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.

A first relay device, a second relay device, a third relay device, a fourth relay device, and a first connection device of a power supply system are disposed in areas different from each other.

A joint assembly for an aircraft comprising: a joint comprising a first portion rotatably coupled to a second portion so that the first portion can rotate relative to the second portion; an actuator for rotating the first portion of the joint and comprising a connecting portion that connects to the first portion of the joint; and a latch moveable to a latched arrangement in which the latch prevents rotation of the first portion of the joint in at least one rotational direction, the latch being biased toward the latched arrangement and operatively connected to the connecting portion such that if the connecting portion becomes separated from the rest of the actuator, the latch moves to the latched arrangement, thereby preventing rotation of the first portion of the joint in the at least one rotational direction.

A joint assembly for an aircraft comprising: a joint comprising a first portion rotatably coupled to a second portion so that the first portion can rotate relative to the second portion; an actuator for rotating the first portion of the joint and comprising a connecting portion that connects to the first portion of the joint; and a latch moveable to a latched arrangement in which the latch prevents rotation of the first portion of the joint in at least one rotational direction, the latch being biased toward the latched arrangement and operatively connected to the connecting portion such that if the connecting portion becomes separated from the rest of the actuator, the latch moves to the latched arrangement, thereby preventing rotation of the first portion of the joint in the at least one rotational direction.

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.

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.

An inverter assembly for an electrical propulsion system comprises at least one printed circuit board assembly (PCBA) having a plurality of power modules, a thermal plate comprising one or more channels, a plurality of fin arrays thermally coupled to the plurality of power modules, and a housing. The plurality of fin arrays are configured to receive a fluid from the one or more channels. The at least one printed circuit board assembly and the thermal plate are disposed within the housing.

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.

An aircraft comprising at least one propulsion assembly comprising: at least one electric motor, a transmission system, at least one coupling module comprising a freewheel inserted between inner and outer shafts coupled by first and second coupling mechanisms to the output and input shafts of the electric motor and of the transmission system, at least one of the first and second coupling mechanisms comprising an angle gearset, at least one hollow intermediate element in which the output shaft of the electric motor, the input shaft of the transmission system and the inner and outer tubes of the coupling module are at least partially positioned.