An apparatus, method and system for combining aerodynamic design with engine power to increase synergy between the two and increase climb performance, engine-out performance, and fuel efficiency for a variety of aircraft or the like.

The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.

An aerodynamic body for use on an aircraft including at least a first perforated surface portion (25) and an ice-protection system (31). The first perforated surface portion (25) has perforations. The ice-protection system (31) includes an actuatable element (33) and the actuatable element (33) is movable or deformable between a first position and a second position. In the first position, the actuatable element (33) is thermally coupled to the first perforated surface portion (25) and configured to prevent an inflow or outflow between a boundary layer of an outer aerodynamic airflow and the aerodynamic body through at least one of the perforations. In the second position, the actuatable element (33) is distanced from the first perforated surface portion (25) and configured to allow an inflow from a boundary layer of an outer aerodynamic airflow through at least one of the perforations into the aerodynamic body.

Variable-porosity panel systems and associated methods. A variable-porosity panel system includes a panel assembly with an exterior layer defining a plurality of exterior layer pores and a sliding layer adjacent to the exterior layer and defining a plurality of sliding layer pores. The variable-porosity panel system additionally includes a shape memory alloy (SMA) actuator configured to translate the sliding layer relative to the exterior layer to modulate a porosity of the panel assembly. The SMA actuator includes an SMA element configured to exert an actuation force on the sliding layer and at least partially received within an SMA element receiver of the sliding layer. The SMA element extends out of the sliding layer only at a sliding layer first end. A method of operating the variable-porosity panel system includes assembling the variable-porosity panel system and/or transitioning the panel assembly of the variable-porosity panel system among the plurality of panel configurations.

The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.

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.

A system for passive deployment of a vortex generator is disclosed, including a housing mounted at a fixed location relative to an airfoil structure and a piston contained in the housing. A vortex generator is moveably mounted adjacent an exterior surface of the airfoil structure, and is moveable between a stowed position inside the airfoil structure and a deployed position outside the airfoil structure. The piston is configured to drive the vortex generator between the stowed position and the deployed position in response to a pressure differential between a first airstream over a first surface of the airfoil structure and a second airstream over a second surface of the airfoil structure.

Variably porous panels and panel assemblies incorporating shape memory alloy components along with methods for actuating the shape memory alloys are disclosed to predictably alter the porosity of a substrate surface, with the shape memory alloy maintained in an orientation relative to the panel that is in-plane with a mold-line of the panel outer surface.

A leading edge structure (11) for a flow control system of an aircraft (1) including a leading edge panel (13) surrounding surrounds a plenum (17) which extends in a span direction (19), wherein the leading edge panel (13) has a first side portion (21) extending from a leading edge point (23) to a first attachment end (25), wherein the leading edge panel (13) has a second side portion (27) opposite the first side portion (21), extending from the leading edge point (23) to a second attachment end (29), wherein the leading edge panel (13) comprises an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), and wherein the leading edge panel (13) comprises a plurality of micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39).

Apparatus for laminar flow control for a skin panel for an aircraft including a body for receipt into a recess of the skin panel. The body defines a chamber. The body includes an outer portion defining one or more micro apertures through the outer portion, each of the one or more micro apertures being in fluid communication with the chamber. The body includes a support portion supporting the outer portion, the support portion defining at least one outlet for allowing air to be drawn from the chamber in use by a suction means in fluid communication with the outlet in use. The apparatus is arranged such that, in use, air is drawn through the one or more micro apertures into the chamber and out of the outlet, thereby to promote laminar airflow over the outer portion in use.