A locking system for an electric propulsion system is disclosed. The system includes a propulsor configured to propel an electric vehicle and a motor operatively connected to the propulsor configured to power the propulsor. The motor includes a rotor connected to the propulsor and a stator configured to rotate the rotor. A propulsor sensor is configured to determine a motion parameter of the propulsor. A lock is configured to prevent a movement of the propulsor. A controller is configured to receive a signal from the propulsor sensor and control the motor as a function of the signal from the propulsor sensor, wherein controlling the motor includes allowing the propulsor to slow at a desired rate for parking.

Techniques for deicing propellers for mobile platforms are disclosed. In one embodiment, a system is provided. The system may include a propeller comprising a propeller blade having a channel extending from an ingress aperture to an egress aperture along a longitudinal axis of the propeller blade. The system may further include a cowl comprising an air duct configured to direct heated air into the channel to deice the propeller blade. The cowl may be configured to selectively couple to the propeller and an electric motor and form a seal between the cowl and the electric motor to capture the heated air exuded by the electric motor. Additional systems and methods are also disclosed.

Provided is a motor for a drone comprising: a rotary shaft; a stator including a hole in which the rotary shaft is disposed; a rotor disposed outside the stator; and a housing coupled to the stator, wherein the stator comprises a stator core and a coil wound around the stator core, wherein the stator core comprises an annular yoke coupled to the housing, teeth extending radially from the yoke, and a shoe disposed at one end of the teeth, wherein the teeth comprise protrusions projecting from the side surface thereof. As such, the present invention provides an advantageous effect of securing an air flow path for heat radiation to enhance a heat radiating effect while preventing water or foreign matter from flowing into the motor.

Provided is a motor for a drone comprising: a rotary shaft; a stator including a hole in which the rotary shaft is disposed; a rotor disposed outside the stator; and a housing coupled to the stator, wherein the stator comprises a stator core and a coil wound around the stator core, wherein the stator core comprises an annular yoke coupled to the housing, teeth extending radially from the yoke, and a shoe disposed at one end of the teeth, wherein the teeth comprise protrusions projecting from the side surface thereof. As such, the present invention provides an advantageous effect of securing an air flow path for heat radiation to enhance a heat radiating effect while preventing water or foreign matter from flowing into the motor.

In examples, provided are leadless power couplers that include (1) a thermal insulating system having an outer wall and an inner wall, (2) a first electrically conductive winding located outside the thermal insulating system, where the first electrically conductive winding is configured to create a varying magnetic field, (3) a plurality of second electrically conductive windings located inside the thermal insulating system and configured to couple to the varying magnetic field, the plurality of second electrically conductive windings being superconductors, (4) a plurality of cryogenic rectifiers, each cryogenic rectifier being coupled to a respective second electrically conductive winding in the plurality of second electrically conductive windings, and (5) a plurality of cryogenic cables coupled between respective outputs of the plurality of cryogenic rectifiers and respective loads.

In examples, provided are leadless power couplers that include (1) a thermal insulating system having an outer wall and an inner wall, (2) a first electrically conductive winding located outside the thermal insulating system, where the first electrically conductive winding is configured to create a varying magnetic field, (3) a plurality of second electrically conductive windings located inside the thermal insulating system and configured to couple to the varying magnetic field, the plurality of second electrically conductive windings being superconductors, (4) a plurality of cryogenic rectifiers, each cryogenic rectifier being coupled to a respective second electrically conductive winding in the plurality of second electrically conductive windings, and (5) a plurality of cryogenic cables coupled between respective outputs of the plurality of cryogenic rectifiers and respective loads.

A stowable lift rotor is coupled to an airframe of a VTOL aircraft. The VTOL aircraft is convertible between a VTOL flight mode and a forward flight mode. The stowable lift rotor includes a lift arm. The proximal end of the lift arm is coupled to the airframe of the VTOL aircraft. The stowable lift rotor also includes a rotor assembly including rotor blades coupled to the distal end of the lift arm. The lift arm is movable between various positions including an extended position in the VTOL flight mode, a stowed position in the forward flight mode and intermediate positions therebetween such that the distance between the rotor assembly and the airframe is greater in the extended position than in the stowed position.

An unmanned aerial vehicle (UAV) has a flight-only mode with a motor only rotating propellers and not rotating on-board wheels to configure the UAV to fly away from a surface of a structure, and a crawling-only mode in which the UAV is configured to crawl on the surface due to the motor only rotating the wheels while not rotating the propellers. In the flight-only mode, a clutch disengages a motor from the wheels so that the motor only engages the propellers to fly to lift from the surface. In the crawling-only mode, the clutch disengages the motor from the propellers so that the motor only engages the wheels to move the UAV on the surface.

The invention relates to a hybrid propulsion architecture (100) for an aircraft, comprising: —a first source (102) of a first energy type, —second sources (104) of a second energy type different from the first energy type, —electrical propulsion systems (106), —an electric power supply network (118) connecting the first and second sources (102, 104) to the electrical propulsion systems, such that each electrical propulsion system is powered by the first source and by one of the second sources, the architecture being characterised in that it further comprises: —means for segregating (120) the electrical propulsion systems, which means are arranged in the electric power supply network and configured to impose a direction of flow of the electric power from the first source to the electrical propulsion systems.

Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.