A controller of an electrically powered vehicle includes an electronic control unit. The electronic control unit performs a switching control by a square wave control in a first switching mode when a rotation speed of the motor is equal to or higher than a first predetermined rotation speed. The electronic control unit performs the switching control by the square wave control in a second switching mode when the rotation speed of the motor is lower than the first predetermined rotation speed. The first predetermined rotation speed is a rotation speed lower than a first resonance region. The first switching mode is a mode of a switching pattern that suppresses LC resonance in the first resonance region. The second switching mode is a mode of a switching pattern that suppresses LC resonance in a second resonance region lower than the first predetermined rotation speed.

A controller of an electrically powered vehicle includes an electronic control unit. The electronic control unit performs a switching control by a square wave control in a first switching mode when a rotation speed of the motor is equal to or higher than a first predetermined rotation speed. The electronic control unit performs the switching control by the square wave control in a second switching mode when the rotation speed of the motor is lower than the first predetermined rotation speed. The first predetermined rotation speed is a rotation speed lower than a first resonance region. The first switching mode is a mode of a switching pattern that suppresses LC resonance in the first resonance region. The second switching mode is a mode of a switching pattern that suppresses LC resonance in a second resonance region lower than the first predetermined rotation speed.

The invention relates to the controlling of a rectifier with multiple electrical phases. In at least one electrical phase, the duty cycles are merged with one another in two consecutive cycles of the pulse-width modulated controlling, i.e. in a first PWM-pulse, the duty cycle is shifted to the end of the PWM-pulse, and in a subsequent PWM-pulse, the duty cycle is shifted to the start of the PWM-pulse. As a result, there must be no switching process between two consecutive PWM-pulses. In this way, the switching losses and consequently the rise in temperature of the rectifier can be minimised.

A motor control device performs rotation control of a motor by supplying a driving waveform to an inverter circuit. The motor control device determines the amount of modulation in accordance with an induced voltage of the motor based on a calculated interpolation angle, and generates the driving waveform by performing pulse modulation by this amount of modulation.

An electric vehicle control device includes: a main transformer to convert AC voltage input to an input winding thereof from an AC power source, and output converted AC voltage from each of a plurality of output windings; a plurality of converter main circuits, each connected to one of a plurality of secondary windings included in the output windings, to convert AC voltage output from connected secondary windings into DC voltage; and a plurality of converter controllers, each targeting for control one of the converter main circuits, to control by pulse width modulation the control-target converter main circuit, by comparing a signal wave and carrier wave. Each of the converter controllers determines a phase angle correction amount of the signal wave and/or the carrier wave, in response to operating state of a load supplied power through a predetermined output winding among the output windings.

An electric vehicle control device includes: a main transformer to convert AC voltage input to an input winding thereof from an AC power source, and output converted AC voltage from each of a plurality of output windings; a plurality of converter main circuits, each connected to one of a plurality of secondary windings included in the output windings, to convert AC voltage output from connected secondary windings into DC voltage; and a plurality of converter controllers, each targeting for control one of the converter main circuits, to control by pulse width modulation the control-target converter main circuit, by comparing a signal wave and carrier wave. Each of the converter controllers determines a phase angle correction amount of the signal wave and/or the carrier wave, in response to operating state of a load supplied power through a predetermined output winding among the output windings.

A rotor assembly has a sleeve, a rotor hub, a lamination core, and a plurality of tapered magnets disposed circumferentially around an inner diameter of the sleeve. The plurality of tapered magnets are configured to abut on one another. The plurality of tapered magnets includes a first set of tapered magnets and a second set of tapered magnets. Insertion of the first set of tapered magnets axially relative to the second set of tapered magnets is configured to increase a diameter of the sleeve. The rotor hub is configured to retain at least one of the lamination core, the plurality of tapered magnets, or the sleeve.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.

A system for an aircraft includes a tiltable proprotor that is tiltable between a lift position for providing lift for the aircraft and a forward flight position for providing forward propulsion for the aircraft is provided. The system includes at least one actuator for adjusting a tilt angle of the tiltable proprotor; and at least one passive damper connected to the tiltable proprotor and configured to limit a rate of change of the tilt angle of the tiltable proprotor.

An electric propulsion system comprising an electric motor assembly. The electric motor assembly may include a housing having an internal volume, a stator ring disposed about a perimeter of the internal volume, and a rotor positioned within the stator. The electric motor assembly may include a main shaft connected to the rotor via a gear reduction, wherein the main shaft extends through the rotor. The electric motor assembly may include a collar connected to the main shaft, wherein the collar encircles the main shaft, and at least a portion of the collar is configured to direct a fluid away from the main shaft and toward the stator ring.