An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.

An electric power supply is described that has direct-current (DC) to alternating-current (AC) circuitry adapted and configured to receive DC power input having a DC input voltage and convert the DC power input to multi-phase, alternating-current (AC) power output. The DC to AC circuitry includes an electromagnetic interference (EMI) noise filter to suppress EMI noise, wherein the EMI noise filter comprises two, electrically insulated, conductive rails configured and adapted to receive the DC power input, ferrite material at least partially surrounding the two conductive rails, and a current sensing element positioned in a gap in the ferrite material and configured to measure leakage current escaping to ground.

An electric power supply is described that has direct-current (DC) to alternating-current (AC) circuitry adapted and configured to receive DC power input having a DC input voltage and convert the DC power input to multi-phase, alternating-current (AC) power output. The DC to AC circuitry includes an electromagnetic interference (EMI) noise filter to suppress EMI noise, wherein the EMI noise filter comprises two, electrically insulated, conductive rails configured and adapted to receive the DC power input, ferrite material at least partially surrounding the two conductive rails, and a current sensing element positioned in a gap in the ferrite material and configured to measure leakage current escaping to ground.

An axial flux electric motor for an aircraft includes a first motor section having a first stator and a first rotor, and a second motor section having a second stator and a second rotor. The first and second rotors are mounted on a common axle. The first rotor is secured to the common axle by a first set of connecting elements. The second rotor is secured to the common axle by a second set of connecting elements. The first set of connecting elements is arranged to break when the relative torque between the common axle and the first rotor is greater than a first particular threshold. The second set of connecting elements is arranged to break when the relative torque between the common axle and the second rotor is greater than a second particular threshold.

An axial flux electric motor for an aircraft includes a first motor section having a first stator and a first rotor, and a second motor section having a second stator and a second rotor. The first and second rotors are mounted on a common axle. The first rotor is secured to the common axle by a first set of connecting elements. The second rotor is secured to the common axle by a second set of connecting elements. The first set of connecting elements is arranged to break when the relative torque between the common axle and the first rotor is greater than a first particular threshold. The second set of connecting elements is arranged to break when the relative torque between the common axle and the second rotor is greater than a second particular threshold.

Drive systems use multiple motors that work together to reduce the propulsion system weight while not sacrificing horsepower while also providing redundancies for safety. The drive systems can be used to power an aircraft. An advantage in the use of multiple smaller, lighter motors in a drive system is that the propulsion system has redundant safety. Should one motor in the propulsion system fail during operation, the other motor or motors will continue to produce thrust to enable the aircraft to continue flight or land safely, as opposed to a forced, no power landing due to a complete motor loss when using one motor.

Drive systems use multiple motors that work together to reduce the propulsion system weight while not sacrificing horsepower while also providing redundancies for safety. The drive systems can be used to power an aircraft. An advantage in the use of multiple smaller, lighter motors in a drive system is that the propulsion system has redundant safety. Should one motor in the propulsion system fail during operation, the other motor or motors will continue to produce thrust to enable the aircraft to continue flight or land safely, as opposed to a forced, no power landing due to a complete motor loss when using one motor.

An aircraft, in particular a personal air mobility aircraft or a drone, having one or more annular propellers, with one or more blades extending radially from a rotor ring body towards the axis of the rotor ring, and one or more belt transmissions, which connect the rotor ring of each annular propeller with the output shaft of a motor unit including an electric motor. Various aircraft configurations include a vertical take-off and horizontal flight configuration. The aircraft surfaces are covered by groups of photovoltaic solar cells connected to a main battery pack for powering the electric motors that drive the annular propellers, and to an auxiliary electric battery for powering the on-board electrical circuit.

An aircraft, in particular a personal air mobility aircraft or a drone, having one or more annular propellers, with one or more blades extending radially from a rotor ring body towards the axis of the rotor ring, and one or more belt transmissions, which connect the rotor ring of each annular propeller with the output shaft of a motor unit including an electric motor. Various aircraft configurations include a vertical take-off and horizontal flight configuration. The aircraft surfaces are covered by groups of photovoltaic solar cells connected to a main battery pack for powering the electric motors that drive the annular propellers, and to an auxiliary electric battery for powering the on-board electrical circuit.