公开(公告)号：US20160167796A1

公开(公告)日：2016-06-16

申请号：US14966028

申请日：2015-12-11

Applicant: AIRBUS GROUP SAS

Inventor： Emmanuel JOUBERT ,  Benoit FERRAN ,  Antonin SANITAS ,  Germain MORIN

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

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.

Abstract translation: 飞机（10）包括：至少一个电动机（135）; 向所述电动马达供电的至少一个独立电源（110,120）; 被称为“辅助推进元件”的推进元件（130）包括：向电动机供电的独立电源（130），将热能转换成电能并将电力供应到 电动机和内燃机; 以及构造成将每个电动机，每个独立电源和辅助推进元件集成的结构（100），所述结构的参数基本上相同，而与辅助推进元件无关。 还描述了装配这种飞行器的方法。

公开(公告)号：US20160167800A1

公开(公告)日：2016-06-16

申请号：US14965926

申请日：2015-12-11

Applicant: AIRBUS GROUP SAS

Inventor： Emmanuel JOUBERT ,  Benoit FERRAN ,  Antonin SANITAS

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

CPC classification number: B64D33/08 ,  B64D27/24 ,  B64D33/10 ,  H01M10/625 ,  H01M10/6563 ,  H01M2220/20

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 translation: 一种用于冷却飞行器的至少一个自主电源（115）的装置（10），包括：用于空气（110）的冷却流体（110）的入口（105）; 冷却流体（110）被馈送到飞行器的至少一个自主电源; 收敛热空气（120）出口（130），包括用于控制空气流速的移动元件（125） 和飞行器的监视元件（150），其根据用于自主电源的冷却的需要（145）来控制用于控制空气流量的移动元件。 还描述了用于冷却飞机的至少一个自主电源的方法和包括这种装置的飞行器。