A method and device for reducing ice and frost on a surface comprising a wettable pattern on a surface. The pattern is wetted with water which is frozen into ice to create overlapping hygroscopic that cover the surface.

A method and device for reducing ice and frost on a surface comprising a wettable pattern on a surface. The pattern is wetted with water which is frozen into ice to create overlapping hygroscopic that cover the surface.

System for protecting an outer surface of an aircraft comprising at least two fuel cells (112, 212) from icing, characterized in that it comprises a first and a third liquid circuit (114, 214) each causing a cooling liquid of the fuel cells (112, 212) to flow, a second and a fourth liquid circuit (118a, 118b) each causing an icing protection liquid to flow, at least two icing protection heat exchangers (120a-d, 220a-d) arranged on the outer surface of the aircraft and having each icing protection liquid pass through them when it flows in the second or fourth liquid circuit (118a, 118b), and two liquid-liquid heat exchangers (116, 216) in which the cooling liquids form a hot pass and the icing protection liquids form a cold pass to reheat the icing protection liquid by the heat from the cooling liquids.

System for protecting an outer surface of an aircraft comprising at least two fuel cells (112, 212) from icing, characterized in that it comprises a first and a third liquid circuit (114, 214) each causing a cooling liquid of the fuel cells (112, 212) to flow, a second and a fourth liquid circuit (118a, 118b) each causing an icing protection liquid to flow, at least two icing protection heat exchangers (120a-d, 220a-d) arranged on the outer surface of the aircraft and having each icing protection liquid pass through them when it flows in the second or fourth liquid circuit (118a, 118b), and two liquid-liquid heat exchangers (116, 216) in which the cooling liquids form a hot pass and the icing protection liquids form a cold pass to reheat the icing protection liquid by the heat from the cooling liquids.

An inlet assembly of a nacelle includes an inlet cowl. The inlet cowl includes a lipskin that has a front section which defines the leading edge of the inlet cowl. The front section includes a composite panel and a metallic coating disposed along an exterior surface of the composite panel to protect the composite panel from damage. The lipskin defines perforations that penetrate through the composite panel and the metallic coating at the front section to convey a liquid through a thickness of the lipskin onto an exterior surface of the inlet cowl.

An inlet assembly of a nacelle includes an inlet cowl. The inlet cowl includes a lipskin that has a front section which defines the leading edge of the inlet cowl. The front section includes a composite panel and a metallic coating disposed along an exterior surface of the composite panel to protect the composite panel from damage. The lipskin defines perforations that penetrate through the composite panel and the metallic coating at the front section to convey a liquid through a thickness of the lipskin onto an exterior surface of the inlet cowl.

The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.

The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.

An aircraft provided with at least two pieces of aeronautic equipment, a first piece of 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 (80) of the second piece of equipment (81) 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.

An aircraft provided with at least two pieces of aeronautic equipment, a first piece of 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 (80) of the second piece of equipment (81) 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.