An electrically-powered tip-jet engine system for turning an aircraft rotor blade comprises first and second fan assemblies having substantially the same moment of inertia and configured to rotate at the same angular speed, each fan assembly comprising a respective plurality of fan blades and a respective electric motor rotor; and a rigid frame assembly comprising an electric motor stator assembly and configured for mounting to the aircraft rotor blade. The first fan assembly is effective to create thrust in a thrust direction by rotating clockwise with respect to the thrust direction, and the second fan assembly is effective to create thrust in the thrust direction by rotating counter-clockwise with respect to the thrust direction. The rotation in opposing directions of the first and second fan assemblies is effective to eliminate gyroscopic effect on the aircraft rotor blade.

An electrically-powered tip-jet engine system for turning an aircraft rotor blade comprises first and second fan assemblies having substantially the same moment of inertia and configured to rotate at the same angular speed, each fan assembly comprising a respective plurality of fan blades and a respective electric motor rotor; and a rigid frame assembly comprising an electric motor stator assembly and configured for mounting to the aircraft rotor blade. The first fan assembly is effective to create thrust in a thrust direction by rotating clockwise with respect to the thrust direction, and the second fan assembly is effective to create thrust in the thrust direction by rotating counter-clockwise with respect to the thrust direction. The rotation in opposing directions of the first and second fan assemblies is effective to eliminate gyroscopic effect on the aircraft rotor blade.

An aircraft (100) with a rotary wing (40) is equipped with a propulsion system (10). The aircraft (100) includes a rotating mast (50) that rotates the rotor wing (40). The propulsion system (10) includes a pole (20) mechanically connected to the rotating mast (50) of the aircraft (100), where at least one end of the pole (20) is equipped with a motor (30) configured to rotate the pole (20) around the axis of the rotating mast (50) in such a way that the rotation of the pole (20) can be used to rotate the rotating wing (40). At each end of the pole (20) is placed a motor group (30), where each motor group (30) includes a pair of counter-rotating propellers (32,32), said pair of counter-rotating propellers (32,32) being arranged in such a way as to generate a rotational torque to rotate the pole (20).

An aircraft (100) with a rotary wing (40) is equipped with a propulsion system (10). The aircraft (100) includes a rotating mast (50) that rotates the rotor wing (40). The propulsion system (10) includes a pole (20) mechanically connected to the rotating mast (50) of the aircraft (100), where at least one end of the pole (20) is equipped with a motor (30) configured to rotate the pole (20) around the axis of the rotating mast (50) in such a way that the rotation of the pole (20) can be used to rotate the rotating wing (40). At each end of the pole (20) is placed a motor group (30), where each motor group (30) includes a pair of counter-rotating propellers (32,32), said pair of counter-rotating propellers (32,32) being arranged in such a way as to generate a rotational torque to rotate the pole (20).

A rotor blade, the rotor blade comprising a cavity and one or more nozzles for the expulsion of compressed air from the rotor blade cavity thereby resulting in rotation of the rotor blade. The rotor blade further comprises a pressure regulating arrangement, the pressure regulating arrangement being operable to release compressed air from the rotor blade cavity.

A rotor blade, the rotor blade comprising a cavity and one or more nozzles for the expulsion of compressed air from the rotor blade cavity thereby resulting in rotation of the rotor blade. The rotor blade further comprises a pressure regulating arrangement, the pressure regulating arrangement being operable to release compressed air from the rotor blade cavity.

An electric compound aircraft is disclosed with a capability of making vertical takeoff and landing and forward flight. In a specific embodiment, the compound aircraft includes an electric motor-powered tip-jet-driven rotary wing, an electric motor-powered tip-jet-driven propeller. The rotary wing provides lift for vertical takeoff and landing, hovering capability and during flight. The propeller provides thrust for forward flight. A fixed wing can be used, in addition to the rotary wing to provide lift for forward flight. Various electric control devices are used to provide control and stability for the compound aircraft and automation.

The present invention relates to a device for controlling the yaw of an aviation device, such as a helicopter, said aviation device comprising a bearing structure and a rotating member connected to the bearing structure to be mobile in rotation, around an axis of rotation, relative to said bearing structure, wherein the rotating member comprises fixing means for fixing at least one blade, the yaw control device comprising a rotor and a stator which form, in combination, an electrical machine, wherein the bearing structure is connected to the first of this stator and this rotor, and wherein the rotating member is connected to the second of this stator and this rotor, wherein the electrical machine is suitable for generating an electromotive force applied to the rotating member.

A method for equalizing rolling moments at high advance ratios is disclosed including impelling an aircraft in a forward direction at an airspeed by means of a thrust source and rotating a rotor of the aircraft at an angular velocity with respect to the airspeed effective to cause a positive total lift on each blade due to air flow over the blades in the retreating direction when the blade is moving in the retreating direction. The rotor includes an even number of blades placed at equal angular intervals around the rotor hub. One or both of cyclic pitch and rotor angle of attack are adjusted such that a rolling moment of the retreating blade due to reverse air flow is between 0.3 and 0.7 times a rolling moment on the advancing blade due to lift.

A method for equalizing rolling moments at high advance ratios is disclosed including impelling an aircraft in a forward direction at an airspeed by means of a thrust source and rotating a rotor of the aircraft at an angular velocity with respect to the airspeed effective to cause a positive total lift on each blade due to air flow over the blades in the retreating direction when the blade is moving in the retreating direction. The rotor includes an even number of blades placed at equal angular intervals around the rotor hub. One or both of cyclic pitch and rotor angle of attack are adjusted such that a rolling moment of the retreating blade due to reverse air flow is between 0.3 and 0.7 times a rolling moment on the advancing blade due to lift.