Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.

Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

Abstract: A system of fuel cells for an aircraft including a plurality of fuel cells, a hydrogen circuit, a cooling circuit and a first air circuit configured to supply oxygen to a first subset of fuel cells having at least two cells. The first air circuit includes an air flow restrictor at each fuel cell inlet of the first subset and configured to distribute the air between the fuel cells of the first subset, and an outlet valve connected to the outlet of the fuel cells of the first subset, the opening of the outlet valve being controlled by a computer as a function of an electrical power that is to be produced by the fuel cells of the first subset. The use of the same air circuit to supply oxygen to several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.

Abstract: An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

Abstract: A system of fuel cells for an aircraft includes a plurality of fuel cells, a hydrogen circuit, an air circuit, and a first cooling circuit configured to cool a first subset of cells including at least two cells. The first cooling circuit includes a computer-controlled device for mixing a first liquid coolant at a first temperature with a second liquid coolant at a second temperature lower than the first temperature to obtain a liquid coolant having a target temperature, a liquid coolant restrictor configured to distribute the liquid coolant between the cells of the first subset, and an outlet valve, the opening of which is controlled by the computer as a function of the cooling needs of the cells of the first subset. The use of a cooling circuit to cool several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: A system of fuel cells for an aircraft includes a plurality of fuel cells, a hydrogen circuit, an air circuit, and a first cooling circuit configured to cool a first subset of cells including at least two cells. The first cooling circuit includes a computer-controlled device for mixing a first liquid coolant at a first temperature with a second liquid coolant at a second temperature lower than the first temperature to obtain a liquid coolant having a target temperature, a liquid coolant restrictor configured to distribute the liquid coolant between the cells of the first subset, and an outlet valve, the opening of which is controlled by the computer as a function of the cooling needs of the cells of the first subset. The use of a cooling circuit to cool several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: A system of fuel cells for an aircraft including a plurality of fuel cells, a hydrogen circuit, a cooling circuit and a first air circuit configured to supply oxygen to a first subset of fuel cells having at least two cells. The first air circuit includes an air flow restrictor at each fuel cell inlet of the first subset and configured to distribute the air between the fuel cells of the first subset, and an outlet valve connected to the outlet of the fuel cells of the first subset, the opening of the outlet valve being controlled by a computer as a function of an electrical power that is to be produced by the fuel cells of the first subset. The use of the same air circuit to supply oxygen to several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

Abstract: An electronic device includes an electronic component and a protective shield including a phase change material having a phase change temperature of between 20° C. and 90° C., an antivibration gel having hyperelastic and/or viscoelastic behavior at 20° C., and a separation barrier positioned so as to separate the phase change material and the antivibration gel. The antivibration gel is positioned, at least partly, in contact with the electronic component, and has a thermal conductivity of greater than 1 W/m·K at 20° C.

Abstract: A piping system includes a first and a second inner tube assembled end to end and a hot fluid detector. For each inner tube, a first peripheral tube into which the inner tube is introduced and fixed. For each first peripheral tube, a second peripheral tube into which the first peripheral tube is introduced and fixed. A sleeve has a first section which surrounds the ends of the second two peripheral tubes facing one another and a second section which extends between the two ends up to the walls of the first two peripheral tubes. A pipe crosses the sleeve and opening out, on the one hand, into the space between the inner tubes and the first peripheral tubes and, on the other hand, in the vicinity of the hot fluid detector. A piping system of this kind is therefore thermally insulated and allows detection in the event of a leak.

Abstract: Ventilation of an internal compartment of a fairing device of a propulsion assembly in an aircraft moving at low speed on the ground or when it is stopped cannot be provided optimally using a conventional dynamic air intake. To solve this problem, the use of a fan housed within the internal compartment is proposed, for which the fan propeller can alternately be coupled to an accessory gear box to drive the fan propeller, and uncoupled from the accessory gear box when it is unnecessary to drive the fan propeller or when it represents a danger.

Abstract: An electronic device includes an electronic component and a protective shield including a phase change material having a phase change temperature of between 20° C. and 90° C., an antivibration gel having hyperelastic and/or viscoelastic behavior at 20° C., and a separation barrier positioned so as to separate the phase change material and the antivibration gel. The antivibration gel is positioned, at least partly, in contact with the electronic component, and has a thermal conductivity of greater than 1 W/m·K at 20° C.

Abstract: A piping system includes a first and a second inner tube assembled end to end and a hot fluid detector. For each inner tube, a first peripheral tube into which the inner tube is introduced and fixed. For each first peripheral tube, a second peripheral tube into which the first peripheral tube is introduced and fixed. A sleeve has a first section which surrounds the ends of the second two peripheral tubes facing one another and a second section which extends between the two ends up to the walls of the first two peripheral tubes. A pipe crosses the sleeve and opening out, on the one hand, into the space between the inner tubes and the first peripheral tubes and, on the other hand, in the vicinity of the hot fluid detector. A piping system of this kind is therefore thermally insulated and allows detection in the event of a leak.

Abstract: A dual-flow turbomachine including a nacelle, compressors, turbines, a fuel supply line, a transfer line, a de-icing circuit, and a heat management system having: a first heat exchanger providing an exchange of heat between fuel in the supply line and oil in the transfer line, a loop comprising a main line and a pump which circulates a heat transfer fluid in the main line, where the main line is connected to an outlet of the pump and enters an inlet of a third heat exchanger, where at the outlet of the third heat exchanger the main line meets an inlet of the de-icing circuit, where at the outlet of the de-icing circuit the main line meets the inlet of the pump, and where the third heat exchanger transfers heat between the heat transfer fluid of the main line and the oil of the transfer line.

Abstract: Ventilation of an internal compartment of a fairing device of a propulsion assembly in an aircraft moving at low speed on the ground or when it is stopped cannot be provided optimally using a conventional dynamic air intake. To solve this problem, the use of a fan housed within the internal compartment is proposed, for which the fan propeller can alternately be coupled to an accessory gear box to drive the fan propeller, and uncoupled from the accessory gear box when it is unnecessary to drive the fan propeller or when it represents a danger.