An aircraft wing, comprising: a plurality of ribs, each rib including a plurality of wire openings, wherein each of the plurality of wire openings are enclosed by one of the plurality of ribs and a skin of the aircraft; and a plurality of high voltage wires disposed in the wire openings in the plurality of ribs such that each wire opening receives only one high voltage wire, and the each wire opening has an opening size larger than a size of the one high voltage wire, the opening size being smaller than a size of a connector mounted to an end of the one high voltage wire and configured to allow mating with another high voltage wire or an electrical component.

A propulsor brake lock system includes an aircraft propulsor, a reduction gear assembly, a brake shaft, and a brake assembly. The aircraft propulsor includes a propeller having a propeller input shaft coupled thereto. The reduction gear assembly includes at least an input gear and an output gear. The input gear and output gear are both rotatable with the propeller input shaft. The brake shaft is coupled to, and is rotatable with, the output gear. The brake assembly is coupled to the brake shaft and is moveable between a disengaged position, in which the brake shaft may rotate whenever the output gear rotates, and an engaged position, in which the brake shaft is prevented from rotating, thereby preventing rotation of the output gear, the input gear, and the propeller input shaft.

A propulsor brake lock system includes an aircraft propulsor, a reduction gear assembly, a brake shaft, and a brake assembly. The aircraft propulsor includes a propeller having a propeller input shaft coupled thereto. The reduction gear assembly includes at least an input gear and an output gear. The input gear and output gear are both rotatable with the propeller input shaft. The brake shaft is coupled to, and is rotatable with, the output gear. The brake assembly is coupled to the brake shaft and is moveable between a disengaged position, in which the brake shaft may rotate whenever the output gear rotates, and an engaged position, in which the brake shaft is prevented from rotating, thereby preventing rotation of the output gear, the input gear, and the propeller input shaft.

An EPU includes a motor unit, a blower device, and a labyrinth structure portion. The motor unit includes a motor, an inverter, and a unit housing. The unit housing accommodates the motor and the inverter in a unit space. In the unit housing, a unit inlet port and a unit outlet port are in communication with the unit space. In the EPU, as the blower device blows air, cooling air flows into the unit space from the unit inlet port and flows out from the unit outlet port. The cooling air flows into the unit inlet port after passing through the labyrinth structure portion. In the labyrinth structure portion, foreign matter is removed from the cooling air.

An EPU includes a motor unit, a blower device, and a labyrinth structure portion. The motor unit includes a motor, an inverter, and a unit housing. The unit housing accommodates the motor and the inverter in a unit space. In the unit housing, a unit inlet port and a unit outlet port are in communication with the unit space. In the EPU, as the blower device blows air, cooling air flows into the unit space from the unit inlet port and flows out from the unit outlet port. The cooling air flows into the unit inlet port after passing through the labyrinth structure portion. In the labyrinth structure portion, foreign matter is removed from the cooling air.

In one embodiment, a rotating electric machine includes a rotor and a stator. The rotor is a rotor which is rotatable around a center axis. The stator surrounds the rotor from one radial side. The stator includes a back yoke, a coil unit, and a plurality of partition units. The back yoke has an annular shape centered on the center axis. The coil unit is disposed on the other radial side of the back yoke. The plurality of partition units partition a winding range in which the coil unit is disposed in a circumferential direction. Each of the partition units includes a magnetic body portion made of a magnetic material. A circumferential dimension of the magnetic body portion is less than a circumferential dimension of the winding range. A radial dimension of the magnetic body portion is or more of a radial dimension of the coil unit.

Aircraft electric machines are described. The aircraft electric machines include a laminated rotor operably connected to a shaft, the laminated rotor comprising a plurality of rotor teeth and air gaps defined between adjacent rotor teeth about a circumference of the laminated rotor, a modular stator assembly comprising at least one stator segment having a winding wrapped about a center body of the at least one stator segment, a cooling element arranged at least one of adjacent to or within the winding, and at least one power module system comprising an active rectifier and wherein the laminated rotor and modular stator are arranged as a switched reluctance rotor-stator assembly.

Aircraft electric machines are described. The aircraft electric machines include a laminated rotor operably connected to a shaft, the laminated rotor comprising a plurality of rotor teeth and air gaps defined between adjacent rotor teeth about a circumference of the laminated rotor, a modular stator assembly comprising at least one stator segment having a winding wrapped about a center body of the at least one stator segment, a cooling element arranged at least one of adjacent to or within the winding, and at least one power module system comprising an active rectifier and wherein the laminated rotor and modular stator are arranged as a switched reluctance rotor-stator assembly.

This aircraft is a Vertical Take Off and Landing Fighter type. The primary power source will be a low bypass jet turbine/engine. The auxiliary power source will be provided by axial flux electric motors. These motors will be housed in a moveable section, the EVTOL apparatus, that houses multiple turbines. These moveable sections will be attached to sides of the fuselage, extending into the dual wing. These moveable sections will move to a vertical position during take-off and landing; and be in a horizontal position during normal flight. These moveable sections will have an intake area aft, and vectoring thrust at the rear. This aircraft is a hybrid utilizing a gas jet turbine and electrical axial flux motors. The EVTOL apparatus is a compact self-contained unit capable of generating thrust through a turbine driven by Axial Flux electric motors.

An electric motor includes a stator having a first side and a second side, a first housing coupled to the first side of the stator, and a second housing coupled to the second side of the stator. A shaft of the electric motor has a first end and a second end. The shaft is rotatably supported by a first bearing and a second bearing. A propeller of the electric motor couples to the first end of the shaft. An inverter includes an inverter housing directly coupled to the first housing.