Patent ID: 8528855

Claim:
A hybrid rotor for an aircraft, comprising: a Magnus rotor; a transverse flow rotor; and a guide mechanism; wherein the Magnus rotor is configured to be actuatable to rotate around a Magnus rotor axis by a first propulsion mechanism, and has a closed lateral surface; wherein the transverse flow rotor is configured to be kept rotating around an axis of rotation and has a number of axially extending rotor blades that actuatable to rotate around the axis of rotation by a second propulsion device, and which are configured stationary relative to the tangential angle position; wherein the Magnus rotor is located within the transverse flow rotor and the Magnus rotor axis extends in the direction of the axis of rotation; wherein the guide mechanism has a housing segment partially surrounding the transverse flow rotor in a circumferential direction; wherein the housing segment has an adjustment mechanism and is configured deflectable at least relative to the Magnus rotor axis; wherein the housing segment is aligned in such a way that the transverse flow rotor generates a propelling force and brings about a transverse flow onto the Magnus rotor in such a way that a force is generated according to a Magnus effect, which acts as lifting force.