A piece of aeronautic equipment intended to equip an aircraft, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (25a) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

A combination of liquid-to-air and air-to-liquid heat exchangers is employed in an aircraft anti-icing system configured to avoid ice buildup on exterior leading edges of wings and engine inlets of aircraft during flight under known or anticipated icing conditions. The anti-icing system may be utilized in lieu of traditionally employed air-to-air heat exchangers. In one embodiment, a heated anti-icing liquid is conveyed through tubes juxtaposed against interior surfaces of the leading edges of the wings and engine inlets. The liquid is heated by engine core bleed air, and the tubes are arranged to optimize heat flux directly from the tubes into the leading edges of the wings and the engine inlets, respectively, to avoid ice accumulation. In one configuration, spring clips retain the tubes directly against the leading edge interiors of the wings and engine inlets, and thermal grease and insulation are used to enhance heat flux.

A method for producing a nacelle inlet assembly includes forming a composite panel that has a carbon fiber reinforced polymer (CFRP) material. The composite panel is formed to have a curved contour that represents at least a portion of an annular barrel shape. The method includes applying a metallic coating to the composite panel to form a lipskin. The metallic coating is applied such that the metallic coating defines an exterior surface of the lipskin and the composite panel defines an interior surface of the lipskin. The method includes laser drilling a plurality of perforations through the lipskin. The laser drilling involves emitting a laser beam that impinges upon the interior surface of the lipskin and penetrates the CFRP material of the composite panel before penetrating the metallic coating and exiting the lipskin through the exterior surface.

A method for producing a nacelle inlet assembly includes forming a composite panel that has a carbon fiber reinforced polymer (CFRP) material. The composite panel is formed to have a curved contour that represents at least a portion of an annular barrel shape. The method includes applying a metallic coating to the composite panel to form a lipskin. The metallic coating is applied such that the metallic coating defines an exterior surface of the lipskin and the composite panel defines an interior surface of the lipskin. The method includes laser drilling a plurality of perforations through the lipskin. The laser drilling involves emitting a laser beam that impinges upon the interior surface of the lipskin and penetrates the CFRP material of the composite panel before penetrating the metallic coating and exiting the lipskin through the exterior surface.

In certain embodiments, the invention is directed to apparatus comprising a liquid-impregnated surface, said surface comprising an impregnating liquid and a matrix of solid features spaced sufficiently close to stably contain the impregnating liquid therebetween or therewithin, and methods thereof. In some embodiments, one or both of the following holds: (i) 0<??0.25, where ? is a representative fraction of the projected surface area of the liquid-impregnated surface corresponding to non-submerged solid at equilibrium; and (ii) S.sub.ow(a)<0, where S.sub.ow(a) is spreading coefficient, defined as ?.sub.wa??.sub.wo??.sub.oa, where ? is the interfacial tension between the two phases designated by subscripts w, a, and o, where w is water, a is air, and o is the impregnating liquid.

In certain embodiments, the invention is directed to apparatus comprising a liquid-impregnated surface, said surface comprising an impregnating liquid and a matrix of solid features spaced sufficiently close to stably contain the impregnating liquid therebetween or therewithin, and methods thereof. In some embodiments, one or both of the following holds: (i) 0<??0.25, where ? is a representative fraction of the projected surface area of the liquid-impregnated surface corresponding to non-submerged solid at equilibrium; and (ii) S.sub.ow(a)<0, where S.sub.ow(a) is spreading coefficient, defined as ?.sub.wa??.sub.wo??.sub.oa, where ? is the interfacial tension between the two phases designated by subscripts w, a, and o, where w is water, a is air, and o is the impregnating liquid.

The present disclosure provides a device for de-icing an air intake lip of an aircraft turbojet engine nacelle. The de-icing device includes a de-icing circuit in which a heat transfer fluid, working in a two-phase form, circulates. The de-icing circuit includes at least one device for circulating the heat transfer fluid in the de-icing circuit, a system for heating the heat transfer fluid and configured to change the phase of the fluid to a vapor phase, and an inlet conduit that opens into the lip through a rear wall and injects the vapor phase fluid into the lip. The fluid changes phase when it condenses on the front wall of the lip to de-ice the lip.

The present disclosure provides a device for de-icing an air intake lip of an aircraft turbojet engine nacelle. The de-icing device includes a de-icing circuit in which a heat transfer fluid, working in a two-phase form, circulates. The de-icing circuit includes at least one device for circulating the heat transfer fluid in the de-icing circuit, a system for heating the heat transfer fluid and configured to change the phase of the fluid to a vapor phase, and an inlet conduit that opens into the lip through a rear wall and injects the vapor phase fluid into the lip. The fluid changes phase when it condenses on the front wall of the lip to de-ice the lip.

An aircraft provided with at least one piece of aeronautic equipment, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (70) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

An aircraft provided with at least one piece of aeronautic equipment, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (70) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section.