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：US09677466B2

公开(公告)日：2017-06-13

申请号：US14966180

申请日：2015-12-11

Applicant: AIRBUS GROUP SAS

Inventor： Hichem Smaoui ,  Bruno Rechain ,  Fabien Retho

IPC: F02B65/00 ,  B64C39/02 ,  F02B37/00 ,  F02B33/40 ,  F01D15/10 ,  F02C6/12 ,  F02C6/14 ,  F02C6/20 ,  B60K6/24 ,  B60K6/38 ,  B60K6/40 ,  B60K6/44 ,  B60K6/387 ,  B60K6/442 ,  B64D27/02

CPC classification number: F02B65/00 ,  B60K6/24 ,  B60K6/387 ,  B60K6/40 ,  B60K6/442 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/048 ,  B64D2027/026 ,  F01D15/10 ,  F02B33/40 ,  F02B37/00 ,  F02C6/12 ,  F02C6/14 ,  F02C6/206 ,  F05D2220/329 ,  F05D2220/40 ,  F05D2220/62 ,  F05D2220/76 ,  F05D2220/90 ,  F05D2260/42 ,  Y02T10/144 ,  Y02T10/6234 ,  Y02T10/6295 ,  Y02T50/64 ,  Y02T50/671

Abstract: A method of managing a power demand to assure the operation of a pilotless aircraft. The aircraft includes an internal combustion engine supplying a maximum principal power which can vary. The management method is particularly suitable for a rotary wing pilotless aircraft. It guarantees the storage of an amount of electrical energy at least equal to a recovery energy of the aircraft in the event of failure of the internal combustion engine. This recovery energy enables the control of autorotation and landing of the aircraft.