A stator includes a stator core having a plurality of stator slots that surround a circumference of the stator core. The plurality of stator slots includes six different stator slot groups. The stator further includes a plurality of wave winding coils including a first lane group and a second lane group. Each lane group includes three independent lanes. The lanes of the first lane group include wave winding coils of a first phase, a third phase, and a fifth phase, and the lanes of the second lane group include wave winding coils of a second phase, a fourth phase, and a sixth phase. The wave winding coils of each phase of each lane include a corresponding connector. Each of the wave winding coils of the same phase of different lanes of one lane group is supported by a same slot group among the six stator slot groups.

A stator includes a stator core having a plurality of stator slots that surround a circumference of the stator core. The plurality of stator slots includes six different stator slot groups. The stator further includes a plurality of wave winding coils including a first lane group and a second lane group. Each lane group includes three independent lanes. The lanes of the first lane group include wave winding coils of a first phase, a third phase, and a fifth phase, and the lanes of the second lane group include wave winding coils of a second phase, a fourth phase, and a sixth phase. The wave winding coils of each phase of each lane include a corresponding connector. Each of the wave winding coils of the same phase of different lanes of one lane group is supported by a same slot group among the six stator slot groups.

Provided are a stator, and a propeller driving device and an aircraft using the stator. The propeller driving device includes: a radial gap type BLDC motor with an inner rotor-outer stator structure where a rotor is placed in a circumferential shape with an air gap inside a stator; and a propeller installation bracket for mounting a propeller to a rotary shaft of the motor, wherein the stator includes: a stator core including an annular back yoke having a predetermined width to form a magnetic circuit and teeth extending from the back yoke in a central direction; an insulator formed to surround an outer circumferential surface on which a coil is wound in each tooth; and a stator coil wound around an outer circumferential surface of the insulator in each tooth. The insulator is formed of an insulating heat dissipation composite material having both heat dissipation performance and insulation performance.

Provided are a stator, and a propeller driving device and an aircraft using the stator. The propeller driving device includes: a radial gap type BLDC motor with an inner rotor-outer stator structure where a rotor is placed in a circumferential shape with an air gap inside a stator; and a propeller installation bracket for mounting a propeller to a rotary shaft of the motor, wherein the stator includes: a stator core including an annular back yoke having a predetermined width to form a magnetic circuit and teeth extending from the back yoke in a central direction; an insulator formed to surround an outer circumferential surface on which a coil is wound in each tooth; and a stator coil wound around an outer circumferential surface of the insulator in each tooth. The insulator is formed of an insulating heat dissipation composite material having both heat dissipation performance and insulation performance.

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.

In a control device including a control unit that controls an EPU for powering a rotor included in an electric aircraft, the EPU includes a motor, an inverter, a control circuit, and a first sensor that detects an operation-related value. If there is no a sudden change in the operation-related value detected by the first sensor, the control unit controls the EPU based on the operation-related value detected by the first sensor. When the sudden change occurs, the control unit stops using the operation-related value detected by the first sensor to control the EPU. After the occurrence of the sudden change, when the sudden change ends before a predetermined period elapses, the control unit resumes using the operation-related value detected by the first sensor to control the EPU, and when the sudden change has not ended, the control unit continues the stoppage.

In a control device including a control unit that controls an EPU for powering a rotor included in an electric aircraft, the EPU includes a motor, an inverter, a control circuit, and a first sensor that detects an operation-related value. If there is no a sudden change in the operation-related value detected by the first sensor, the control unit controls the EPU based on the operation-related value detected by the first sensor. When the sudden change occurs, the control unit stops using the operation-related value detected by the first sensor to control the EPU. After the occurrence of the sudden change, when the sudden change ends before a predetermined period elapses, the control unit resumes using the operation-related value detected by the first sensor to control the EPU, and when the sudden change has not ended, the control unit continues the stoppage.

A rotor of an aircraft electric motor includes a shaft made of a first material, and a skin made of a second material different from the first material. The skin includes two half-shells welded together, each half-shell of the two half-shells including a chamfer, and the chamfers assembling the two half-shells together. The shaft includes a shoulder portion the skin being fixed on the shoulder portion. The rotor further includes an interpenetration layer of the first material and of the second material, the interpenetration layer including an alloy of the first material and an alloy of the second material, the interpenetration layer being between the shaft and the skin.

A rotorcraft having an electric drive for driving a main rotor of a rotorcraft, more particularly a helicopter, the electric drive comprising: a coupler for coupling the electric drive to a rotor mast, which can be coupled for conjoint rotation with a drive unit of a helicopter rotor transmission, for coupling for conjoint rotation with the main rotor or tail rotor. A rotorcraft with an electric drive is provided with which the space requirement is reduced, the construction is simplified and the maintenance requirement is reduced. This problem is solved in that the electric drive is designed as an electric ring motor, with the electric ring motor being arranged and attached coaxially with the rotor mast.

A rotorcraft having an electric drive for driving a main rotor of a rotorcraft, more particularly a helicopter, the electric drive comprising: a coupler for coupling the electric drive to a rotor mast, which can be coupled for conjoint rotation with a drive unit of a helicopter rotor transmission, for coupling for conjoint rotation with the main rotor or tail rotor. A rotorcraft with an electric drive is provided with which the space requirement is reduced, the construction is simplified and the maintenance requirement is reduced. This problem is solved in that the electric drive is designed as an electric ring motor, with the electric ring motor being arranged and attached coaxially with the rotor mast.