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.

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.

Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.

A wing system (2) for an aircraft includes a movable flow body (6) and a cover panel (8), wherein the flow body (6) and the cover panel (8) both are movably supported on a main wing body (4). While the flow body (6) is actively driven into upwards or downwards deflected positions, the cover panel (8) is coupled with the flow body (6) to follow its motion. The cover panel covers a part of the flow body (6) and the main wing body (4) in order to provide a substantially continuous, closed outer contour.

A drive apparatus for differentially actuating a plurality of high-lift surfaces of an aircraft may include a common rotary and a plurality of clutches incorporated into the common driveline. The plurality of clutches may include a first clutch provided between a first outboard driveline section and a central driveline section of the common driveline, and a second clutch provided between a second outboard driveline section and the central driveline section of the common driveline. A first and second power drive unit (PDU) may be arranged remote from a fuselage of the aircraft and mechanically coupled to the common driveline at a drive connection disposed in a region of the first clutch and the second clutch, respectively. The first clutch and the second clutch may mechanically connect and disconnect the first and second outboard driveline section from the central driveline section, respectively.

A drive apparatus for differentially actuating a plurality of high-lift surfaces of an aircraft may include a common rotary and a plurality of clutches incorporated into the common driveline. The plurality of clutches may include a first clutch provided between a first outboard driveline section and a central driveline section of the common driveline, and a second clutch provided between a second outboard driveline section and the central driveline section of the common driveline. A first and second power drive unit (PDU) may be arranged remote from a fuselage of the aircraft and mechanically coupled to the common driveline at a drive connection disposed in a region of the first clutch and the second clutch, respectively. The first clutch and the second clutch may mechanically connect and disconnect the first and second outboard driveline section from the central driveline section, respectively.

An airfoil assembly comprising an airplane wing, a spoiler, and a flap for unmanned and high endurance aircraft. The spoiler is located on an upper surface of the airplane wing while the flap is located on a lower surface of the airplane wing. The spoiler and the flap can occupy at least one-third, and up to three-quarters, the chord span of the airplane wing. The spoiler and the flap are both capable of moving upwards and downwards with respect to the airplane wing through their respective frames.

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 camber adjustment system for a wing of an aircraft includes a droop panel that is configured to moveably couple to a portion of the wing, a flap, a cam rod moveably coupled to the droop panel, a bell crank cam arm moveably coupled to the flap, and a jackscrew interface between the cam rod and the bell crank cam arm. The droop panel is configured to move in response to movement of the flap via the jackscrew interface.

A flap and spoiler system of an aircraft wing including a spoiler having a spoiler leading edge and a spoiler trailing edge. The flap and spoiler system also includes a flap having a flap leading edge and a flap trailing edge, an axis of rotation through the flap, and a top surface portion above the axis of rotation. The top surface portion has a first semi-circular shape such that, when the flap rotates about the axis of rotation, the spoiler trailing edge remains substantially stationary. When the spoiler trailing edge remains substantially stationary the spoiler is not driven by a spoiler drive.