A propulsion system, comprising: a motor assembly including a stator and a rotor, a heat exchanger configured to receive air to cool a liquid, and a thermal plate including one or more channels configured to convey the liquid from the heat exchanger to the motor assembly. The heat exchanger is mechanically and fluidically coupled to the thermal plate.

An electrical system for an aircraft, comprising at least one processor configured to: receive aircraft movement information, detect that the movement information indicates a potential crash, detect a loss of continuity in at least one low voltage wire, and blow a battery pack fuse to disconnect supply of the high voltage power to the aircraft.

An electrical propulsion system comprises an inverter, an electrical motor assembly, an assembly, and a rotor position sensor. The inverter comprises a printed circuit board assembly (PCBA). The electrical motor assembly comprises a stator and a rotor. The assembly is configured to rotate a propeller and comprises a moving component and a stationary component. The rotor position sensor comprises at least one sensor coupled to the PCBA, and a magnet located on the moving component. The at least one sensor is configured to detect a magnetic field of the magnet through the stationary component.

Electrically powered vehicles with redundant power distribution circuits employ inverters and a multi-phase alternating current (AC) motor. An electrically powered vehicle includes batteries, inverters, interphase transformers, and a three-phase AC motor. Each of the inverters generates a three-phase AC input from power supplied by an associated one of the batteries. The interphase transformers generate drive phases for the AC motor from the three-phase AC inputs generated by the inverters.

A motor gearbox assembly includes a gearbox housing that encloses a motor comprising a stator and a rotor, which is rotatable with respect to the stator. The rotor is rotatably mounted on a main power output shaft and is coupled to a first rotor pinion gear. The assembly further comprises a layshaft rotatably mounted in the gearbox housing outside of the motor, a first layshaft gear at a first axial end of the layshaft on a first side of the rotor and the stator, the first layshaft gear being engaged with the first rotor pinion gear and a second layshaft gear at a second axial end of the layshaft, the second axial end being on a second side of the rotor and the stator that is opposite the first side, the second layshaft gear being engaged with a power output gear coupled to the main power output shaft.

A motor gearbox assembly includes a gearbox housing that encloses a motor comprising a stator and a rotor, which is rotatable with respect to the stator. The rotor is rotatably mounted on a main power output shaft and is coupled to a first rotor pinion gear. The assembly further comprises a layshaft rotatably mounted in the gearbox housing outside of the motor, a first layshaft gear at a first axial end of the layshaft on a first side of the rotor and the stator, the first layshaft gear being engaged with the first rotor pinion gear and a second layshaft gear at a second axial end of the layshaft, the second axial end being on a second side of the rotor and the stator that is opposite the first side, the second layshaft gear being engaged with a power output gear coupled to the main power output shaft.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45 diameter) footprint.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45 diameter) footprint.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45 diameter) footprint.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45 diameter) footprint.