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 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.

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 joint assembly for an aircraft comprising: a joint comprising a first portion rotatably coupled to a second portion so that the first portion can rotate relative to the second portion; an actuator for rotating the first portion of the joint and comprising a connecting portion that connects to the first portion of the joint; and a latch moveable to a latched arrangement in which the latch prevents rotation of the first portion of the joint in at least one rotational direction, the latch being biased toward the latched arrangement and operatively connected to the connecting portion such that if the connecting portion becomes separated from the rest of the actuator, the latch moves to the latched arrangement, thereby preventing rotation of the first portion of the joint in the at least one rotational direction.

An electrical propulsion system includes an electrical motor configured to drive one or more propellers of the aircraft, a capacitor configured to stabilize a direct current (DC) bus voltage, a first inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to alternate current (AC) voltages to drive a first set of stator windings of the electrical motor, in response to a first pulse width modulation (PWM) vector, and a second inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to AC voltages to drive a second set of stator windings of the electrical motor, in response to a second PWM vector. The first PWM vector and the second PWM vector are substantially equal and opposite vectors.

A brushless electric motor includes a motor casing having a first bearing, a motor end-cap including a second bearing, a multi-phase stator assembly, and a rotor assembly having a rotor shaft. The shaft has a first end, a second end, and a knurled section therebetween. The shaft also has a first bearing surface proximate the first end and supported by the first bearing, a second bearing surface proximate the second end and supported by the second bearing, and a rotor position and speed sensor target. The shaft additionally has a sun gear integrated with the shaft proximate the first bearing surface for engaging a partial planetary gear set. The rotor assembly also includes a rotor lamination fixed to the shaft at the knurled section and having opposing first and second sides, and first and second end plates arranged on the respective first and second sides of the rotor lamination.

A balancing method for balancing at high speed a flexible rotor of a rotary machine, the rotary machine having a stator, and the rotor being supported in the stator by at least two radial magnetic bearings. The balancing method including a step of placing the rotor inside the stator, a step of performing at least one first run in order to identify amplitude and angular location of the unbalance in a first speed range below critical speed, a step of placing first balancing masses inside the rotor on predefined first balancing planes, a step of performing at least one second run in order to identify amplitude and angular location of the unbalance in a second speed range above critical speed, and a step of placing second balancing masses inside the rotor on predefined second balancing planes.

An armature manufacturing method includes preparing a core member that includes a rotation shaft at a central portion and that is formed with plural teeth in a radiating shape centered on the rotation shaft; and winding winding wires onto slots between the plural teeth so as to form plural types of winding coil sections, each with a different winding wire diameter.

An electric motor, in particular for a kitchen machine, is proposed, wherein the rotor of the electric motor has a rotor core with a plurality of sector portions, between which permanent magnets are respectively arranged. The sector portions have outer sides with a changing radius of curvature, the radius of curvature decreasing continuously from the center of the respective outer side in the direction of the adjacent permanent magnets. Alternatively or additionally, the sector portions may have concave recesses each formed between an inner side of the sector portion and an extension extending transversely from the inner side. Further, a kitchen machine having a corresponding electric motor is proposed. Furthermore, a method of manufacturing an electric motor is proposed in which the electric motor is balanced by setting balancing holes on the axial end faces of the rotor core.

Provided is a motor rotor which, without changing an integral fastening structure relying on swage pins, increases resistance to the excessive excitation force of the motor rotor and which can easily prevent decreases in fastening strength; a motor that uses the motor rotor, and an electric compressor are also provided. This motor rotor is provided with a cylindrical rotor core comprising multiple laminated magnetic steel sheets, end plates and balance weights laminated on both ends of the rotor core, and multiple headed swage pins which are inserted from one side and which integrally fasten the rotor core, the end plates and the balance weights. The material of the balance weight arranged to the head of the swage pin is harder than that of the swage pin, and the material of the balance weight arranged to the swage part of the swage pin is softer than that of the swage pin.