公开(公告)号：US10680294B2

公开(公告)日：2020-06-09

申请号：US15951380

申请日：2018-04-12

Applicant: Airbus SAS

Inventor： Benoit Ferran ,  Emmanuel Joubert ,  Clément Dinel

IPC: H02J7/00 ,  H01M10/48 ,  G01R31/382 ,  H01M10/44 ,  G01R31/392

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.

公开(公告)号：US10150570B2

公开(公告)日：2018-12-11

申请号：US14965926

申请日：2015-12-11

Applicant: AIRBUS SAS

Inventor： Emmanuel Joubert ,  Benoit Ferran ,  Antonin Sanitas

IPC: B64D33/08 ,  H01M10/625 ,  H01M10/6563 ,  B64D27/24 ,  B64D33/10

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.

公开(公告)号：US09932129B2

公开(公告)日：2018-04-03

申请号：US14898128

申请日：2014-06-11

Applicant: AIRBUS SAS

Inventor： Emmanuel Joubert ,  Charles Nespoulous ,  Bruno Rechain ,  Hichem Smaoui

IPC: B64F1/04 ,  B64C25/32 ,  B64F1/22

CPC classification number: B64F1/04 ,  B64C25/32 ,  B64F1/22 ,  B64F1/228 ,  Y02T50/826

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.

公开(公告)号：US10882413B2

公开(公告)日：2021-01-05

申请号：US16007760

申请日：2018-06-13

Applicant: Airbus SAS

Inventor： Benoit Ferran ,  Emmanuel Joubert ,  Clément Dinel

IPC: H01M10/65 ,  B60L53/62 ,  H01M10/63 ,  H01M10/48 ,  H01M10/44 ,  H01M10/656 ,  B60L11/18 ,  H01M10/613 ,  H01M10/625 ,  H01M10/6563 ,  B64D41/00 ,  B64D27/24 ,  B60L3/00 ,  B60L58/24 ,  B60L58/12 ,  B60L58/27 ,  H01M10/46

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.

公开(公告)号：US10569891B2

公开(公告)日：2020-02-25

申请号：US16017728

申请日：2018-06-25

Applicant: Airbus SAS

Inventor： Benoit Ferran ,  Emmanuel Joubert ,  Clément Dinel

IPC: B64D27/24 ,  H02J7/00 ,  G01R31/00 ,  H01M2/10 ,  G01R31/378 ,  H01M10/44 ,  B60L58/20 ,  B60L58/12 ,  B60K1/04 ,  B60L58/22 ,  B60L50/60 ,  B60L58/16

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.

公开(公告)号：US10138899B2

公开(公告)日：2018-11-27

申请号：US14898127

申请日：2014-06-13

Applicant: AIRBUS SAS

Inventor： Emmanuel Joubert ,  Hichem Smaoui ,  Charles Nespoulous ,  Bruno Rechain

IPC: F04D29/58 ,  F04D25/08 ,  F04D25/06 ,  F04D25/12 ,  B64D27/24 ,  B64D33/08 ,  B64D33/10 ,  B64D33/02 ,  B64D29/02

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.