A method and apparatus for controlling an airflow. The method draws air through a group of inlets. The group of inlets is located in a group of locations on the vehicle such that the group of inlets actively controls the airflow relative to an aircraft when drawing the air. The method compresses the air drawn by the group of inlets in a group of air compressor units located in an aircraft structure to form pressurized air. Further, the method sends the pressurized air through a group of exit ports in the aircraft structure. The pressurized air flowing out of the group of exit ports actively controls the airflow for an aircraft, enabling an improved performance of the aircraft.

The propulsion system for vessels comprises at least one suction sail (3), said at least one suction sail (3) comprising a suction system (10) and a transmission unit (8) to drive the rotation of said suction sail (3), wherein the suction sail (3) comprises at least two suction zones (7) arranged symmetrically on two sides of the suction sail (3), said suction zones (7) comprising variable suction means.

It provides a propulsion system for vessels that allows reducing their fuel consumption and polluting emissions by using an improved version of suction sails.

A system for suction of the boundary layer of a wing and protection against icing of this wing includes a wall including micro-perforations and delimiting a leading edge extended by a pressure-side wall and by a suction-side wall. The system also includes a perforated tube running along the leading edge, an exhaust duction for sucking air from this tube in order to suck the boundary layer successively via the micro-perforations of the wall and via the perforations of the tube, and a supply duct for blowing hot air into this perforated tube during a phase of protection against icing, this hot air being discharged successively via the perforations of the tube and via the micro-perforations of the wall.

An intentional fluid manipulation apparatus (IFMA) assembly with a first thrust apparatus that imparts a first induced velocity to a local free stream flow during a nominal operation requirement. The first thrust apparatus creates a streamtube. A second thrust apparatus is located in a downstream portion of the streamtube. The second thrust apparatus imparts a second induced velocity to the local free stream flow. The second induced velocity at the location of the second thrust apparatus has a component in a direction opposite to the direction of the first induced velocity at the location of the second thrust apparatus.

A rotorcraft is provided and includes a fuselage. The fuselage includes drag generating portions, a main rotor assembly and an auxiliary propulsor having an expected propulsion efficiency. The auxiliary propulsor is disposed to ingest boundary layer flows and in wake regions associated with the drag generating portions and is provided with a corresponding increase in the expected propulsion efficiency thereof.

A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air.

A method of providing ice protection on a surface of an aircraft using exhaust air from a laminar flow control compressor. An aircraft structure, for example a wing, includes a skin. The skin has an external surface, on an outer face of the skin. The skin has an internal surface, located opposite the external surface on an inner face of the skin. The aircraft structure includes a laminar flow control system including a compressor. The aircraft structure is so arranged that the exhaust air from the compressor is directed onto the internal surface of the skin of the aircraft structure, for example thus providing hot exhaust air which function as an ice protection system (whether by de-icing or anti-icing).

An aircraft inlet comprising an annular air intake structure defined by an inner surface and an outer surface, a plurality of perforations formed in the outer surface of the aircraft inlet, a plenum chamber situated within the aircraft inlet and configured to receive air entering the plurality of perforations, and/or a plurality of sensors disposed about the outer surface of the aircraft inlet, each sensor associated with a region of the plurality of perforations. Each sensor may comprise a hot film anemometer. The aircraft inlet may further comprise a regulator coupled at one end to the plenum chamber and at another end to a pump, wherein the regulator regulates a suction produced by the pump.

A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a fan rotatable about a central axis of the electric propulsion engine. The fan includes a fan shaft mechanically coupled to a power gearbox. The electric propulsion engine also includes an electric motor having a driveshaft, with the electric motor coupled to the power gearbox through the drive shaft. The electric motor rotates the fan through the power gearbox. The driveshaft includes a flexible element for accommodating a misalignment of the electric motor and the power gearbox.

A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a power gearbox mechanically coupled to an electric motor. The electric propulsion engine further includes a fan rotatable about a central axis of the electric propulsion engine by the electric motor through the power gearbox. Moreover, the electric propulsion engine includes an attachment assembly for mounting at least one of the electric motor or the power gearbox. The attachment assembly includes a torsional damper for accommodating a torsional vibration of the electric motor or the power gearbox.