A multilayer heating structure for controlling ice accumulation on a surface of an aircraft includes a carbon nano-tube (CNT) heater. The heater includes: a CNT layer; a first encapsulation layer disposed on a first side of the CNT layer formed of a first encapsulation layer thermoplastic material; and a second encapsulation layer disposed on a second side of the CNT layer formed of a second encapsulation layer thermoplastic material.

A system for heating an aircraft surface having a thermally disadvantaged zone includes a carbon nano-tube (CNT) sheet heating element having a power inlet configured to receive power from an external electrical power source and provide it to the CNT sheet heating element that extends across the thermally disadvantaged zone. The CNT sheet heating element is configured and arranged such upon application of power from the external electrical power source to the CNT sheet heating element, the CNT sheet heating element produces a first heat output in a first zone and a second heat output in the thermally disadvantaged zone with the second heat output being greater than the first heat output.

A system for heating an aircraft surface having a thermally disadvantaged zone includes a carbon nano-tube (CNT) sheet heating element having a power inlet configured to receive power from an external electrical power source and provide it to the CNT sheet heating element that extends across the thermally disadvantaged zone. The CNT sheet heating element is configured and arranged such upon application of power from the external electrical power source to the CNT sheet heating element, the CNT sheet heating element produces a first heat output in a first zone and a second heat output in the thermally disadvantaged zone with the second heat output being greater than the first heat output.

A system for controlling ice accumulation on a surface of an aircraft, the system includes a carbon nano-tube (CNT) heater comprising: a CNT layer; a first encapsulation layer disposed on a first side of the CNT layer formed of a first encapsulation layer thermoplastic material; and a second encapsulation layer disposed on a second side of the CNT layer formed of a second encapsulation layer thermoplastic material. The system also includes a fore composite structure that includes a fore composite structure thermoplastic material disposed on the first side of CNT heater, an aft composite structure that includes an aft composite structure thermoplastic material disposed on the first side of CNT heater and a sensor layer disposed between the CNT heater and the one of the fore and aft composite structures.

A system for controlling ice accumulation on a surface of an aircraft, the system includes a carbon nano-tube (CNT) heater comprising: a CNT layer; a first encapsulation layer disposed on a first side of the CNT layer formed of a first encapsulation layer thermoplastic material; and a second encapsulation layer disposed on a second side of the CNT layer formed of a second encapsulation layer thermoplastic material. The system also includes a fore composite structure that includes a fore composite structure thermoplastic material disposed on the first side of CNT heater, an aft composite structure that includes an aft composite structure thermoplastic material disposed on the first side of CNT heater and a sensor layer disposed between the CNT heater and the one of the fore and aft composite structures.

Described herein are methods for forming resistive heaters and force sensing elements on a flexible substrate, and devices that include these elements to provide a force responsive conductive heater, such as a seat heater in a vehicle. The methods include printing a conductive ink on a flexible substrate that is heated to 30° C. to 90° C. before and/or during the printing process and curing the substrate to produce a conductive pattern thereon. The conductive inks generally include a particle-free metal-complex composition formulated from at least one metal complex and a solvent, and optionally, a conductive filler material.

The present disclosure is directed to a system comprising a structure being prone to lightning strikes and icing, wherein the structure comprises a shielding arrangement electrically connected to a lightning arrangement, an electric heating arrangement connected to a power source for mitigating icing of the structure, and an electrical insulation arrangement being effectively provided between the shielding arrangement and the electric heating arrangement. A power source is configured for applying a predetermined amount of electric test- and/or maintenance-energy such that the electric test- and/or maintenance-energy is effectively present between the shielding arrangement and the electric heating arrangement. A determination device is electrically connected to the shielding arrangement and to the electric heating arrangement in a way that the shield-heating-voltage and/or the shield-heating-current being present between the shielding arrangement and the electric heating arrangement can be determined.

An aircraft headlight includes at least one visible light source for emitting a headlight light output; a light transmissive cover, at least partially covering the at least one visible light source; and at least one infrared emitter for emitting infrared radiation. At least 90% of radiation energy, comprised in the infrared radiation emitted by the at least infrared emitter, is emitted within a predefined wavelength range; and the light transmissive cover allows at least 25%, in particular at least 30%, more particularly at least 45%, of the radiation energy, which is emitted within the predefined wavelength range, to pass through the light transmissive cover.

A system and method for monitoring the health of a heater connected to a power supply by first and second power leads which conduct an inlet and outlet current, respectively. The system includes an injection transformer with a number of primary turns that are inductively coupled to the first power lead, a signal generator configured to generate and supply a time-varying injection signal to the primary turns thereby imposing the time-varying injection signal on the inlet current, and a signal reader configured to receive a diagnostic signal from the heater, filter the diagnostic signal to pass a frequency associated with the time-varying injection signal, and produce a heater capacitance signal that is indicative of a capacitance value of the heater, where the heater capacitance signal is indicative of the health of the heater.

A probe head of an air data probe includes a body extending from a first end to a second end of the probe head and a rod heater. The body includes an inlet adjacent the first end of the probe head, an air passageway extending through the body from the inlet to a second end of the probe head, a water dam extending radially through the body such that the air passageway is redirected around the water dam, a heater bore extending within the body, and an enhanced conduction area between heater bore and an exterior surface of the probe head. The inlet, the air passageway, the water dam, and the heater bore are all unitary to the body. The rod heater is positioned within the heater bore.