Abstract: A wing (3) for an aircraft (1) including a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5). The trailing edge high lift assembly (9) includes a flap (11) and a connection assembly (13) movably mounting the flap (11) to the main wing (5). The connection assembly (13) includes an actuator unit (35) moving the flap (11) between a retracted position and at least one extended position. The flap (11) includes a leading edge part (23) and a trailing edge part (27) mounted to the leading edge part (23) pivotable about a pivot axis (31).

Abstract: An apparatus for shortening a wingspan of an aircraft is disclosed. The apparatus comprises a first bracket and a second bracket extending from a wingtip of the aircraft, and a motor coupled to a fixed wing of the aircraft. A first outboard link is rotatably coupled to the first bracket and to the motor, and a second outboard link is rotatably coupled to the second bracket and to the motor. A first inboard link is rotatably coupled to the first bracket and to the fixed wing, and a second inboard link is rotatably coupled to the second bracket and to the fixed wing. The motor is configured to rotate the first outboard link and the second outboard link to move the wingtip between an extended position and a stowed position.

Abstract: According to one aspect of the present disclosure, an apparatus for shortening a wingspan of an aircraft is disclosed. The apparatus comprises a first track affixed to a fixed wing of the aircraft. A first roller assembly is affixed to a wingtip of the aircraft, with the first roller assembly moveably captured within the first track. A second track is also affixed to the fixed wing. A second roller assembly is affixed to the wingtip and is moveably captured within the second track. A wingtip actuation assembly is configured to translate the first roller assembly within the first track and the second roller assembly within the second track to move the wingtip between an extended position and a stowed position under the fixed wing.

Abstract: A multirotor aircraft that comprises a body, at least three motors and at least one wing that is connected to the body. The wing is designed to be folded and unfolded during flight of the multirotor aircraft and designed to change during the flight a low-drag creation position to a lift creation position, and vice versa. At least one motor has a greater motor power than another motor and the distance from the strong motor to the center of gravity of the multirotor aircraft is shorter than the distance from the another motor to the center of gravity. The wing is positioned in the geometric area between the motors.

Abstract: A drone is disclosed having a low acoustic signature. The drone includes a fuselage, a main inboard wing attached to the fuselage, a pylon located towards an aft end of the fuselage and having an end that is higher than the main inboard wing, and a propulsor connected to the pylon and situated above the fuselage. The drone includes a plurality of booms connected to the main inboard wing and a plurality of horizontal tails attached to the plurality of booms. The horizontal tails have an outboard tail arrangement and are tiltable.

Abstract: An extension linkage for a wing flap can include at least one arm that includes two elements connected by a joint. The linkage can include an actuation mechanism, additional arms and/or each arm can include more than two elements, tie rods and/or cross pieces connecting two or more arms, and any other suitable components. The linkage functions to translate and rotate a body attached to one end of the arm relative to a primary structure attached to a second end of the arm. The linkage resides entirely within a space defined by the upper skin and the lower skin of the wing rearward of the mounting when in a retracted configuration.

Abstract: A wing apparatus and aircraft are described providing greater maneuverability and efficiency for vertical takeoff and landing vehicles. Use of a fowler flap is shown in combination with a sliding panel. The sliding panel can nest within a wing similar to a fowler flap. During vertical maneuvers the sliding panel can be moved forward and on top of the wing. This can alleviate download during vertical maneuvers while minimizing drag as forward flight begins.

Abstract: In one embodiment, a drone is provided with several inflatable tubes that each connect a propeller component to a body of the drone. In order to increase the handling of the drone, a patch is placed on the top surface of each inflatable tube that includes some number of shape memory alloy wires. The shape memory alloy wires shrink and become rigid when an electric current is applied to them. The optimal locations on each tube to place the patches, and the shape of the patches, is determined using a topology optimization. Later, the wires in the patches can be selectively activated or deactivated by an operating entity to provide an additional means to control the drone. Additionally, the drone is equipped with several landing arms which may include a shape memory alloy torsion coil spring to help the arm deployment during landing.

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

Abstract: Disclosed is a wing in which, while a continuous surface is maintained, a chord length and camber of an airfoil may be modified via only a rotational drive alone, whereby a structure is simple and aerodynamic efficiency may be improved.

Abstract: Disclosed is an aircraft with a super high aspect ratio based on self-unfolding folding wing technology, the aircraft including: an aircraft body; a fixed wing; and a movable wing assembly including a first movable wing and a second movable wing. When the aircraft takes off, the first movable wing and the second movable wing are in a folded position. The first movable wing and the second movable wing are deflected and moved to an unfolded position or a folded position by the aerodynamic force and moment generated by the deflection of aerodynamic control surfaces and the differential thrust and moment generated by a distributed propulsion system.

