A propeller driving unit for an unmanned aerial vehicle (UAV). The propeller driving unit comprises a motor unit comprising a first motor module and a second motor module, with the first motor module being adapted to independently drive a first propeller or a first set of propellers, the second motor module being adapted to independently drive a second propeller or a second set of propellers; wherein the first and second motor modules are coaxially arranged within the motor unit. The invention also relates to an unmanned aerial vehicle comprising the described propeller driving unit.

A vertical takeoff and landing aircraft includes a flight fuselage on which a main wing and auxiliary wings are mounted; a pair of front propellers respectively mounted at both sides of the flight fuselage so as to be variable in the horizontal and vertical directions; a rear propeller mounted on the auxiliary wings provided at the rear of the flight fuselage so as to be variable in the horizontal and vertical directions; front and rear variable parts mounted on the flight fuselage and the auxiliary wings so as to vary the front propellers and the rear propeller in the horizontal or vertical direction; and a control unit for controlling the front and rear variable parts.

An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes an engine, a trinary lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes a plurality of ducted fans in a tandem lateral and forward orientation. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that bypass air combines with engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

The invention relates to a nubomachine with a longitudinal axis, comprising two, respectively upstream (122) and downstream, coaxial outer propellers (122), characterised in that at least some of the blades (148) of the upstream propeller (122) comprise at least one internal air circulation chimney (150) that communicates with air-bleeding openings (152) in tire boundary layers of the blades (148). and communicates with air outflow openings (158) on the radially outer end thereof, the air-bleeding openings (152) leading to opening inlets (152a) on tire passive surfaces (156) of the blades (148). the inlets (152a) of the air-bleeding openings being radially arranged in an area (H1) contained between 10% and 45% of the radial dimension (H2) of the blades (148). measured above turd from the radial height of the blades for which the tangent of the leading edge (138) of the blades is orthogonal to the longitudinal axis, and the inlets (152a) of the air bleeding openings being arranged in an area contained between 0% and 30% of the local chord of the blades (148), measured at the level of said inlets (152a) and from the leading edges (138) of tire blades (148).

An active flow control system for generating yaw control moments for an aircraft during forward flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors that influence the path of airflow above and below the yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.

A propeller structure in the form of twin Mobius blades for an aircraft is provided in which it is possible to easily control flight speed and posture by free movement and interlocking movement through supersymmetrical twisting, it is possible to selectively individually control the left and right propeller blades by rotating and operating the left and right propeller blades of an aircraft body in a spur gear scheme through one drive shaft connected by first to third motors and fourth to sixth motors, respectively, it is possible to enhance the propulsion and control each blade by forming a propeller with a structure a plurality of pairs of blades on both sides of the aircraft body, and it is easy to control the direction by rotating and operating the blades by a tilting scheme of a toothed gear through a drive shaft connected to a tail blade of the aircraft body by a seventh motor.

A propeller structure in the form of twin Mobius blades for an aircraft is provided in which it is possible to easily control flight speed and posture by free movement and interlocking movement through supersymmetrical twisting, it is possible to selectively individually control the left and right propeller blades by rotating and operating the left and right propeller blades of an aircraft body in a spur gear scheme through one drive shaft connected by first to third motors and fourth to sixth motors, respectively, it is possible to enhance the propulsion and control each blade by forming a propeller with a structure a plurality of pairs of blades on both sides of the aircraft body, and it is easy to control the direction by rotating and operating the blades by a tilting scheme of a toothed gear through a drive shaft connected to a tail blade of the aircraft body by a seventh motor.

An active flow control system for generating roll control moments for an aircraft during hover flight. The system includes right and left roll effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left roll effectors. Based upon which of the injectors is injecting pressurized air, the right and left roll effectors generate no roll control moment, generate a roll right control moment or generate a roll left control moment.

An active flow control system for generating roll control moments for an aircraft during forward flight. The system includes right and left roll effectors disposed on a trailing edge of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left roll effectors that influence the path of airflow across the wing. Based upon which of the injectors is injecting pressurized air, the right and left roll effectors generate no roll control moment, generate a roll right control moment or generate a roll left control moment.

An active flow control system for generating roll control moments for an aircraft during forward flight. The system includes right and left roll effectors disposed on a trailing edge of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left roll effectors that influence the path of airflow across the wing. Based upon which of the injectors is injecting pressurized air, the right and left roll effectors generate no roll control moment, generate a roll right control moment or generate a roll left control moment.