An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The aerial vehicle may be powered with electric motors.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The aerial vehicle may be powered with electric motors.

Disclosed is a design for high efficiency double pitch angle propellers, having a propeller hub, and two or more propeller blades with airfoil-shaped cross-section fixed around the periphery of the hub at equal angles. The blades have a geometric pitch angle together with the rotation direction as well as a second pitch angle that forms an acute angle or a wide angle with respect to the rotation axis, from its frontal side. The advantage of the second pitch angle is that it has no torque effect on the motor as there is not any force component on the rotation direction. Therefore for the additional pitch obtained from the second pitch angle. The propeller does not attract extra energy from the motor.

Disclosed is a design for high efficiency double pitch angle propellers, having a propeller hub, and two or more propeller blades with airfoil-shaped cross-section fixed around the periphery of the hub at equal angles. The blades have a geometric pitch angle together with the rotation direction as well as a second pitch angle that forms an acute angle or a wide angle with respect to the rotation axis, from its frontal side. The advantage of the second pitch angle is that it has no torque effect on the motor as there is not any force component on the rotation direction. Therefore for the additional pitch obtained from the second pitch angle. The propeller does not attract extra energy from 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, and is configured to drive the propeller to rotate through the rotator. The connection assembly is arranged between the propeller and the motor, and includes a locking member and an elastic member. The elastic member is configured to provide a force onto the locking member in response to the propeller being locked to the motor by the locking member, to maintain a locking state of the locking member.

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, and is configured to drive the propeller to rotate through the rotator. The connection assembly is arranged between the propeller and the motor, and includes a locking member and an elastic member. The elastic member is configured to provide a force onto the locking member in response to the propeller being locked to the motor by the locking member, to maintain a locking state of the locking member.

Provided herein is a rotor attachment assembly for an aircraft. A rotor attachment assembly includes a connecting assembly associated with the aircraft and a rotor assembly configured to be connected to the connecting assembly. The rotor assembly includes a plurality of fins configured to fit a respective plurality of cut-outs of the connecting assembly, a hollow section configured to accommodate at least a part of a pin of the connecting assembly so as to center the rotor assembly relative to the connecting assembly, and a spring configured to expand to allow the fins to pass and to close to retain the fins when the rotor assembly is connected to the connecting assembly.

An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight. An aerial vehicle adapted to withstand impacts upon its propellers. An aerial vehicle able to quickly alter the thrust of its propellers.

An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight. An aerial vehicle adapted to withstand impacts upon its propellers. An aerial vehicle able to quickly alter the thrust of its propellers.

A rotor assembly includes a motor, a propeller, and a connection assembly. The motor includes a stator and a rotator rotatable with respect to the stator. The connection assembly includes a locking member provided between the propeller and the rotator. The locking member is configured to rotate with respect to the rotator and the propeller to lock the propeller to the motor.