Abstract: A charging system for electrical accumulator vehicle batteries, comprising a charging station principally designed to generate a charging current for the batteries, a system for thermally conditioning the batteries, by the circulation of a heat transfer fluid. A vehicle-mounted segment comprises a component for measuring the battery temperatures, a system for measuring the state of charge of the batteries, and a heat transfer fluid distribution circuit. A non-vehicle-mounted segment comprises a ground module of the thermal conditioning system for generating a flux of a heat transfer fluid, a control-command module designed to determine, during charging, as a function of the states of charge of the batteries and the battery temperatures, the flow rates and temperatures of the heat transfer fluid and a charging current required to achieve a target final state, characterized by a target temperature and a target charge at the end of a given charging time.

Abstract: A method for managing a battery according to a state of health of the battery, comprising, prior to using the battery, predetermining a maximum depth of discharge profile according to the state of health of the battery, the profile being dependent on a technology of the battery, on a nominal energy level to be made available each time the battery is discharged, the nominal energy level being substantially constant over a service life of the battery. While using the battery, a maximum depth of discharge of the battery is adjusted at regular intervals, each time the state of health of the battery decreases by a percentage corresponding to an update interval p % that is equal to p/100, that is, for all state of health values (SOHn) that are equal to SOH0-n×p %, where n is an integer comprised between 0 and 20/p.

Abstract: The vehicle receives batteries comprising cells arranged into at least one pack configured to be held in a vehicle structure, the pack being alternatively chosen from among at least one pack(P) and at least one pack(E) which are mechanically interchangeable and electrically substitutable. The pack(P) cells exhibit a maximum power density substantially higher than the pack(E) cells exhibit, and comprise cells exhibiting an energy density per unit mass substantially less than the pack(E) cells exhibit. The maximum electrical power of the pack(P) corresponds to the maximum electrical power needed to accomplish a first vehicle mission and the energy storage capacity of the pack(P) is at least sufficient to accomplish the first mission. The electrical energy storage capacity of the pack(E) corresponds to the electrical energy storage capacity needed to accomplish a second vehicle mission and the maximum electrical power is at least sufficient to accomplish the second mission.

Abstract: A method for managing unbalanced thrusts caused by engine failures in an aircraft provided with a distributed propulsion system, the distributed propulsion system including 2N powertrains (PTi), with N a strictly positive integer and i an integer lying between 1 and 2N inclusive, distributed symmetrically in relation to a plane of symmetry of the aircraft, according to which the power of at least one powertrain belonging to a first side of the plane of symmetry is reduced when a failure occurs in a powertrain belonging to the opposite side, such that the sum of the moments of the thrusts generated by the powertrains in relation to the center of gravity of the aircraft is nil, to within regulatory tolerances.

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: The vehicle receives batteries comprising cells arranged into at least one pack configured to be held in a vehicle structure, the pack being alternatively chosen from among at least one pack(P) and at least one pack(E) which are mechanically interchangeable and electrically substitutable. The pack(P) cells exhibit a maximum power density substantially higher than the pack(E) cells exhibit, and comprise cells exhibiting an energy density per unit mass substantially less than the pack(E) cells exhibit. The maximum electrical power of the pack(P) corresponds to the maximum electrical power needed to accomplish a first vehicle mission and the energy storage capacity of the pack(P) is at least sufficient to accomplish the first mission. The electrical energy storage capacity of the pack(E) corresponds to the electrical energy storage capacity needed to accomplish a second vehicle mission and the maximum electrical power is at least sufficient to accomplish the second mission.

Abstract: A charging system for electrical accumulator vehicle batteries, comprising a charging station principally designed to generate a charging current for the batteries, a system for thermally conditioning the batteries, by the circulation of a heat transfer fluid. A vehicle-mounted segment comprises a component for measuring the battery temperatures, a system for measuring the state of charge of the batteries, and a heat transfer fluid distribution circuit. A non-vehicle-mounted segment comprises a ground module of the thermal conditioning system for generating a flux of a heat transfer fluid, a control-command module designed to determine, during charging, as a function of the states of charge of the batteries and the battery temperatures, the flow rates and temperatures of the heat transfer fluid and a charging current required to achieve a target final state, characterized by a target temperature and a target charge at the end of a given charging time.

Abstract: A device for cooling at least one autonomous electric power source of an aircraft, includes: an inlet for air cooling a cooling fluid; the cooling fluid being fed towards at least one autonomous electric power source of the aircraft; a convergent hot air outlet, including moving elements for controlling the air flowrate; and supervision elements of the aircraft, which control the moving elements for controlling the air flowrate depending on the need for cooling of the autonomous electric power source. A method for cooling at least one autonomous electric power source of an aircraft and an aircraft including such a device are also described.

