Airbus (sas)

Airbus Group Sas

Sirbus Sas

Airbus Corporation

Benoit Ferran

Emmanuel Joubert

Clément Dinel

Antonin Sanitas

Germain Morin

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.

Charging system for at least one accumulator battery of a vehicle including heat transfer fluid distribution for thermal conditioning of the battery and method for managing the recharging of said at least one battery

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 (SOH) that are equal to SOH-n&#xd7;p %, where n is an integer comprised between 0 and 20/p.

Method for managing a battery according to its state of health

A method for estimating a state of energy of a battery, comprising the steps of estimating a state of charge of the battery, determining a discrepancy between the state of charge and the state of energy as a function of the state of charge, computing the state of energy as a function of the estimated state of charge and of the determined discrepancy. Also a battery including apparatus configured to implement the method is provided.

Method for estimating a state of energy of a battery

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.

Vehicle receiving a system for storing electrical energy

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.

Device and method for cooling at least one autonomous electric power source of an aircraft

The aircraft () includes: at least one electric motor (); at least one stand-alone electrical power supply () supplying power to the electric motor; propulsion elements () referred to as 'auxiliary propulsion elements', included in the group including: a stand-alone electrical power supply () 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 () 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.

Growing community of inventors

Paris, France

Benoit Ferran