Abstract: 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.

Abstract: A process and a machine for reducing a profile of a flap system including forming a track housing within a flap system including: a foil and a track housing within the foil, two track housing lugs extending out from an opening therein and beyond a leading edge of the foil, and a track that has a curved shape configured to: support the foil; and guide a movement of the foil along the track. The flap system may include an anchor plate and an actuator configured to connect to the foil, and a pylon that includes: a length and a depth enclosing a section of a dual channel portion of the track extending out an exit hole of the track housing in the foil. The process may continue by attaching the anchor plate and the pylon to a wing, and the actuator to the anchor plate.

Abstract: Underwing-mounted trailing edge bifold flaps for wings of aircraft are disclosed. A bifold flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The bifold flap includes a forward panel and an aft panel. The aft panel is pivotally coupled to the forward panel and foldable relative thereto. The aft panel is folded toward the forward panel when the bifold flap is in the stowed position. The aft panel is unfolded from the forward panel when the bifold flap is in the deployed position. A bullnose pivotally coupled to the forward panel pivots relative to the bifold flap as the bifold flap moves between the stowed and deployed positions.

Abstract: The illustrative examples provide a slat movement system for use in an aircraft. An aircraft comprises a wing having a fixed edge and a wing front spar, and a moveable slat connected to the wing by a four bar linkage and a slat arm, the slat arm movable along a track comprising a slot terminating prior to the wing front spar.

Abstract: The illustrative examples provide a slat movement system for use in an aircraft. An aircraft comprises a wing having a fixed edge and a wing front spar, and a moveable slat connected to the wing by a four bar linkage and a slat arm, the slat arm movable along a track comprising a slot terminating prior to the wing front spar.

Abstract: Underwing-mounted trailing edge flaps for wings of aircraft are disclosed. A flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The flap includes a first edge, a second edge located opposite the first edge, a first surface extending between the first edge and the second edge, and a second surface located opposite the first surface and extending between the first edge and the second edge. The first edge is located rearward of the second edge when the flap is in the stowed position, and forward of the second edge when the flap is in the deployed position. A bullnose pivotally coupled to the flap at a location along the first edge pivots relative to the flap as the flap moves between the stowed and deployed positions.

Abstract: A process and a machine for reducing a profile of a flap system including forming a track housing within a flap system including: a foil and a track housing within the foil, two track housing lugs extending out from an opening therein and beyond a leading edge of the foil, and a track that has a curved shape configured to: support the foil; and guide a movement of the foil along the track. The flap system may include an anchor plate and an actuator configured to connect to the foil, and a pylon that includes: a length and a depth enclosing a section of a dual channel portion of the track extending out an exit hole of the track housing in the foil. The process may continue by attaching the anchor plate and the pylon to a wing, and the actuator to the anchor plate.

Abstract: Underwing-mounted trailing edge bifold flaps for wings of aircraft are disclosed. A bifold flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The bifold flap includes a forward panel and an aft panel. The aft panel is pivotally coupled to the forward panel and foldable relative thereto. The aft panel is folded toward the forward panel when the bifold flap is in the stowed position. The aft panel is unfolded from the forward panel when the bifold flap is in the deployed position. A bullnose pivotally coupled to the forward panel pivots relative to the bifold flap as the bifold flap moves between the stowed and deployed positions.

Abstract: Underwing-mounted trailing edge flaps for wings of aircraft are disclosed. A flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The flap includes a first edge, a second edge located opposite the first edge, a first surface extending between the first edge and the second edge, and a second surface located opposite the first surface and extending between the first edge and the second edge. The first edge is located rearward of the second edge when the flap is in the stowed position, and forward of the second edge when the flap is in the deployed position. A bullnose pivotally coupled to the flap at a location along the first edge pivots relative to the flap as the flap moves between the stowed and deployed positions.

Abstract: Wing assemblies comprise a three-position Krueger flap and an actuation assembly that comprises a drive linkage assembly, a primary linkage assembly coupled between the drive linkage assembly and the three-position Krueger flap, and a secondary linkage assembly. The primary linkage assembly comprises a dual linkage that is pivotally and translationally coupled relative to a wing support structure. The secondary linkage assembly comprises a cam, a follower, and a dual-linkage axle that is coupled to the follower and to the dual linkage and that defines a dual-linkage pivot axis of the dual linkage.

Abstract: Actuated assemblies comprise a base object, an actuated object, a rotary actuator, and a joint. The rotary actuator is configured to selectively pivot the actuated object relative to the base object. The rotary actuator comprises a housing that is operatively coupled to the base object, and an output gear that is configured to be selectively rotated relative to the housing. The joint comprises a crowned spline and a joint spherical bearing. The crowned spline is meshed with the output gear of the rotary actuator and is fixed relative to the actuated object. The joint spherical bearing comprises an outer race that is fixed relative to the base object, and an inner race that is positioned for rotational and pivotal movement within the outer race and that is fixed relative to the crowned spline.