Abstract: A method and an architecture for implementing the method for the management of a hybrid thermal/electrical propulsion aircraft in the course of its various flight phases. The hybrid propulsion receives at each instant i a total power command Ptot,com,i distributed between thermal Pth,com,i and electrical Pe,com,i power commands. The method includes steps of calculating a maximum admissible thermal power command Pth,com,max,i for compliance with acoustic objectives on the ground, selecting the thermal power command Pth,com,i in a bounded range of values, determining the electrical power command Pe,com,i. The thermal Pth,com,i and electrical Pe,com,i power commands supplied by the hybrid propulsion are thus adjusted in the course of the different flight phases depending on a height hi of the aircraft in order to make it possible to comply with acoustic requirements on the ground.

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: A method for managing unbalanced thrusts caused by engine failures in an aircraft provided with a distributed propulsion system, the distributed propulsion system including 2N powertrains (PTi), with N a strictly positive integer and i an integer lying between 1 and 2N inclusive, distributed symmetrically in relation to a plane of symmetry of the aircraft, according to which the power of at least one powertrain belonging to a first side of the plane of symmetry is reduced when a failure occurs in a powertrain belonging to the opposite side, such that the sum of the moments of the thrusts generated by the powertrains in relation to the center of gravity of the aircraft is nil, to within regulatory tolerances.

Abstract: A method for managing a battery according to a state of health of the battery, comprising, prior to using the battery, predetermining a maximum depth of discharge profile according to the state of health of the battery, the profile being dependent on a technology of the battery, on a nominal energy level to be made available each time the battery is discharged, the nominal energy level being substantially constant over a service life of the battery. While using the battery, a maximum depth of discharge of the battery is adjusted at regular intervals, each time the state of health of the battery decreases by a percentage corresponding to an update interval p % that is equal to p/100, that is, for all state of health values (SOHO that are equal to SOHo-n×p %, where n is an integer comprised between 0 and 20/p.

Abstract: A method for prohibiting the propulsion of an electrical airplane when the airplane is galvanically connected to a ground station. The electrical airplane comprises a battery assembly, a low voltage electrical network provided with power contactors, at least one integrated electrical propulsion system and a processor. The method comprises steps of detection of a connection to the ground station by the battery assembly, of non-supply of the integrated electrical propulsion systems and of their switch to protection mode, and of stopping of the propulsion systems regardless of their supply of electrical energy and the user set point.

Abstract: The aircraft (10) includes: at least one electric motor (135); at least one stand-alone electrical power supply (110, 120) supplying power to the electric motor; propulsion elements (130) referred to as “auxiliary propulsion elements”, included in the group including: a stand-alone electrical power supply (130) supplying power to the electric motor, a power supply converting thermal energy into electrical energy and supplying power to the electric motor, and an internal combustion engine; and a structure (100) configured to integrate each electric motor, each stand-alone electrical power supply and the auxiliary propulsion elements, the parameters of the structure being substantially identical regardless of the auxiliary propulsion elements. A method of fitting out such an aircraft is also described.

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: A drive system of at least one rotor of an aircraft via electrical energy in addition to or as a replacement of a mechanical system. The electrical energy is provided at least in part by at least one device for recovering thermal energy from hot gases of an internal combustion engine of the aircraft.

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 (10) for cooling at least one autonomous electric power source (115) of an aircraft, includes: an inlet (105) for air (110) cooling a cooling fluid (110); the cooling fluid (110) is fed towards at least one autonomous electric power source of the aircraft; a convergent hot air (120) outlet (130), including moving elements (125) for controlling the air flowrate; and supervision elements (150) of the aircraft, which control the moving elements for controlling the air flowrate depending on the need (145) for cooling of the autonomous electric power source. A method for cooling at least one autonomous electric power source of an aircraft and an aircraft including such a device are also described.

Abstract: The aircraft (10) includes: at least one electric motor (135); at least one stand-alone electrical power supply (110, 120) supplying power to the electric motor; propulsion elements (130) referred to as “auxiliary propulsion elements”, included in the group including: a stand-alone electrical power supply (130) supplying power to the electric motor, a power supply converting thermal energy into electrical energy and supplying power to the electric motor, and an internal combustion engine; and a structure (100) configured to integrate each electric motor, each stand-alone electrical power supply and the auxiliary propulsion elements, the parameters of the structure being substantially identical regardless of the auxiliary propulsion elements. A method of fitting out such an aircraft is also described.

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.