A flight propulsion system for Vertical Take-Off and Landing (VTOL) and Short Take-Off and Landing (STOL) aircraft, having a two cyclorotors, installed in the front and rear portions of a pair-wings mechanism involving top wing and bottom wing, three degree-of-freedom DOF adjusting mechanism for pair-wings, a dielectric barrier discharge (DBD) plasma actuators, a bar mechanism for pitching oscillation and rotation speed controls and rear cyclorotor, a yawing mechanism for rear cyclorotor, all on each side of the flight vehicle. This propulsion system is particularly useful for VTOL aircraft. The main features are: high controllability and manoeuvrability, low noise and environmental pollutions, VTOL, STOL, hover state flights, marine and ground take-off and landing, high safety, suitable for different aircraft scales and for different missions and purposes, instant altering the flight direction.

A flight propulsion system for Vertical Take-Off and Landing (VTOL) and Short Take-Off and Landing (STOL) aircraft, having a two cyclorotors, installed in the front and rear portions of a pair-wings mechanism involving top wing and bottom wing, three degree-of-freedom DOF adjusting mechanism for pair-wings, a dielectric barrier discharge (DBD) plasma actuators, a bar mechanism for pitching oscillation and rotation speed controls and rear cyclorotor, a yawing mechanism for rear cyclorotor, all on each side of the flight vehicle. This propulsion system is particularly useful for VTOL aircraft. The main features are: high controllability and manoeuvrability, low noise and environmental pollutions, VTOL, STOL, hover state flights, marine and ground take-off and landing, high safety, suitable for different aircraft scales and for different missions and purposes, instant altering the flight direction.

A power distribution system for an electric aircraft includes a first electric propulsion unit comprising at least two power stages; a first battery pack electrically connected to a first power stage of the at least two power stages; a second battery pack electrically connected to a second power stage of the at least two power stages; and a control system configured to control the first battery pack, the second battery pack, the first power stage, and the second power stage to transfer power from the first battery pack to the second battery pack through the first power stage and the second power stage.

A power distribution system for an electric aircraft includes a first electric propulsion unit comprising at least two power stages; a first battery pack electrically connected to a first power stage of the at least two power stages; a second battery pack electrically connected to a second power stage of the at least two power stages; and a control system configured to control the first battery pack, the second battery pack, the first power stage, and the second power stage to transfer power from the first battery pack to the second battery pack through the first power stage and the second power stage.

A rotor assembly includes a propeller, a motor, and a connection assembly. The motor includes a stator and a rotator rotatable with respect to the stator. The connection assembly is configured to connect the propeller to the motor and includes a locking member that is arranged between the propeller and the motor. The locking member is configured to rotate with respect to the rotator and the propeller in a rotation direction identical to a rotation direction of the propeller in operation to lock the propeller to the motor.

A rotor assembly includes a propeller, a motor, and a connection assembly. The motor includes a stator and a rotator rotatable with respect to the stator. The connection assembly is configured to connect the propeller to the motor and includes a locking member that is arranged between the propeller and the motor. The locking member is configured to rotate with respect to the rotator and the propeller in a rotation direction identical to a rotation direction of the propeller in operation to lock the propeller to the motor.

The technology described herein relates to autonomous aerial vehicle rotor configurations. In some embodiments, the aerial vehicle includes a central body that extends along a longitudinal axis from a forward end to an aft end including a port side opposite a starboard side. Multiple rotor arms each have a proximal end coupled to the central body and a rotor assembly arranged at a distal end to provide propulsion for the aerial vehicle. The rotor assemblies include a first set of rotor assemblies and a second set of rotor assemblies. The first set of rotor assemblies are arranged in a non-inverted configuration on a top side of the aerial vehicle such that each rotor assembly includes an upward-facing rotor. The second set of rotor assemblies are arranged in an inverted configuration on a bottom side of the aerial vehicle such that each rotor assembly includes a downward-facing rotor.

The technology described herein relates to autonomous aerial vehicle rotor configurations. In some embodiments, the aerial vehicle includes a central body that extends along a longitudinal axis from a forward end to an aft end including a port side opposite a starboard side. Multiple rotor arms each have a proximal end coupled to the central body and a rotor assembly arranged at a distal end to provide propulsion for the aerial vehicle. The rotor assemblies include a first set of rotor assemblies and a second set of rotor assemblies. The first set of rotor assemblies are arranged in a non-inverted configuration on a top side of the aerial vehicle such that each rotor assembly includes an upward-facing rotor. The second set of rotor assemblies are arranged in an inverted configuration on a bottom side of the aerial vehicle such that each rotor assembly includes a downward-facing rotor.

A bearing system includes an inboard bearing assembly and an outboard bearing assembly. The inboard bearing assembly includes an inboard fitting and an inboard race. The inboard fitting includes a plate with a convex mating surface and a first aperture formed through the plate for receiving a blade root of a rotor blade. The inboard race comprising a concave mating surface configured to receive the convex mating surface a second aperture formed the inboard race. The outboard bearing assembly includes an outboard bearing assembly comprising an outboard fitting having an aperture formed therethrough for receiving the blade root of the rotor blade.

A bearing system includes an inboard bearing assembly and an outboard bearing assembly. The inboard bearing assembly includes an inboard fitting and an inboard race. The inboard fitting includes a plate with a convex mating surface and a first aperture formed through the plate for receiving a blade root of a rotor blade. The inboard race comprising a concave mating surface configured to receive the convex mating surface a second aperture formed the inboard race. The outboard bearing assembly includes an outboard bearing assembly comprising an outboard fitting having an aperture formed therethrough for receiving the blade root of the rotor blade.