A turboprop includes a propeller, a propeller shaft carrying the propeller, the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine having at least a first configuration in which it is mechanically coupled to the propeller shaft and at least one oil pump configured to supply a hydraulic circuit for adjusting the pitch of the propeller. The oil pump is configured to be electrically operated. An aircraft can include such a turboprop and methods can control such a turboprop and such an aircraft.

A turboprop includes a propeller, a propeller shaft carrying the propeller, the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine having at least a first configuration in which it is mechanically coupled to the propeller shaft and at least one oil pump configured to supply a hydraulic circuit for adjusting the pitch of the propeller. The oil pump is configured to be electrically operated. An aircraft can include such a turboprop and methods can control such a turboprop and such an aircraft.

The device for charging a battery of an aircraft comprises a reversible electrical power converter comprising a power inlet configured to be connected to the battery and a power outlet configured to be connected to a propulsion rotary electric machine driving a propeller of the aircraft in such a way that the power converter transfers electrical energy between the electric machine and the battery. The charging device also comprises a means for deactivating the propeller, the means being configured to prevent the rotation of the propeller and a parking socket connected between the charging contactor and the power outlet.

The device for charging a battery of an aircraft comprises a reversible electrical power converter comprising a power inlet configured to be connected to the battery and a power outlet configured to be connected to a propulsion rotary electric machine driving a propeller of the aircraft in such a way that the power converter transfers electrical energy between the electric machine and the battery. The charging device also comprises a means for deactivating the propeller, the means being configured to prevent the rotation of the propeller and a parking socket connected between the charging contactor and the power outlet.

An electrically powered vehicle may include a DC bus and a plurality of batteries, each coupled in parallel to the DC bus. At least one switch is coupled in series between at least one battery of the plurality of batteries and the DC bus and a plurality of inverter circuits may each be coupled in parallel to the DC bus. A plurality of motors may each be coupled to a respective inverter circuit of the plurality of inverter circuits. In various embodiments, the electrically powered vehicle may further include a plurality of switches, each switch coupled in series between a respective battery of the plurality of batteries.

An electrically powered vehicle may include a DC bus and a plurality of batteries, each coupled in parallel to the DC bus. At least one switch is coupled in series between at least one battery of the plurality of batteries and the DC bus and a plurality of inverter circuits may each be coupled in parallel to the DC bus. A plurality of motors may each be coupled to a respective inverter circuit of the plurality of inverter circuits. In various embodiments, the electrically powered vehicle may further include a plurality of switches, each switch coupled in series between a respective battery of the plurality of batteries.

A propulsion unit comprising a propulsion system, at least one electric motor positioned in a first external zone, a transmission system, a coupling device which comprises: a first coupling shaft coupled to an output of the electric motor, passing through the transmission system and having a first end protruding into a second external zone; a second coupling shaft coupled to an input of the transmission system, passing through at least one wall of the transmission system and having a first end protruding into the second external zone; and a coupling system configured to couple the first ends of the first and second coupling shafts in terms of rotation and which is positioned in the second external zone. Also an aircraft having at least one such propulsion unit.

A propulsion unit comprising a propulsion system, at least one electric motor positioned in a first external zone, a transmission system, a coupling device which comprises: a first coupling shaft coupled to an output of the electric motor, passing through the transmission system and having a first end protruding into a second external zone; a second coupling shaft coupled to an input of the transmission system, passing through at least one wall of the transmission system and having a first end protruding into the second external zone; and a coupling system configured to couple the first ends of the first and second coupling shafts in terms of rotation and which is positioned in the second external zone. Also an aircraft having at least one such propulsion unit.

A propulsion system is provided for an aircraft. This propulsion system includes a propulsor rotor, a drivetrain, a first power unit and a second power unit. The drivetrain is coupled to the propulsor rotor. The first power unit includes a first overrunning clutch and a first electric motor. The first overrunning clutch is configured to selectively couple the first electric motor to the drivetrain. The first electric motor is configured to drive rotation of the propulsor rotor through the first overrunning clutch and the drivetrain. The second power unit includes a second overrunning clutch and a second electric motor. The second overrunning clutch is configured to selectively couple the second electric motor to the drivetrain. The second electric motor is configured to drive the rotation of the propulsor rotor through the second overrunning clutch and the drivetrain.

A power transmission system for a propeller hub of an aircraft is described, wherein the power transmission system comprises a hollow inner conductive cylinder configured to be mounted to a rotatable shaft a hollow outer insulating cylinder concentric with the inner conductive cylinder, wherein at least a portion of the outer insulating cylinder is located radially outwardly of the inner conductive cylinder, a conductive element positioned at a first end surface of the outer insulating cylinder, wherein the outer insulating cylinder comprises a bore extending radially outwardly from an inner diameter to an outer diameter of the outer insulating cylinder to house a conductive rod for connecting the inner conductive cylinder to a first electrical terminal; wherein the conductive element is configured to be connectable to a second electrical terminal. An aircraft, such as a UAV, comprising the power transmission is also described.