A nozzle for use with a rotor blade for a reaction drive type helicopter includes a first wall, a second wall opposing the first wall, and sidewalls extending between the first wall and the second wall enclosing a cavity having an upstream end and a downstream end. The nozzle includes an inlet section for receiving a gasflow at the upstream end. The distance between the first wall and the second wall reduces to a throat downstream of the inlet section. An expansion section extending from the throat, downstream thereof.

A device for controlling a collective pitch and a cyclic pitch of rotor blades of a rotoreraft of a direct turbine driven type and. contra-rotating coaxial rotor type (DTDR) includes: a lower rotor and an upper rotor that are mounted concentrically on a shared rotor shaft; a first plate, that is not rotatable, fastened to a structure of the rotorcraft and connected to an actuator that communicates collective pitch and cyclic pitch controls to it, the first plate being mounted so as to be movable in translation along the shared rotor shaft and to oscillate relative to the shared rotor shaft, via a lower ball joint mechanism; and a second plate, that is rotatable, housed on the lower bail joint mechanism so as to be always parallel to the first plate, the second plate being driven in rotation by a member connecting it to the lower rotor.

A device for controlling a collective pitch and a cyclic pitch of rotor blades of a rotoreraft of a direct turbine driven type and. contra-rotating coaxial rotor type (DTDR) includes: a lower rotor and an upper rotor that are mounted concentrically on a shared rotor shaft; a first plate, that is not rotatable, fastened to a structure of the rotorcraft and connected to an actuator that communicates collective pitch and cyclic pitch controls to it, the first plate being mounted so as to be movable in translation along the shared rotor shaft and to oscillate relative to the shared rotor shaft, via a lower ball joint mechanism; and a second plate, that is rotatable, housed on the lower bail joint mechanism so as to be always parallel to the first plate, the second plate being driven in rotation by a member connecting it to the lower rotor.

An unmanned aircraft system has a vertical takeoff and landing flight mode and a forward flight mode. The unmanned aircraft system includes an airframe, a rotor assembly rotatably coupled to the airframe and a propeller rotatably coupled to the airframe. The rotor assembly including at least two rotor blades having tip jets that are operably associated with a compressed gas power system. The propeller is operably associated with an electric power system. In the vertical takeoff and landing flight mode, compressed gas from the compressed gas power system is discharged through the tip jets to rotate the rotor assembly and generate vertical lift. In the forward flight mode, the electric power system drives the propeller to generate forward thrust and autorotation of the rotor assembly generates vertical lift.

An unmanned aircraft system has a vertical takeoff and landing flight mode and a forward flight mode. The unmanned aircraft system includes an airframe, a rotor assembly rotatably coupled to the airframe and a propeller rotatably coupled to the airframe. The rotor assembly including at least two rotor blades having tip jets that are operably associated with a compressed gas power system. The propeller is operably associated with an electric power system. In the vertical takeoff and landing flight mode, compressed gas from the compressed gas power system is discharged through the tip jets to rotate the rotor assembly and generate vertical lift. In the forward flight mode, the electric power system drives the propeller to generate forward thrust and autorotation of the rotor assembly generates vertical lift.

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.

An aircraft's two wings and joined thruster propellers or turbines serve as rotary wings in helicopter mode and as fixed wings in airplane mode. The thrusters along the wingspans or at the wing tips drive both rotary wing rotation and airplane flight. Large-angle controlled feathering about the pitch change axes of the left and right wings and thrusters allows them to rotate, relative to each other, between facing and thrusting forward in the same direction for airplane flight or facing and thrusting oppositely for helicopter flight. Optional controls include: helicopter cyclic and collective pitch; airplane roll by differential wing pitch; yaw by differential prop thrust; fuselage pitch by wing pitch change and prop thrust change interacting with an underslung craft e.g.; and fuselage yaw control independent of rotor rotation via a powered rotary mast coupling or a tail responsive to rotor downwash. A teetering rotor hub is a further option.

An aircraft's two wings and joined thruster propellers or turbines serve as rotary wings in helicopter mode and as fixed wings in airplane mode. The thrusters along the wingspans or at the wing tips drive both rotary wing rotation and airplane flight. Large-angle controlled feathering about the pitch change axes of the left and right wings and thrusters allows them to rotate, relative to each other, between facing and thrusting forward in the same direction for airplane flight or facing and thrusting oppositely for helicopter flight. Optional controls include: helicopter cyclic and collective pitch; airplane roll by differential wing pitch; yaw by differential prop thrust; fuselage pitch by wing pitch change and prop thrust change interacting with an underslung craft e.g.; and fuselage yaw control independent of rotor rotation via a powered rotary mast coupling or a tail responsive to rotor downwash. A teetering rotor hub is a further option.

This invention is about a rotorcraft that possesses a configuration made up of the join of three technologies Know separately as Jet Tip, Circulation Control and Advancing Blade Concept. These three technologies synergizes of unusual form allowing the embodiment of a rotorcraft with advantages qualitative and quantitative in fields as flight characteristics, manufacturing, maintenance, security in flight and operational costs.

This invention is about a rotorcraft that possesses a configuration made up of the join of three technologies Know separately as Jet Tip, Circulation Control and Advancing Blade Concept. These three technologies synergizes of unusual form allowing the embodiment of a rotorcraft with advantages qualitative and quantitative in fields as flight characteristics, manufacturing, maintenance, security in flight and operational costs.