The present application relates to a heat generating side window, for a vehicle, comprising: a substrate comprising an upper edge, a lower edge, a front edge and a rear edge; a heat generating member positioned adjacently to the substrate; an upper busbar positioned on the heat generating member and electrically connected to the heat generating member; and a lower busbar positioned on the heat generating member and electrically connected to the heat generating member.

A heatable leading-edge apparatus for an aircraft having a main structure and a heating layer. The heating layer comprises a fiber composite layer with fibers and with a matrix which surrounds the fibers. The fibers are at least partially formed as conducting fibers, such as carbon fibers, with an electrically insulating coating. Owing to the conducting fibers, which act as electrical heating elements, a desired surface temperature can be established on an outer side of the leading-edge apparatus.

A defrosting system for defrosting an evaporator assembly is disclosed. The system includes the evaporator assembly, an electrically resistive coating having an electrically insulative matrix and a conductive doping agent disposed on at least one surface of the evaporator assembly, and a plurality of electrical terminals arranged and disposed to supply electricity to the electrically resistive coating. A method for defrosting an evaporator assembly and a coating for heating evaporator assemblies are also disclosed.

A ventilation door device for a refrigerator comprises: a frame, having an end plate provided with an opening portion, and having a blocking plate assembly rotatably mounted on the end plate, wherein the blocking plate assembly can rotate between a closed position in which the opening portion is completely closed and an open position in which the opening portion is completely open; a housing, engaging with the frame, wherein a driving chamber is formed between the housing and the frame; and a driving module, wherein the driving module is at least partially held in the driving chamber, and drives the blocking plate assembly to rotate. The frame has a housing engagement portion located on a side edge of the end plate and extending substantially perpendicular to the end plate. The housing is connected to the housing engagement portion of the frame. The blocking plate assembly comprises a blocking plate mounted on the end plate and an elastic component provided on the blocking plate. When the blocking plate assembly is in the closed position, the elastic component abuts the frame and deforms elastically to seal the opening portion. The end plate of the frame has a sealing portion arranged around the opening portion and protruding from the end plate. When the blocking plate assembly is in the closed position, the elastic component abuts the sealing portion of the frame.

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.

Disclosed is a heating device, including a substrate, a metal oxide layer formed on the substrate, hyper heat accelerator dots having a spherical shape formed on the metal oxide layer and arranged in a lattice form, and a conductive adhesive layer formed on the metal oxide layer and the hyper heat accelerator dots, wherein the lower portions of the hyper heat accelerator dots having a spherical shape are included in the metal oxide layer and the upper portions thereof are included in the conductive adhesive layer.

A pseudo sheet structure is usable for a sensor configured to emit an electromagnetic wave in a band ranging from 20 GHz to 100 GHz. The pseudo sheet structure includes a plurality of conductive linear bodies arranged at an interval L satisfying a formula (1) below, 0.034×λ.sub.S≤L≤20 mm (1). In the formula (1), L is the interval between the plurality of conductive linear bodies, λ.sub.S is a wavelength of the electromagnetic wave emitted by the sensor, and a unit for each of L and λ.sub.S is mm.

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. The structure further includes for and aft composite structures. The first and second encapsulation layer thermoplastic materials have higher melting temperatures that one or both the fore composite structure thermoplastic material and the aft composite structure thermoplastic material.

An airfoil (100) comprises a skin (110), comprising an external surface (112) and an internal surface (114), opposite the external surface (112). The skin (110) is magnetically and electrically conductive. The airfoil (100) also comprises an interior space (108), formed by the skin (110). The internal surface (114) faces the interior space (108). The airfoil (100) additionally comprises a leading edge (106) along the external surface (112). The airfoil (100) further comprises a hybrid acoustic induction-heating system (102), configured to impede formation of ice on the external surface (112). The hybrid acoustic induction-heating system (102) comprises an induction coil (130) within the interior space (108). At least a portion (136) of the induction coil (130) is sufficiently close to the internal surface (114) to produce an eddy current (180) in the skin (110) when an alternating electrical current (134) is flowing in the induction coil (130). The hybrid acoustic induction-heating system (102) also comprises at least one magnet (140) within the interior space (108). At least the one magnet (140) is configured to produce a steady-state magnetic field (182) within the skin (110).

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.