An electric machine, (e.g., for an aircraft), includes a stator and a rotor that is rotatable relative to the stator, wherein a gap by way of which magnetic forces act between the stator and the rotor is configured between a gap face of the stator and a gap face of the rotor. The electric machine further includes a bearing installation by which the rotor is mounted so as to be rotatable relative to the stator in such a manner that the gap face of the rotor in a normal operation of the electric machine is spaced apart from the gap face of the stator. The stator and/or the rotor have/has a friction-reducing layer that at least partially forms the respective gap face and, along which the respective other gap face, is configured to slide in the event of a defect.

An electric machine, (e.g., for an aircraft), includes a stator and a rotor that is rotatable relative to the stator, wherein a gap by way of which magnetic forces act between the stator and the rotor is configured between a gap face of the stator and a gap face of the rotor. The electric machine further includes a bearing installation by which the rotor is mounted so as to be rotatable relative to the stator in such a manner that the gap face of the rotor in a normal operation of the electric machine is spaced apart from the gap face of the stator. The stator and/or the rotor have/has a friction-reducing layer that at least partially forms the respective gap face and, along which the respective other gap face, is configured to slide in the event of a defect.

A controller (a control unit) of a power supply system of a vertical take-off and landing aircraft is configured to: after lift is generated by wings (a front wing and a rear wing), perform stop control of controlling electric power supplied to a motor so that rotation of a VTOL rotor continues to stop; temporarily cancel the stop control in response to the temperature of any one switching element detected by a temperature detection unit (a temperature sensor) becoming equal to or higher than a temperature threshold during the stop control; and resume the stop control after the stop control has been temporarily canceled.

An articulating motor mount assembly including a first frame segment attachable to an airframe of an aircraft. A second frame segment is rotatably coupled to the first frame segment in a plane oblique to a longitudinal axis of the first frame segment. A third frame segment is rotatably coupled to the second frame segment in a plane oblique to a longitudinal axis of the second frame segment and configured to carry a thrust device. A first actuator is positioned to rotate the second frame segment relative to the first frame segment and a second actuator is positioned to rotate the third frame segment relative to the second frame segment.

An articulating motor mount assembly including a first frame segment attachable to an airframe of an aircraft. A second frame segment is rotatably coupled to the first frame segment in a plane oblique to a longitudinal axis of the first frame segment. A third frame segment is rotatably coupled to the second frame segment in a plane oblique to a longitudinal axis of the second frame segment and configured to carry a thrust device. A first actuator is positioned to rotate the second frame segment relative to the first frame segment and a second actuator is positioned to rotate the third frame segment relative to the second frame segment.

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 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.

A stator for an electric machine comprises: a body; a plurality of stator teeth fixed on the body; anda plurality of tooth windings, which each have a first electrical conductor, which runs from one end portion, via at least one winding portion around at least one stator tooth, to another end portion, and a second electrical conductor, which is electrically insulated from the first electrical conductor and which runs from one end portion, via the at least one winding portion around the same at least one stator tooth, to another end portion; wherein one end portion of each of the first and second electrical conductors of the tooth windings can be or is electrically connected to an inverter, and the other end portions of the first electrical conductors of the tooth windings are electrically interconnected at a star point.

A stator for an electric machine comprises: a body; a plurality of stator teeth fixed on the body; anda plurality of tooth windings, which each have a first electrical conductor, which runs from one end portion, via at least one winding portion around at least one stator tooth, to another end portion, and a second electrical conductor, which is electrically insulated from the first electrical conductor and which runs from one end portion, via the at least one winding portion around the same at least one stator tooth, to another end portion; wherein one end portion of each of the first and second electrical conductors of the tooth windings can be or is electrically connected to an inverter, and the other end portions of the first electrical conductors of the tooth windings are electrically interconnected at a star point.

Provided are a rotor, and a propeller driving device and an aircraft using same. The propeller driving device includes: a housing in which an upper cover and a lower cover having a plurality of through holes are respectively coupled to an upper portion and a lower portion of a cylindrical case; a stator arranged inside the case; a rotor arranged at a distance from the stator; and a rotary shaft connected to the rotor through a plurality of bridges and having both ends rotatably supported by an upper bearing and a lower bearing positioned at respective centers of the upper cover and the lower cover, wherein inner cooling of a motor is formed by an air flow passage that passes through a plurality of through holes of the upper cover and the lower cover and a plurality of spaces formed between the plurality of bridges.