104, 204, 304) of airfoil (100, 200, 300) is disclosed. The method (400) comprises detecting (402) first ambient conditions known to cause the ice to form on exterior surface (104, 204, 304). The method (400) also comprises supplying (404) inductive heat and acoustic pressure to exterior surface (104, 204, 304) when the first ambient conditions are detected. The method (400) additionally comprises detecting (406) second ambient conditions known to impede the ice from forming on exterior surface (104, 204, 304). The method (400) further comprises discontinuing (408) to supply the inductive heat and the acoustic pressure to exterior surface (104, 204, 304) when the second ambient conditions are detected.

A heated composite structure and a method for forming a heated composite structure. The structure includes carbon fibers embedded within a thermoplastic matrix. The carbon fibers are connected with first and second electrodes that are configured to be connected with an electric source such that applying current to the electrodes causes current to flow through the embedded carbon fibers to provide resistive heating sufficient to heat the composite structure to impede formation of ice on the composite structure.