Abstract: Methods comprise flying an aircraft at cruise which results in an aerodynamic lift force on a flight control surface of the aircraft that urges the flight control surface away from a stowed position. Concurrently with the flying, the methods include counteracting the aerodynamic lift force with a magnetic force that urges the flight control surface towards the stowed position and that results in the flight control surface being maintained in the stowed position during the flying. Flight control systems comprise a flight control surface and an adjacent structure. The flight control surface or the adjacent structure comprises a magnet and the other of the flight control surface or the adjacent structure comprises a ferromagnetic structure. A magnetic force urges the flight control surface toward a stowed position.

Abstract: Methods comprise flying an aircraft at cruise which results in an aerodynamic lift force on a flight control surface of the aircraft that urges the flight control surface away from a stowed position. Concurrently with the flying, the methods include counteracting the aerodynamic lift force with a magnetic force that urges the flight control surface towards the stowed position and that results in the flight control surface being maintained in the stowed position during the flying. Flight control systems comprise a flight control surface and an adjacent structure. The flight control surface or the adjacent structure comprises a magnet and the other of the flight control surface or the adjacent structure comprises a ferromagnetic structure. A magnetic force urges the flight control surface toward a stowed position.

Abstract: Wing assemblies (100) comprise an inboard flight control surface (102), an outboard flight control surface (104) positioned directly adjacent to and outboard of the inboard flight control surface (102), and a dual actuation assembly (106) coupled directly to and forming a linkage between the inboard flight control surface (102) and the outboard flight control surface (104). The dual actuation assembly (106) is configured to selectively transition the inboard flight control surface (102) and the outboard flight control surface (104), in tandem, amongst a retracted configuration (108) and a range of extended configurations (110).

Abstract: Wing assemblies comprise a three-position Krueger flap and an actuation assembly that comprises a drive linkage assembly, a primary linkage assembly coupled between the drive linkage assembly and the three-position Krueger flap, and a secondary linkage assembly. The primary linkage assembly comprises a dual linkage that is pivotally and translationally coupled relative to a wing support structure. The secondary linkage assembly comprises a cam, a follower, and a dual-linkage axle that is coupled to the follower and to the dual linkage and that defines a dual-linkage pivot axis of the dual linkage.

Abstract: Wing assemblies (100) comprise an inboard flight control surface (102), an outboard flight control surface (104) positioned directly adjacent to and outboard of the inboard flight control surface (102), and a dual actuation assembly (106) coupled directly to and forming a linkage between the inboard flight control surface (102) and the outboard flight control surface (104). The dual actuation assembly (106) is configured to selectively transition the inboard flight control surface (102) and the outboard flight control surface (104), in tandem, amongst a retracted configuration (108) and a range of extended configurations (110).

Abstract: 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.

Abstract: Actuated assemblies comprise a base object, an actuated object, a rotary actuator, and a joint. The rotary actuator is configured to selectively pivot the actuated object relative to the base object. The rotary actuator comprises a housing that is operatively coupled to the base object, and an output gear that is configured to be selectively rotated relative to the housing. The joint comprises a crowned spline and a joint spherical bearing. The crowned spline is meshed with the output gear of the rotary actuator and is fixed relative to the actuated object. The joint spherical bearing comprises an outer race that is fixed relative to the base object, and an inner race that is positioned for rotational and pivotal movement within the outer race and that is fixed relative to the crowned spline.

Abstract: An actuation apparatus for an aerodynamic surface includes a cam track plate having a forward cam track and an aft cam track, a support arm coupled to the leading edge slat panel, the support arm having a forward roller and an aft roller thereon, the forward roller disposed in the forward cam track and the aft roller disposed in the aft cam track, and a bell crank pivotally mounted to the cam track plate, the bell crank having an aft end coupled by an aft link to the wing structure and a forward end coupled by a forward link to the support arm. The forward roller translates within the forward cam track and the aft roller translates within the aft cam track to cause downward rotation of the aerodynamic surface and increased camber of the aerodynamic surface as the aerodynamic surface is extended toward a deployed position.

Abstract: A wing spoiler actuator mechanism includes an upper spoiler having a free end and a hinge end pivotally coupled to a wing structure at a first fixed axis, a door pivotally coupled to the wing structure at a second axis, and an actuator pivotally mounted to the wing structure between the upper spoiler and the door, the actuator having an extendable first end coupled to the upper spoiler and an opposite second end. Extension of the first end of the actuator rotates the upper spoiler to a deployed position and rotates the actuator such that the second end of the actuator induces downward rotation of the door from a closed position to an open position and the second end of the actuator extends below the wing structure during spoiler deployment.