Flaperon actuation systems for aircraft are disclosed herein. An example aircraft includes a wing including, a fixed wing portion, a flaperon, and an actuation system. The actuation system includes a first actuator coupled to the fixed wing portion. The first actuator is operable to move the flaperon along a first degree of freedom between a stowed position in which the flaperon is aligned with the fixed wing portion and a deployed position in which the flaperon is moved downward relative to the fixed wing portion. The actuation system also includes a linkage assembly coupled between the fixed wing portion and the flaperon. The linkage assembly includes a second actuator operable to move the flaperon along a second degree of freedom to pitch the flaperon between an upward position and a downward position.

Systems and methods are described herein to implement transverse momentum injection at low frequencies to directly modify large-scale eddies in a turbulent boundary layer on a surface of an object. A set of transverse momentum injection actuators may be positioned on the surface of the object to affect large-scale eddies in the turbulent boundary layer. The system may include a controller to selectively actuate the transverse momentum injection actuators with an actuation pattern to affect the large-scale eddies to modify the drag of the fluid flow on the surface. In various embodiments, the transverse momentum injection actuators may be operated at frequencies less than 10,000 Hertz.

A flight control surface with an actuator with an aerodynamic fairing for a swept aircraft wing. The swept aircraft wing includes a movable flight control surface with a hinge line non-perpendicular to the line of flight of the aircraft, and an actuator arm configured to actuate the flight control surface. The actuator arm includes a longitudinal axis substantially aligned with the line of flight, the actuator arm extending at least partially from an outer surface of the aircraft wing, and a fairing arranged on the outer surface of the aircraft wing to at least partially cover the actuator arm. Aligning the actuator arm with the line of flight of the aircraft may allow for an improved fairing to be provided.

A flight control surface with an actuator with an aerodynamic fairing for a swept aircraft wing. The swept aircraft wing includes a movable flight control surface with a hinge line non-perpendicular to the line of flight of the aircraft, and an actuator arm configured to actuate the flight control surface. The actuator arm includes a longitudinal axis substantially aligned with the line of flight, the actuator arm extending at least partially from an outer surface of the aircraft wing, and a fairing arranged on the outer surface of the aircraft wing to at least partially cover the actuator arm. Aligning the actuator arm with the line of flight of the aircraft may allow for an improved fairing to be provided.

A morphing wing includes a pantograph mechanism capable of being extended and contracted in a predetermined direction, a plurality of flight feathers attached to the pantograph mechanism, connection members configured to connect flight feathers adjacent to each other among the plurality of flight feathers, a first rotating mechanism configured to rotate the pantograph mechanism around one axis of a plane that intersects the direction, and a second rotating mechanism configured to rotate the pantograph mechanism around another axis of the plane. Each of the plurality of flight feathers is configured so that an angle formed by adjacent flight feathers connected via the connection members increases as the pantograph mechanism extends.

A morphing wing includes a pantograph mechanism capable of being extended and contracted in a predetermined direction, a plurality of flight feathers attached to the pantograph mechanism, connection members configured to connect flight feathers adjacent to each other among the plurality of flight feathers, a first rotating mechanism configured to rotate the pantograph mechanism around one axis of a plane that intersects the direction, and a second rotating mechanism configured to rotate the pantograph mechanism around another axis of the plane. Each of the plurality of flight feathers is configured so that an angle formed by adjacent flight feathers connected via the connection members increases as the pantograph mechanism extends.

Linkage assemblies for aircraft wing hinged panels are described herein. An example linkage assembly includes a flap follower arm coupled between a spoiler support beam and a flap, a rocker, a panel link coupled between the hinged panel and the rocker, and a cross-bar link coupled between the flap follower arm and the rocker. The flap follower arm, the rocker, the panel link, and the cross-bar link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other.

Linkage assemblies for aircraft wing hinged panels are described herein. An example linkage assembly includes a flap follower arm coupled between a spoiler support beam and a flap, a rocker, a panel link coupled between the hinged panel and the rocker, and a cross-bar link coupled between the flap follower arm and the rocker. The flap follower arm, the rocker, the panel link, and the cross-bar link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other.

Technologies for providing blended wing body aircraft control surfaces are described herein. In some examples, one or more of the control surfaces have angular configurations that reduce the formation of air vortexes when in upward or downward configurations, thereby reducing the drag on the aircraft when the control surfaces are being used.

A movable flow body device for an aircraft including an elongated flow body having a main extension axis, a first mechanical interface in a first position along the main extension axis, a second mechanical interface in a second position and a third mechanical interface in a third position. The first mechanical interface may be a master interface arranged in a central region, while the second and third mechanical interfaces are slave interfaces. Preferably, in the outboard position, a link plate between a support lever and a support rib of the flow body is inverted compared to the further inboard mechanical interface, which allows for supporting slimmer and longer flow bodies in the outboard region and providing a rigging hinge line through the whole flow body.