A control augmentation system for high aspect ratio aircraft has aileron/flaperon and throttle position sensors; spoiler and flap controls; a mode switch with manual, and landing modes; and a controller driving left and right spoiler and flap servos, the controller including at least one processor with memory containing firmware configured to: when the mode switch is in manual mode, drive both spoiler servos to a symmetrical position according to the spoiler control; when the mode switch is in landing mode, drive the left spoiler to a position dependent on aileron and throttle position, and the right spoiler to a position dependent on aileron and throttle position, the left and right spoiler positions differing whenever ailerons are not centered, and an average of spoiler positions is more fully deployed when the throttle position is at a low-power setting than when the throttle position is at a high-power setting.

An aircraft wing including a wingbox with an upper cover, a lower cover, a forward spar and a rear spar. A leading edge of a trailing edge panel is attached to the wingbox. A support structure is attached to the wingbox. A kinked link includes a first arm, a second arm, and a corner where the first and second arms meet. The first arm of the kinked link is pivotally attached to the trailing edge panel at a first pivot joint, and the second arm of the kinked link is pivotally attached to the support structure at a second pivot joint.

Flexible control surfaces and related methods are disclosed. Example apparatus disclosed herein include an airfoil including a skin, the skin having perforations filled with an elastomer to increase a flexibility of the skin; and a flexible core adjacent the perforations of the skin to support the skin.

A composite trailing edge control surface includes a contiguous one-piece composite control surface skin wrapped around a plurality of stiffening cores, a plurality of hinge fittings, and a plurality of substantially parallel ribs. The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin on a substantially flat tool. A plurality of stiffener cores having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin that is trimmed and has fastener apertures and hinge fitting access apertures provided there-through.

A composite trailing edge control surface includes a contiguous one-piece composite control surface skin wrapped around a plurality of stiffening cores, a plurality of hinge fittings, and a plurality of substantially parallel ribs. The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin on a substantially flat tool. A plurality of stiffener cores having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin that is trimmed and has fastener apertures and hinge fitting access apertures provided there-through.

A hydraulic actuator is adapted to drive a spoiler of a wing having a flap. When the hydraulic actuator drives the spoiler in an overlapping region where a driving range of the flap and a driving range of the spoiler overlap, an output suppressing structure suppress a drive output of the hydraulic actuator in the overlapping region to be less than that in a non-overlapping region other than the overlapping region.

The present disclosure is generally directed to a composite trailing edge control surface including a contiguous one-piece composite control surface skin wrapped around a plurality of stiffening cores, a plurality of hinge fittings, and a plurality of substantially parallel ribs. The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin on a substantially flat tool. A plurality of stiffener cores having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin that is trimmed and has fastener apertures and hinge fitting access apertures provided there-through.

The present disclosure is generally directed to a composite trailing edge control surface including a contiguous one-piece composite control surface skin wrapped around a plurality of stiffening cores, a plurality of hinge fittings, and a plurality of substantially parallel ribs. The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin on a substantially flat tool. A plurality of stiffener cores having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin that is trimmed and has fastener apertures and hinge fitting access apertures provided there-through.

An air brake system for aircraft comprising control surfaces, such as slats, flaps and spoilers mounted to the wings of an aircraft, wherein each control surface is split, along a spanwise direction, into parts of the control surface, and the parts of each control surface are deployed desynchronously when the aircraft touches down.

An air brake system for aircraft comprising control surfaces, such as slats, flaps and spoilers mounted to the wings of an aircraft, wherein each control surface is split, along a spanwise direction, into parts of the control surface, and the parts of each control surface are deployed desynchronously when the aircraft touches down.