A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, wherein the rear section extends between the front section and the aft region, the rotary wing aircraft comprising: a propeller that is rotatably mounted at the rear section in the aft region, a main rotor that is rotatably mounted at the front section, and a source of asymmetry that is connected to the front section such that the front section comprises at least in sections an asymmetrical cross-sectional profile in direction of the associated roll axis, wherein the source of asymmetry is configured to generate sideward thrust for main rotor anti-torque from main rotor downwash.

A method for controlling a hybrid helicopter having at least one lifting rotor, at least one forward-movement propeller and an empennage provided with at least one moveable empennage surface. The method includes the following steps: using a main sensor to determine a current value of a rotor parameter conditioning a current power drawn by the lifting rotor, using an estimator to determine a current setpoint of the rotor parameter, adjusting a position of the moveable empennage surface using a deflection controller as a function of the current value and of current setpoint.

A method for controlling a hybrid helicopter having at least one lifting rotor, at least one forward-movement propeller and an empennage provided with at least one moveable empennage surface. The method includes the following steps: using a main sensor to determine a current value of a rotor parameter conditioning a current power drawn by the lifting rotor, using an estimator to determine a current setpoint of the rotor parameter, adjusting a position of the moveable empennage surface using a deflection controller as a function of the current value and of current setpoint.

A control device controls an electric drive system mounted on an electric vertical takeoff and landing aircraft with a rotor, and including a drive motor that turns the rotor. The control device controls the electric drive system to operate selectively in any one operation mode of at least two operation modes: a normal mode and a functional test mode. In the normal mode, the control device controls the drive motor in accordance with a command from a body control device that controls the flight of the electric vertical takeoff and landing aircraft. In the functional test mode, the control device controls the drive motor in accordance with a command sent from outside according to a functional test program, or in accordance with the functional test program preset in the control device.

The invention relates to an aircraft with a longitudinal central axis, comprising: a fuselage structure (2) which is designed to accommodate persons and/or payload; a wing structure (3) which has at least two wing halves (3.1) which are attached to the fuselage structure (2) and which have a fuselage-side main region (H) and a tip region (S); at least one forward propulsion unit (4) which is designed to generate a forward force, acting in the direction of the central axis, on the aircraft; at least four lifting propulsion units (5) which are designed to generate a lift force, acting in the direction of the central axis, on the aircraft.

The invention relates to an aircraft with a longitudinal central axis, comprising: a fuselage structure (2) which is designed to accommodate persons and/or payload; a wing structure (3) which has at least two wing halves (3.1) which are attached to the fuselage structure (2) and which have a fuselage-side main region (H) and a tip region (S); at least one forward propulsion unit (4) which is designed to generate a forward force, acting in the direction of the central axis, on the aircraft; at least four lifting propulsion units (5) which are designed to generate a lift force, acting in the direction of the central axis, on the aircraft.

A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.

A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.

Embodiments are directed to boosting aircraft engine performance for takeoff and critical mission segments by reducing airflow used for cooling exhaust gases. The airflow is reduced by stopping an accessory blower or by closing an external air vent Eliminating the cooling airflow to the exhaust has the effect of lowering the backpressure on the engine, which thereby increases maximum engine power.

Rotorcraft including a fuselage, at least three rotor system arms, a forward propulsion unit for providing forward propulsion to the rotorcraft and a flight control system. Each rotor system arm has a rotor system including a mast having at least two rotor blades and an electric rotor motor coupled to the mast for driving the mast whereupon the rotor blades act as a rotating rotor disc. Each rotor system has an individually controllable collective rotor blade pitch. At least one rotor system has a controllable cyclic rotor blade pitch. The flight control system controls the at least three electric rotor motors, the collective rotor blade pitch of each rotor system, the cyclic rotor blade pitch of the at least one rotor system and the forward propulsion unit in response to an input control indicating a desired maneuver to operate the rotorcraft for takeoff, flight and landing.