公开(公告)号：US09611049B2

公开(公告)日：2017-04-04

申请号：US14896653

申请日：2014-06-02

Applicant: EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANYEADS FRANCE ,  AIRBUS GROUP SAS

Inventor： Didier Esteyne ,  Emmanuel Joubert ,  Hichem Smaou ,  Charles Nespoulous ,  Bruno Rechain

IPC: H02P1/00 ,  B64D31/02 ,  B64D27/24 ,  H02J1/08 ,  H02J7/00 ,  H02J4/00 ,  H02J1/00

CPC classification number: B64D31/02 ,  B64D27/24 ,  B64D2221/00 ,  H02J1/08 ,  H02J4/00 ,  H02J7/0054 ,  H02J2001/008 ,  Y02T50/62

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.

公开(公告)号：US10017264B2

公开(公告)日：2018-07-10

申请号：US14966028

申请日：2015-12-11

Applicant: AIRBUS GROUP SAS

Inventor： Emmanuel Joubert ,  Benoit Ferran ,  Antonin Sanitas ,  Germain Morin

IPC: B64D41/00 ,  B64D27/24 ,  B64D37/02 ,  F02B61/06 ,  F02B65/00 ,  B64D27/02

CPC classification number: B64D27/24 ,  B64D37/02 ,  B64D41/00 ,  B64D2027/026 ,  F02B61/06 ,  F02B65/00 ,  Y02T50/64 ,  Y10S903/951

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.