Abstract: An aircraft wing portion comprises a shroud. This shroud has a leading edge and a trailing edge, a pressure-side surface and a suction-side surface. The shroud also has a through-duct connecting the pressure-side surface to the suction-side surface. The through-duct houses a rotor. The shroud comprises a front part, extending from the leading edge to the through-duct. The shroud has a profile with a front section, corresponding to its front part. The through-duct is closer to the trailing edge than to the leading edge, while the profile has a distance between the pressure-side surface and the suction-side surface that is at its maximum on its front section. This front section has a camber of less than ten percent.

Abstract: An aircraft includes drive units, at least one battery of the drive units, at least one electrical generation source connected to each battery and comprising at least one electrical converter, and a power supply control device to control each electrical generation source according to the power requirements of the drive units and to treat each battery passively. Each electrical converter is connected to each battery via a respective junction including two metal-oxide-semiconductor field-effect transistors connected in series and of opposite forward directions. Each junction can operate exclusively according to a unidirectional state in which the current flows from the electrical converter to the battery, a bidirectional state, and a blocking state.

Abstract: An aircraft includes drive units, at least one battery of the drive units, at least one electrical generation source connected to each battery and comprising at least one electrical converter, and a power supply control device to control each electrical generation source according to the power requirements of the drive units and to treat each battery passively. Each electrical converter is connected to each battery via a respective junction including two metal-oxide-semiconductor field-effect transistors connected in series and of opposite forward directions. Each junction can operate exclusively according to a unidirectional state in which the current flows from the electrical converter to the battery, a bidirectional state, and a blocking state.

Abstract: An aircraft includes drive units, at least one battery (B1, . . . ,BM) of the drive units, at least one electrical generation source connected to each battery (B1, . . . ,BM) and comprising at least one electrical converter (E1, . . . ,EN), and a power supply control device to control each electrical generation source according to the power requirements of the drive units and to treat each battery (B1, . . . ,BM) passively. Each electrical converter (E1, . . . ,EN) is connected to each battery (B1, . . . ,BM) via a respective junction including two contactors or electromechanical relays and a diode. Each junction can operate exclusively according to a unidirectional state in which the current flows from the electrical converter (E1, . . . ,EN) to the battery (B1, . . . ,BM), a bidirectional state, and a blocking state.

Abstract: An aircraft having a hybrid power source includes horizontal drive thrusters powered by an electric motor and forming a horizontal drive unit, vertical take-off/landing rotors forming with electric motors and a corresponding stored electrical energy source a vertical drive unit comprising an electric power supply bus, power generation sources connected to the electric power supply buses and by an input of a vertical drive unit and to each horizontal drive unit via an output of each vertical drive unit. The electric power supply controller emits a power command to the power generation source according to power requirements of the vertical and/or horizontal drive units. The stored electrical energy sources supply electricity according to the difference between the power requirements of the vertical and/or horizontal drive units. The power generation source recharges the stored electrical energy sources, so that the stored electrical energy sources are passively controlled.

Abstract: An aircraft having a hybrid power source includes horizontal drive thrusters powered by an electric motor and forming a horizontal drive unit, vertical take-off/landing rotors forming with electric motors and a corresponding stored electrical energy source a vertical drive unit comprising an electric power supply bus, power generation sources connected to the electric power supply buses and by an input of a vertical drive unit and to each horizontal drive unit via an output of each vertical drive unit. The electric power supply controller emits a power command to the power generation source according to power requirements of the vertical and/or horizontal drive units. The stored electrical energy sources supply electricity according to the difference between the power requirements of the vertical and/or horizontal drive units. The power generation source recharges the stored electrical energy sources, so that the stored electrical energy sources are passively controlled.

Abstract: A power management system for an aircraft with a hybrid power source comprises a rechargeable electricity source and an electricity generating source, a detector determining status data of the elements of the aircraft power consumption electrical circuit, and power data relating to the instantaneous electrical power demanded by the aircraft and/or the charging status of the rechargeable electricity sources, an automaton receiving the power data from the detector and determining a control status for the power sources, an adapter determining a backup electrical configuration when the status data indicate a failure, a controller determining an electrical control for the rechargeable electrical source and the electrical generating source based on the instantaneous electrical power demanded, and a switch emitting commands to the switches of the aircraft power consumption electrical circuit to implement a nominal electrical configuration, or, a backup electrical configuration for the adapter in case of receipt ther

Abstract: A power management system for an aircraft with a hybrid power source comprises a rechargeable electricity source and an electricity generating source, a detector determining status data of the elements of the aircraft power consumption electrical circuit, and power data relating to the instantaneous electrical power demanded by the aircraft and/or the charging status of the rechargeable electricity sources, an automaton receiving the power data from the detector and determining a control status for the power sources, an adapter determining a backup electrical configuration when the status data indicate a failure, a controller determining an electrical control for the rechargeable electrical source and the electrical generating source based on the instantaneous electrical power demanded, and a switch emitting commands to the switches of the aircraft power consumption electrical circuit to implement a nominal electrical configuration, or, a backup electrical configuration for the adapter in case of receipt ther

Abstract: An aircraft having a hybrid power source includes two horizontal drive units, four vertical drive units, a vertical drive unit comprising a power supply bus the output of which may be connected to a single horizontal drive unit which may be connected to at least two vertical drive units via a switch, two power generation sources connected, on the one hand, to each of the power supply buses by a respective input of the corresponding vertical drive unit and, on the other hand, to each horizontal drive unit via the respective output of each vertical drive unit, and a power supply command arranged to send a power command to the power generation sources according to the power requirements of the vertical drive units and/or horizontal drive units. The power generation sources are also suitable for recharging power sources of the vertical drive units.

Abstract: An aircraft having a hybrid power source includes two horizontal drive units, four vertical drive units, a vertical drive unit comprising a power supply bus the output of which may be connected to a single horizontal drive unit which may be connected to at least two vertical drive units via a switch, two power generation sources connected, on the one hand, to each of the power supply buses by a respective input of the corresponding vertical drive unit and, on the other hand, to each horizontal drive unit via the respective output of each vertical drive unit, and a power supply command arranged to send a power command to the power generation sources according to the power requirements of the vertical drive units and/or horizontal drive units. The power generation sources are also suitable for recharging power sources of the vertical drive units.