An example aircraft disclosed herein includes a wing, a spoiler rotatably coupled to the wing, the spoiler movable between a cruise position and an upward position and between the cruise position and a droop position, and a spoiler actuation system coupled to a hydraulic system of the aircraft, the spoiler actuation system including a first piston and a second piston, a rack coupled between the first piston and the second piston, the rack movable between a first position and a second position, a pinion coupled to the rack, the pinion to rotate between a third position and a fourth position when the rack moves between the first position and the second position, a first crank arm coupled to the pinion, the first crank arm to rotate with the pinion between the third position and the fourth position, and a second crank arm coupled to the first crank arm and to the spoiler, the second crank arm to move the spoiler between the cruise position and the upward position when the first crank arm rotates between the third position and the fourth position.

A kite comprises: a wing; upper and lower flaps located along at least a portion of an edge of the wing that forms the trailing edge of the wing when the wing is active; a controller configured to generate control signals; and an actuator arrangement configured to change orientations of the upper and lower flaps relative to the wing based on the control signals generated by the controller.

A kite comprises: a wing; upper and lower flaps located along at least a portion of an edge of the wing that forms the trailing edge of the wing when the wing is active; a controller configured to generate control signals; and an actuator arrangement configured to change orientations of the upper and lower flaps relative to the wing based on the control signals generated by the controller.

An aircraft spoiler mechanism includes a spoiler fore-section, a spoiler aft-section, and a reverse-motion linkage arm. The spoiler fore-section includes a forward end, a hinge end, an actuator coupling, and a pivot coupling to couple to a wing structure of an aircraft to enable rotation of the spoiler fore-section relative to the wing structure. The spoiler aft-section includes a hinge portion coupled to the hinge end of the spoiler fore-section and a crank-arm. The reverse-motion linkage arm includes a first end, a second end, and a pivot point coupled to the forward end of the spoiler fore-section. The spoiler mechanism also includes a first linkage to couple the first end of the reverse-motion linkage arm to the wing structure and a second linkage coupled to the second end of the reverse-motion linkage arm and to the crank-arm on the spoiler aft-section.

An aircraft spoiler mechanism includes a spoiler fore-section, a spoiler aft-section, and a reverse-motion linkage arm. The spoiler fore-section includes a forward end, a hinge end, an actuator coupling, and a pivot coupling to couple to a wing structure of an aircraft to enable rotation of the spoiler fore-section relative to the wing structure. The spoiler aft-section includes a hinge portion coupled to the hinge end of the spoiler fore-section and a crank-arm. The reverse-motion linkage arm includes a first end, a second end, and a pivot point coupled to the forward end of the spoiler fore-section. The spoiler mechanism also includes a first linkage to couple the first end of the reverse-motion linkage arm to the wing structure and a second linkage coupled to the second end of the reverse-motion linkage arm and to the crank-arm on the spoiler aft-section.

A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.

A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.

A flap support mechanism includes a carrier beam on which a flap is mounted. The carrier beam is rotatably mounted at a fixed rotational axis and has a pair of flanges, each flange having an aperture, and a channel extending aft from the pair of flanges. A fuse pin is received through the aperture in each flange. A coupler link is attached to an actuator at a first end and pivotally engaged to the carrier beam by the fuse pin. Extension of the coupler link by the actuator rotates the carrier beam from a stowed position to a deployed position. Responsive to a moment induced on the flap and carrier beam by a ground contact load, the fuse pin is frangible to shear releasing the coupler link to translate into the channel.

A flap support mechanism includes a carrier beam on which a flap is mounted. The carrier beam is rotatably mounted at a fixed rotational axis and has a pair of flanges, each flange having an aperture, and a channel extending aft from the pair of flanges. A fuse pin is received through the aperture in each flange. A coupler link is attached to an actuator at a first end and pivotally engaged to the carrier beam by the fuse pin. Extension of the coupler link by the actuator rotates the carrier beam from a stowed position to a deployed position. Responsive to a moment induced on the flap and carrier beam by a ground contact load, the fuse pin is frangible to shear releasing the coupler link to translate into the channel.

A slat control system for an aircraft may include a flight control computer configured to generate a gap command in response to an occurrence of a gap-command condition. The slat control system may further include an edge control system including an edge control device having a plurality of control device positions including at least one designated control device position. The slat control system may additionally include a device actuation system configured to move a leading edge device of an aircraft. The edge control system may be configured to automatically command the device actuation system to extend the leading edge device from a sealed position to a gapped position when the edge control device is in the designated control device position and the gap command is received by the edge control system.