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.

Aspects relate to aircraft and methods of use for aerodynamic control with winglet surfaces. In an aspect an exemplary aircraft includes a first wing having a first winglet at a distal end of the wing, wherein the first winglet comprises at least a first control surface at a first trailing edge of the first winglet and a second wing having a second winglet at a distal end of the wing, wherein the second winglet comprises at least a second control surface at a second trailing edge of the second winglet.

Aspects relate to aircraft and methods of use for aerodynamic control with winglet surfaces. In an aspect an exemplary aircraft includes a first wing having a first winglet at a distal end of the wing, wherein the first winglet comprises at least a first control surface at a first trailing edge of the first winglet and a second wing having a second winglet at a distal end of the wing, wherein the second winglet comprises at least a second control surface at a second trailing edge of the second winglet.

A secondary flight control system is provided. The secondary flight control system comprising: a first flight control surface system; a second flight control surface system; and a power distribution unit operably connected to the first flight control surface system and the second flight control surface system, wherein the power distribution unit is configured to generate torque to actuate the first flight control surface system and the second flight control surface system.

A system for mechanical operation of an aircraft wing includes a torque tube rotatable at a first rate of rotation to cause a downward rotation of a control surface relative to the aircraft wing. A gearing assembly including an output shaft is coupled to the torque tube. The torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation less than the first rate of rotation. A rotational member is coupled to the output shaft, and the output shaft is configured to drive a rotation of the rotational member. A first end of a linear actuator is coupled to the rotational member at a forward attach point, which is eccentric to a rotational center of the rotational member. The rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing.

A system for mechanical operation of an aircraft wing includes a torque tube rotatable at a first rate of rotation to cause a downward rotation of a control surface relative to the aircraft wing. A gearing assembly including an output shaft is coupled to the torque tube. The torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation less than the first rate of rotation. A rotational member is coupled to the output shaft, and the output shaft is configured to drive a rotation of the rotational member. A first end of a linear actuator is coupled to the rotational member at a forward attach point, which is eccentric to a rotational center of the rotational member. The rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing.

Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.

Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.

A control surface assembly for an unmanned aerial vehicle (UAV) is disclosed. The control surface assembly has a fin configured to be rotatably coupled to a fuselage of the UAV, with a control surface member rotatably coupled to the fin. A control surface linkage is configured to be coupled between the control surface member and an actuator disposed in the fuselage. The fin is rotatable with respect to the fuselage between a stowed configuration and a deployed configuration. In the deployed configuration, the control surface linkage is configured to rotate the control surface member with respect to the fin, when the actuator actuates the control surface linkage. In the stowed configuration, however, the control surface linkage is configured to move with respect to the fin without rotating the control surface member, when the actuator actuates the control surface linkage.

A wing assembly for an aircraft is disclosed having a wing and a wing tip device at the tip of the wing, wherein the wing tip device is moveable between a flight configuration and a ground configuration. The wing has a spar extension which extends spanwise away from a distal end of the wing, the spar extension having a first end portion fixed in the wing and a second end portion which, in the flight configuration, is disposed in the wing tip device such that, in the flight configuration, the spar extension transmits flight loads between the wing tip device and flight-load bearing structure in the wing. The wing assembly may have an actuation assembly to move the wing tip device.