Abstract: An electromechanical machine includes at least one coil made from a material that becomes electrically superconducting when its temperature is below a critical temperature. A functional part is contained in an internal volume of a thermally insulating and fluid-tight enclosure of the machine. A wall of the insulating enclosure is traversed in a fluid-tight fashion by at least one shaft for transmitting mechanical power between the functional part located in the internal volume of the insulating enclosure and a space outside the insulating enclosure. The functional part can be used as a heat sink, pre-cooled to maintain the temperature conditions for maintaining superconductivity inside the insulating enclosure.

Abstract: An electric propulsion assembly for an aircraft includes a nacelle having a nacelle cowl which defines an inner space for arranging an electric propulsion unit, which includes a blower, of the aircraft. An electric motor assembly is placed in the inner space and connected to the propulsion unit to supply power to the propulsion unit. An airflow generated by the blower flows in a space between the motor assembly and the nacelle cowl defining a duct to supply thrust to the aircraft. A power electronics system has at least one heat exchanger to transfer thermal energy from the system to a work fluid to cool the system. The heat exchanger is placed to project at least partially into the duct, so that the work fluid consists of the air flow generated by the blower.

Abstract: Drone comprising a central body and a plurality of arms, preferably at least three arms, each arm comprising a first end mounted on the central body, each arm comprising, in the vicinity of a second end, at least one electric motor and at least one propeller coupled to said electric motor, each arm accommodating at least one electric battery.

Abstract: A device for moving aircraft along the ground includes at least one runway and at least one aircraft. The aircraft is secured to a tractor element having a magnetic mass formed mainly of type II superconductor material and the runway includes stator coils arranged in the runway with at least one line of coils parallel to an axis of the runway. A command/control system supplies power to the stator coils to generate a magnetic field that levitates the tractor element, magnetized beforehand into a phase II superconducting state, above the runway.

Abstract: An electrical power supply device for electric propulsion aircraft includes first and second electric motors configured to ensure the propulsion of the aircraft. First and second high-voltage electrical circuits are connected respectively to the two electric motors. A low-voltage electrical circuit is connected to at least one control and/or command facility of the aircraft. First and second pack of batteries are connected respectively to the two high-voltage electrical circuits. First and second battery management systems are connected to the low voltage circuit. Two battery management systems are linked respectively to the two packs of batteries. An electrical converter is connected to the first high-voltage electrical circuit and to the low-voltage electrical circuit.

Abstract: A device for moving aircraft along the ground includes at least one runway and at least one aircraft. The aircraft is secured to a tractor element having a magnetic mass formed mainly of type II superconductor material and the runway includes stator coils arranged in the runway with at least one line of coils parallel to an axis of the runway. A command/control system supplies power to the stator coils to generate a magnetic field that levitates the tractor element, magnetized beforehand into a phase II superconducting state, above the runway.

Abstract: An electric propulsion assembly for an aircraft includes a nacelle having a nacelle cowl which defines an inner space for arranging an electric propulsion unit, which includes a blower, of the aircraft. An electric motor assembly is placed in the inner space and connected to the propulsion unit to supply power to the propulsion unit. An airflow generated by the blower flows in a space between the motor assembly and the nacelle cowl defining a duct to supply thrust to the aircraft. A power electronics system has at least one heat exchanger to transfer thermal energy from the system to a work fluid to cool the system. The heat exchanger is placed to project at least partially into the duct, so that the work fluid consists of the air flow generated by the blower.

Abstract: An electrical power supply device for electric propulsion aircraft includes first and second electric motors configured to ensure the propulsion of the aircraft. First and second high-voltage electrical circuits are connected respectively to the two electric motors. A low-voltage electrical circuit is connected to at least one control and/or command facility of the aircraft. First and second pack of batteries are connected respectively to the two high-voltage electrical circuits. First and second battery management systems are connected to the low voltage circuit. Two battery management systems are linked respectively to the two packs of batteries. An electrical converter is connected to the first high-voltage electrical circuit and to the low-voltage electrical circuit.

Abstract: An electromechanical machine includes at least one coil made from a material that becomes electrically superconducting when its temperature is below a critical temperature. A functional part is contained in an internal volume of a thermally insulating and fluid-tight enclosure of the machine. A wall of the insulating enclosure is traversed in a fluid-tight fashion by at least one shaft for transmitting mechanical power between the functional part located in the internal volume of the insulating enclosure and a space outside the insulating enclosure. The functional part can be used as a heat sink, pre-cooled to maintain the temperature conditions for maintaining superconductivity inside the insulating enclosure.

Abstract: A system for recharging the batteries carried on board an electrically powered aircraft. The system includes a charging aircraft, a device to temporarily and electrically connecting the charging aircraft to the electrically powered aircraft. The electrically powered aircraft includes a charge-regulating device.