The electrified vehicle includes a first motor that drives a first wheel, a second motor that drives a second wheel different from the first wheel, a temperature sensor provided for the first motor, and a control device. The control device estimates the temperature of the first motor based on the detection signal from the temperature sensor, and corrects the temperature of the first motor based on information indicating a relative relation between operation of the first motor and operation of the second motor. These processes allow the control device to estimate the temperature of the second motor, control the operation of the first motor based on the estimated temperature of the first motor, and control the operation of the second motor based on the estimated temperature of the second motor.

The electrified vehicle includes a first motor that drives a first wheel, a second motor that drives a second wheel different from the first wheel, a temperature sensor provided for the first motor, and a control device. The control device estimates the temperature of the first motor based on the detection signal from the temperature sensor, and corrects the temperature of the first motor based on information indicating a relative relation between operation of the first motor and operation of the second motor. These processes allow the control device to estimate the temperature of the second motor, control the operation of the first motor based on the estimated temperature of the first motor, and control the operation of the second motor based on the estimated temperature of the second motor.

An electric propulsion system for a vertical takeoff-and-landing aircraft having an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, a gearbox assembly, and electric motor assembly may each abut at least one of the others. The electric engine may use a liquid, such as oil, for cooling and lubricating components of the inverter assembly, gearbox assembly, and electric motor assembly. Further, the electric engine may use volumes of oil for cooling and lubricating components below a threshold volume so that the electric engines do not require a fire protective barrier.

A motor drive system for an electrified vehicle includes a DC source, such as a battery, and an inverter, which includes one or more phase drivers, each configured to switch current from the DC source to generate AC power upon one or more output terminals using a hybrid of two or more different solid-state switches, each having a corresponding voltage rating. A nine-switch inverter includes three phase drivers, each including high, low, and middle solid-state switches, with Si-MOSFET high and low switches having a first voltage rating of half of the rated voltage of the system, and with Gallium Nitride (GaN) transistors rated to block a full rated voltage of the system used for the middle switches. A delay driver synchronizes timing between two different solid-state switches by energizing control terminals at different rates. The inverter can be operated using near-state pulse-width modulation (NSPWM) to reduce switching losses.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.

An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.

A hybrid vehicle includes an engine; a generator that generates a counter-electromotive force; a motor; a first inverter for the generator; a second inverter for the motor; a step-up converter that steps up an electric power of a first voltage system electric power line and supplies the electric power to a second voltage system electric power line; and a smoothing capacitor of the second voltage system electric power line. In a case where the hybrid vehicle travels by driving the engine in a state in which the stepping up by the step-up converter and an operation of the first inverter are stopped when an abnormality occurs in a voltage sensor, when an electronic control unit determines that there is an indication that the voltage of the capacitor will rise, the first inverter is controlled to cause three phases of the first inverter to be in an ON state.

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.

A motor control device performs rotation control of a motor by supplying a first driving waveform and a second driving waveform respectively to a pair of switching elements which make up part of upper and lower arms in an inverter circuit. The motor control device determines the amount of modulation of the second driving waveform from a combination of the calculated interpolation angle and the rotational speed of the motor. The motor control device generates the first driving waveform having a rectangular shape, and further generates the second driving waveform by performing pulse modulation by the determined amount of modulation.