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 present disclosure relates generally to electric aircraft, and more specifically to electric power distribution for electric aircraft. In one embodiment, an electric aircraft is disclosed, comprising: a fuselage; two wings mounted on opposite sides of the fuselage; a plurality of first electric propulsion units, arranged on both sides of the fuselage, aft of the wings during forward flight; a plurality of second electric propulsion units arranged on both sides of the fuselage, forward of the wings during forward flight; and a plurality of battery packs, each battery pack configured to power at least: a portion of one of the first electric propulsion units on one side of the fuselage, and a portion of one of the second electric propulsion units on the other side of the fuselage.

The present disclosure relates generally to electric aircraft, and more specifically to electric power distribution for electric aircraft. In one embodiment, an electric aircraft is disclosed, comprising: a fuselage; two wings mounted on opposite sides of the fuselage; a plurality of first electric propulsion units, arranged on both sides of the fuselage, aft of the wings during forward flight; a plurality of second electric propulsion units arranged on both sides of the fuselage, forward of the wings during forward flight; and a plurality of battery packs, each battery pack configured to power at least: a portion of one of the first electric propulsion units on one side of the fuselage, and a portion of one of the second electric propulsion units on the other side of the fuselage.

Embodiments include an aircraft comprising a fuselage; a wing connected to the fuselage; and first and second propulsion systems connected to the wing on opposite sides of the fuselage, wherein at least a portion of each of the first and second propulsion systems and at least a portion of the wing are tiltable between a first position in which the aircraft is in a hover mode and a second position in which the aircraft is in a cruise mode, wherein each of the propulsion systems includes pylon and a rotor assembly comprising a plurality of rotor blades.

Embodiments include an aircraft comprising a fuselage; a wing connected to the fuselage; and first and second propulsion systems connected to the wing on opposite sides of the fuselage, wherein at least a portion of each of the first and second propulsion systems and at least a portion of the wing are tiltable between a first position in which the aircraft is in a hover mode and a second position in which the aircraft is in a cruise mode, wherein each of the propulsion systems includes pylon and a rotor assembly comprising a plurality of rotor blades.

In an inverter device, an inverter high-voltage unit is accommodated in an inverter housing. The inverter housing includes an inverter opening portion and an inverter lid portion. The inverter lid portion covers the inverter opening portion to hide the inverter high-voltage unit. When a control mode of a flight control device is set to an interlock mode, power supply from a battery to a motor is cut off as the inverter lid portion is opened. When the control mode is set to an interlock release mode, the power supply from the battery to the motor is not cut off even when the inverter lid portion is opened. The control mode is set to the interlock release mode when the eVTOL is in flight.

An aircraft and its associated aircraft linear support arms. The aircraft linear support arms include at least a rotor motor and a propeller. The rotor motor is connected to the propeller, and the linear support arm has a cross-sectional shape of an inverted teardrop shape. The streamlined structure of the inverted teardrop-shaped arm can reduce eddy currents formed by the propeller's downwash flow due to interference caused by the aircraft body, thereby reducing the wear and tear of the lift motor and increasing the efficiency of the lift motor.

The propulsion unit including a casing having an inner curved surface and an outer curved surface, at least one tire disposed within the casing within a duct defined by the inner curved surface and the outer curved surface, a first propeller and a second propeller having a plurality of blades extending from within the casing toward a center axis of the casing, and one or more motors housed within the casing, the one or motor being configured to operate the at least one tire, the first propeller, and the second propeller independently of one another. There is also provided a vehicle with one or more propulsion units of the present disclosure.

A method of operating an electrical power system for an aircraft. The electrical power system includes a semiconductor-based active power converter and a contactor coupled to and controllable by the semiconductor-based active power converter. The method includes, in response to a determination that there is a fault within the electrical power system, operating in a fault mode which includes: maintaining the semiconductor-based active power converter in a blocked configuration (optionally followed by maintaining the semiconductor-based active power converter in a crow-bar configuration); and subsequently causing the contactor to be opened.