Provided is a propulsion system, including a first propulsion unit, a second propulsion unit, a rotor, a first coupling and a second coupling. The first propulsion unit is configured for being fixedly mounted to an airframe. The rotor is configured for being pivotably mounted with respect to the first propulsion unit to allow selectively pivoting of the rotor from a horizontal mode to a vertical mode. The first coupling is configured for selectively coupling and decoupling the rotor with respect to the first propulsion unit. The second coupling is configured for selectively coupling and decoupling the rotor with respect to the second propulsion unit, independently of the first coupling.

Provided is a propulsion system, including a first propulsion unit, a second propulsion unit, a rotor, a first coupling and a second coupling. The first propulsion unit is configured for being fixedly mounted to an airframe. The rotor is configured for being pivotably mounted with respect to the first propulsion unit to allow selectively pivoting of the rotor from a horizontal mode to a vertical mode. The first coupling is configured for selectively coupling and decoupling the rotor with respect to the first propulsion unit. The second coupling is configured for selectively coupling and decoupling the rotor with respect to the second propulsion unit, independently of the first coupling.

An aerial vehicle includes a hull containing the main processor, energy storage, support components such as sensors, wireless communication, and landing gear. Attached to the hull are at least three thrust or propulsion units each with two degrees of freedom from the hull allowing them to orient independently in any direction and apply thrust independently from the hull or any other thrust or propulsion unit. In some embodiments, a mount for auxiliary attachments is included or the auxiliary system is built into the hull. Components like the energy storage, auxiliary attachments, and/or propulsion units may also be replaceable as required.

An aerial vehicle includes a hull containing the main processor, energy storage, support components such as sensors, wireless communication, and landing gear. Attached to the hull are at least three thrust or propulsion units each with two degrees of freedom from the hull allowing them to orient independently in any direction and apply thrust independently from the hull or any other thrust or propulsion unit. In some embodiments, a mount for auxiliary attachments is included or the auxiliary system is built into the hull. Components like the energy storage, auxiliary attachments, and/or propulsion units may also be replaceable as required.

Techniques to control flight of an aircraft are disclosed. In various embodiments, a set of inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is determined.

Techniques to control flight of an aircraft are disclosed. In various embodiments, a set of inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is determined.

The unmanned aerial vehicle, UAV, has a fuselage (1) with at least one rotating shaft (2) and one wing (3) positioned on the rotating shaft (2), protruding from either side of the fuselage (1). Preferably, the UAV has at least one rotor propeller (4) arranged on each rotating shaft (2), on either side of the fuselage (1), with one or more rotor blades (4a) and a housing (4b), which includes an actuator. The UAV is capable of shifting between a first flight mode using rotatable wings that rotate freely around the rotating shaft (2) only due to a direction and strength of wind impinging against a surface of the wings (3) and a downstream flow generated by the rotor propellers (4), and a second flight mode using fixed wings, kept in a predetermined position by a wing-locking mechanism, preferably a substantially horizontal position.

A flying vehicle includes a first rotor assembly, a second rotor assembly and a second rotor assembly pylon arranged to mount the second rotor assembly to the remainder of the flying vehicle. The first rotor assembly and the second rotor assembly are located so that they are spaced in a longitudinal direction of the flying vehicle and so they are substantially on a vertical plane that is parallel to a vertical plane aligned with a longitudinal axis of the flying vehicle. The first rotor assembly includes a tilt-rotor arranged to tilt between delivery of substantially vertical flight thrust and substantially conventional flight thrust. The second rotor assembly includes a stacked plurality of substantially vertical thrust rotors mounted to the pylon so as to be substantially to the same side of the pylon.

A flying vehicle includes a first rotor assembly, a second rotor assembly and a second rotor assembly pylon arranged to mount the second rotor assembly to the remainder of the flying vehicle. The first rotor assembly and the second rotor assembly are located so that they are spaced in a longitudinal direction of the flying vehicle and so they are substantially on a vertical plane that is parallel to a vertical plane aligned with a longitudinal axis of the flying vehicle. The first rotor assembly includes a tilt-rotor arranged to tilt between delivery of substantially vertical flight thrust and substantially conventional flight thrust. The second rotor assembly includes a stacked plurality of substantially vertical thrust rotors mounted to the pylon so as to be substantially to the same side of the pylon.

A rotor system for an aircraft is described and includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast. The drive system includes at least one electric motor for providing rotational energy to a motor shaft; and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the motor shaft and providing rotational energy to the rotor mast via a rotor shaft.