A battery charging system for a hybrid electric powerplant can be configured to determine a maximum available charging power available from windmilling and/or excess thermal engine power available, and to use up to the maximum available charging power and/or the excess thermal engine power available to charge a battery. In certain embodiments, a control module can be configured to determine the maximum available charging power available from windmilling.

The invention relates to an electric drive for an aircraft hybrid system. This electric drive comprises a rotor and a stator, wherein the stator may be connected to a structure of the aircraft and the rotor has an annular flange with a shaft through opening for mounting on a propeller flange, wherein the flange is formed of at least two parts, wherein each of these parts of the flange delimits a section of the shaft through opening.

The invention relates to an electric drive for an aircraft hybrid system. This electric drive comprises a rotor and a stator, wherein the stator may be connected to a structure of the aircraft and the rotor has an annular flange with a shaft through opening for mounting on a propeller flange, wherein the flange is formed of at least two parts, wherein each of these parts of the flange delimits a section of the shaft through opening.

An unmanned aerial vehicle (“UAV”) is configured with a redundant power generation system on-board the UAV. A redundant power system on-board the UAV can selectively utilize an auxiliary power source during operation and/or flight of the UAV. The power system on-board the UAV may include a battery and at least one auxiliary power source comprising a combustion engine. The combustion engine on-board the UAV may be selectively operated to charge the battery when a charge level of the battery is below a full charge level, and/or to power one or more propeller motors of the UAV.

An unmanned aerial vehicle (“UAV”) is configured with a redundant power generation system on-board the UAV. A redundant power system on-board the UAV can selectively utilize an auxiliary power source during operation and/or flight of the UAV. The power system on-board the UAV may include a battery and at least one auxiliary power source comprising a combustion engine. The combustion engine on-board the UAV may be selectively operated to charge the battery when a charge level of the battery is below a full charge level, and/or to power one or more propeller motors of the UAV.

A propulsion unit, notably for an aircraft, including a turbomachine; a propeller that can be selectively coupled to the turbomachine; a rotary electrical machine able to drive at least the turbomachine, and selective coupling of the rotary electric machine to the propeller and/or the turbomachine that is able to couple only the propeller to the rotary electrical machine during a defined stage of operation of the propulsion unit and that is able to couple or not couple the rotary electric machine to a gas generator and/or a free turbine of the turbomachine.

Rotary-wing aircraft or fixed-wing aircraft consisting of one or a plurality of rotors and/or one or a plurality of airscrews being caused to rotate by means of at least one shaft, the said aircraft comprising a distributed electric motor unit configured to ensure the propulsion and/or the lifting of the said aircraft by causing the said shaft to rotate, the motor unit being a distributed electric motor unit connected directly to the rotating shaft, no mechanism for the transmission of movement being interposed between the said unit and the said shaft, the distributed electric motor unit being composed of a plurality of stacked electric motor elements, each said electric motor element being connected directly to the rotating shaft and consisting of at least one fixed stator and at least one moving rotor capable of connection to the said rotating shaft in order to transmit to it a mechanical power of the following kind where: .Math.Pr=the nominal mechanical power necessary for the propulsion and/or for the lifting of the said aircraft, .Math.Pim=the maximum mechanical power capable of being delivered by the electric motor element on level i, to the rotating shaft, for instance Pim<Pr, .Math.Ki=the power derating of the electric motor element on level i, for instance 0≦ki≦1, Ki being a variable that is adjustable as a function of the undamaged number of electric motor elements and/or as a function of the nominal mechanical power necessary for the propulsion and/or for the lifting of the said aircraft at a moment in time t, n=the number of electric motor elements comprising the distributed electric, motor unit, for instance n≧2,—the axes of rotation of the moving rotors and of the rotating shaft being coaxial.

Rotary-wing aircraft or fixed-wing aircraft consisting of one or a plurality of rotors and/or one or a plurality of airscrews being caused to rotate by means of at least one shaft, the said aircraft comprising a distributed electric motor unit configured to ensure the propulsion and/or the lifting of the said aircraft by causing the said shaft to rotate, the motor unit being a distributed electric motor unit connected directly to the rotating shaft, no mechanism for the transmission of movement being interposed between the said unit and the said shaft, the distributed electric motor unit being composed of a plurality of stacked electric motor elements, each said electric motor element being connected directly to the rotating shaft and consisting of at least one fixed stator and at least one moving rotor capable of connection to the said rotating shaft in order to transmit to it a mechanical power of the following kind where: .Math.Pr=the nominal mechanical power necessary for the propulsion and/or for the lifting of the said aircraft, .Math.Pim=the maximum mechanical power capable of being delivered by the electric motor element on level i, to the rotating shaft, for instance Pim<Pr, .Math.Ki=the power derating of the electric motor element on level i, for instance 0≦ki≦1, Ki being a variable that is adjustable as a function of the undamaged number of electric motor elements and/or as a function of the nominal mechanical power necessary for the propulsion and/or for the lifting of the said aircraft at a moment in time t, n=the number of electric motor elements comprising the distributed electric, motor unit, for instance n≧2,—the axes of rotation of the moving rotors and of the rotating shaft being coaxial.

The machine, such as an aircraft, is provided with a powertrain which comprises a vaned propulsion system (3), and a thermal drive system (1), including a first thermal engine (1A) and a second thermal engine (1B), which is configured to allow the vaned propulsion system (3) to be driven. The powertrain also includes an electric drive system (2) which allows the vaned propulsion system (3) to be driven, an electrical power supply system (4) including a battery (40) which allows the electric drive system (2) to be supplied with power. A clutch system (10) allows any or each of the thermal engines (1A, 1B) to be engaged in order to drive the vaned propulsion system (3), the clutch system (10) also being configured to allow any or each of the thermal engines (1A, 1B) to be disengaged from the vaned propulsion system (3).

The machine, such as an aircraft, is provided with a powertrain which comprises a vaned propulsion system (3), and a thermal drive system (1), including a first thermal engine (1A) and a second thermal engine (1B), which is configured to allow the vaned propulsion system (3) to be driven. The powertrain also includes an electric drive system (2) which allows the vaned propulsion system (3) to be driven, an electrical power supply system (4) including a battery (40) which allows the electric drive system (2) to be supplied with power. A clutch system (10) allows any or each of the thermal engines (1A, 1B) to be engaged in order to drive the vaned propulsion system (3), the clutch system (10) also being configured to allow any or each of the thermal engines (1A, 1B) to be disengaged from the vaned propulsion system (3).