An aircraft can include a turbine engine including a rotor and a stator, and also including a compressor, a combustor, and a turbine in axial flow arrangement. The aircraft can further include an anti-icing system with a magnetic field generator having a rotating portion and a non-rotating portion, as well as an array of carbon nanotubes thermally coupled to an exposed surface.

A field-connectable cable cap for a heating cable in which the cable cap includes a power indicator that illuminates when sufficient power is supplied to the distal end of the heating cable. The indicator gives an installer or a user an indication that the heating cable is functioning properly the entire length of the heating cable. The cable cap may further include a connection feature, such as an aperture, that provides a connection point for a cable pulling device such as a fish tape.

A frozen accumulation detection assembly and method of operation for a motor vehicle is provided. The assembly includes a light source for emitting light on a surface of the motor vehicle, such as running board, and a sensor for measuring a reflectance level of the light off of the surface of the motor vehicle. The assembly further includes a heating element coupled to the surface of the motor vehicle. The reflectance level may be used as an indicator of frozen accumulation on the surface of the motor vehicle, and may help determine if the heating element should be energized.

In an embodiment, a heating device comprises a radiation source that emits a source radiation, a radiation emitting layer comprising an emitting layer host material and a luminescent agent, wherein the radiation emitting layer comprises an edge, an emitting layer first surface, and an emitting layer second surface; wherein the radiation source is coupled to the edge, wherein the source radiation is transmitted from the radiation source through the edge and excites the luminescent agent, whereafter the luminescent agent emits an emitted radiation, wherein at least a portion of the emitted radiation exits through the emitting layer second surface through an escape cone; an absorber layer, wherein the absorber layer comprises an absorber layer first surface and wherein the absorber layer first surface is in direct contact with the emitting layer second surface, wherein the absorber layer comprises an absorber that absorbs emitted radiation that escapes through the escape cone.

Heated platform systems are disclosed herein. Heated platform systems according to the present disclosure include a fiber reinforced panel that has a heating element that is made from a plurality of conductive mats. The plurality of conductive mats are placed into electrical continuity with one another by electrical leads, and are electrically isolated from one another by electrical insulating interleaf layers that prevent electrical shunting of adjacent conductive mats.

A lamp or lens assembly for a motor vehicle that includes electrically conductive traces for defogging or deicing the lens. Aspects include a light transmissive lens coupled to a lamp housing. The light transmissive lens may define a curved cross-section with a curvature extending across the length and/or the width of the lens. The lens may include one or more electrically conductive traces positioned on a surface of the lens, the electrically conductive traces optionally extending across and curving with the curvature of the light transmissive lens. One or more coatings may optionally cover the conductive traces and a portion of the lens surface leaving portions uncovered. The electrically conductive traces may extend outwardly away from the surface of the lens with height that is greater than their width.

A heater mat assembly for a rotor blade spar is provided including a plurality of electrically conductive heater wires extending in a spaced parallel configuration along a path of the rotor blade spar. An electrical current is flowed through the plurality of heater wires to inhibit ice accumulation on a portion of the rotor blade spar. At least one layer of a first insulating material is arranged adjacent a first side of each of the plurality of heater wires such that the at least one layer of the first insulating material is disposed between the plurality of heater wires and an adjacent surface of the rotor blade spar. The first insulating material comprises a thermally and electrically insulating material.

Within examples, systems for multiple zone heaters for rotor craft are provided and methods for operation. An example system for a rotor craft comprises multiple blades coupled to a rotor and areas of the multiple blades divided into sections. A given blade includes an inboard section extending from the rotor outward and an outboard section extending from the inboard section to a tip of the given blade. The system also includes a plurality of first spanwise heater systems included on respective outboard sections of the multiple blades, a plurality of second spanwise heater systems included on respective inboard sections of the multiple blades, and a control unit coupled to the plurality of first spanwise heater systems and the plurality of second spanwise heater systems. Respective heater systems of the sections of multiple blades are energized in a sequence based on outside air temperature.

A method of determining ice accretion on a surface of an aircraft can include supplying a known power to a heating element formed in a patch, wherein the patch includes a temperature sensor. A controller module can compare a sensed thermal signature with a threshold signature and determine the presence of ice accretion on the aircraft.

A resistive heating circuit for a heated or ice protected aircraft structure includes a flexible dielectric substrate, a resistive heating element supported by the substrate, and a bus bar. The bus bar is electrically connected to the resistive heating element and includes a conductive ink printed onto the substrate such that the bus bar and resistive heating element flex freely with the heated or ice protected aircraft structure. Heated or ice protected aircraft structures and methods of making resistive heating circuits for heated or ice protected aircraft structures are also described.