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.

A light aerial vehicle laminated glazing includes a structural transparent plastic sheet covering the whole of the surface of the glazing, a protective transparent plastic sheet covering the whole of the surface of the glazing, an interlayer adhesive bonding the structural and protective sheets, a glass covered with a conductive layer having a heating function incorporated within the adhesive and covering a fraction of the surface of the glazing at most equal to 66% containing the main viewing zone.

Disclosed is a first method of providing a heating system to an outer skin of an aircraft, that has the steps of forming laser-induced graphene (LIG) on a polymer sheet by directing laser energy towards the polymer sheet; coupling electrical leads to the LIG; and bonding the polymer sheet against the outer skin or erosion protection layer secured to the outer skin so that to the polymer sheet conforms with a shape of the outer skin.

Disclosed is a first method of providing a heating system to an outer skin of an aircraft, that has the steps of forming laser-induced graphene (LIG) on a polymer sheet by directing laser energy towards the polymer sheet; coupling electrical leads to the LIG; and bonding the polymer sheet against the outer skin or erosion protection layer secured to the outer skin so that to the polymer sheet conforms with a shape of the outer skin.

An electric aircraft includes a propeller, an electric motor, and a controller. The electric motor is configured to supply power to the propeller. The controller is configured to control the electric motor. The controller is disposed inside a leading-edge portion of a wing to cause heat to be transmitted to a skin of the wing. The heat is generated by the controller when the controller controls the electric motor.

An electric aircraft includes a propeller, an electric motor, and a controller. The electric motor is configured to supply power to the propeller. The controller is configured to control the electric motor. The controller is disposed inside a leading-edge portion of a wing to cause heat to be transmitted to a skin of the wing. The heat is generated by the controller when the controller controls the electric motor.

A system, power management system and method are disclosed. The power management system includes a pitot tube, one or more heating elements disposed in the pitot tube, and one or more power switches, wherein each power switch of the one or more power switches is coupled to a respective heating element and configured to energize or de-energize the respective heating element in response to a control signal. The power management system also includes a temperature detector coupled to the pitot tube and configured to determine a temperature of the pitot tube, and a processor complex coupled to the one or more power switches and the temperature detector and configured to output the control signal to energize or de-energize at least one of the heating elements through a respective at least one of the respective one or more power switches in response to at least the determined temperature of the pitot tube or a detection of a fault.

A system, power management system and method are disclosed. The power management system includes a pitot tube, one or more heating elements disposed in the pitot tube, and one or more power switches, wherein each power switch of the one or more power switches is coupled to a respective heating element and configured to energize or de-energize the respective heating element in response to a control signal. The power management system also includes a temperature detector coupled to the pitot tube and configured to determine a temperature of the pitot tube, and a processor complex coupled to the one or more power switches and the temperature detector and configured to output the control signal to energize or de-energize at least one of the heating elements through a respective at least one of the respective one or more power switches in response to at least the determined temperature of the pitot tube or a detection of a fault.

A method for installing a replacement electrical heat sensor in a heatable aircraft window laminate structure comprising the steps of: drilling a blind hole in the edge of the window laminate; routing a channel in the edge of the window laminate from the blind hole to a terminal block of an originally installed heat sensor; inserting the replacement heat sensor into the hole; filling the hole with a material to seal the hole and the heat sensor from contamination; heating the window laminate; photographing the window laminate using an infrared camera to determine uniformity of heat distribution; placing a heated plate against the exterior surface of the window laminate directly over the position of the replacement heat sensor; measuring an electrical resistance of the replacement heat sensor to confirm proper operation of the replacement heat sensor.

A method for installing a replacement electrical heat sensor in a heatable aircraft window laminate structure comprising the steps of: drilling a blind hole in the edge of the window laminate; routing a channel in the edge of the window laminate from the blind hole to a terminal block of an originally installed heat sensor; inserting the replacement heat sensor into the hole; filling the hole with a material to seal the hole and the heat sensor from contamination; heating the window laminate; photographing the window laminate using an infrared camera to determine uniformity of heat distribution; placing a heated plate against the exterior surface of the window laminate directly over the position of the replacement heat sensor; measuring an electrical resistance of the replacement heat sensor to confirm proper operation of the replacement heat sensor.