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.

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: 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: 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.