Abstract: A radio frequency (RF) communication system may include mobile vehicles, with each mobile vehicle including RF equipment and a controller. The controller may be configured to determine a reward matrix based upon possible RF equipment configurations and associated operational parameters, and operate the RF equipment to implement an RF equipment configuration based upon the reward matrix. The system may also include an oversight controller configured to update respective reward matrices of the mobile vehicles.

Abstract: An aircraft (1002) including a wing (1001), having a fixed wing (1005) with a wing tip device (1003) moveably mounted at the outer end thereof. The wing tip device (1003) is moveable between: a flight configuration; and a ground configuration about an axis of rotation. The wing tip device (1003) and the fixed wing (1005) meet along an interfacing cut line (1035). The interfacing cut line (1035) includes a curved section (1039) cent red on the axis of rotation (1011), the radius of the curved section constantly increasing as the cut line passes around the axis (for example a spiral shape).

Abstract: A fluid foil has a main fixed portion and a tip portion movably mounted at a tip end of the main fixed portion. The main fixed portion has an upper surface and a lower surface, and the tip portion has an upper surface and a lower surface. The fluid foil is operable in: a) a first configuration in which the upper surface of the tip portion is angled downwardly with respect to the upper surface of the main fixed portion; and b) a second configuration in which the tip portion is rotated upwardly with respect to the first configuration such that the upper surface of the tip portion and the upper surface of the main fixed portion are substantially continuous surfaces. The movement of the tip portion with respect to the main fixed portion is exclusively passively actuated by movement of the foil with respect to a surrounding fluid.

Abstract: An unmanned aerial vehicle (UAV) is provided including a fuselage, a pair of wings extending outwardly from the fuselage, and a deployable surface moveable from a first undeployed position during normal flight to a second deployed position when there is a system failure during flight. A method of adjusting a center of pressure of a UAV is also provided including the steps of providing a UAV with a fuselage, a pair of wings extending outwardly from the fuselage, and a deployable surface moveable from a first undeployed position during normal flight to a second deployed position when there is a system failure during flight, sensing when there is a system failure, and moving the deployable surface from the first undeployed position to the second deployed position.

Abstract: An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.

Abstract: A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

Abstract: Described herein is an aircraft. The aircraft comprises a body. The aircraft also comprises a wing coupled to and extending from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The aircraft further comprises a strut. The strut comprises a strut inboard end portion coupled to and extending from the body and a strut outboard end portion coupled to and extending from the intermediate portion of the wing. The aircraft additionally comprises at least one aerodynamic control surface movably coupled to the strut.

Abstract: A hybrid wing autonomous aircraft having, an airframe, at least one hybrid wing member having an airframe end and an extended end, and having leading and trailing edges and a plurality of control structures, the airframe end coupled to the airframe, and the extended end further configured with a wing extension device, the wing extension device configured to extend a supplemental lifting surface from the extended end, an airframe actuator configured to cause the extension end of the hybrid wing member to move from a first position relative to the airframe to a second position relative to the airframe, wherein the second position is greater in distance from the airframe than the first position.

Abstract: An Unmanned Aerial Vehicle (UAV) has a fuselage, a rotor system, and a wing configured for selective positioning during flight of the UAV to a deployed position, a stowed position, and to positions between the deployed position and the stowed position. The UAV has a flexible wing skin at least partially carried by a leading arm and the leading arm is rotatable relative to the fuselage.

Abstract: Provided are multi-tread vehicles and methods of operating such vehicles to access small interior spaces. A multi-tread vehicle may include two or more tread sections such that each pair of adjacent tread sections is interconnected by a connector section. Furthermore, each pair may have one or more degrees of articulations, such as being pivotable with respect to each other around one or more axis and/or being bendable with respect to each other around one or more axis. These articulation degrees may be provided by the connector section and/or by couplings between the connector section and each tread section. In some embodiments, each tread section may include two portions detachably coupled to each other. This detachable coupling may be used for disassembly of the multi-tread vehicle after or even during its use, for example, when only a portion of the vehicle needs to be retrieved from an interior space.

Abstract: The present invention provides a foldable wing which comprises a wing supporting skeleton, a sliding rail, a skin supporting rib, a skin and a wing movement unit. The wing supporting skeleton comprises a horizontal beam, a longitudinal beam, a wing front edge beam, a wing trailing edge beam, a fixture connector and a sliding block, The wing supporting skeleton is a triangular girder for maintaining planar and sectional shapes of the foldable wing, supporting the skin supporting rib and the skin, and sustaining an aerodynamic load from the skin and a load of a fuselage. After the triangular girder is subjected to a force of the wing movement unit, a shape and an area of the triangular girder are changed so as to achieve folding and unfolding of the foldable wing. A rotocraft and a glider using the foldable wing are also provided.

Abstract: A skin for an aircraft is configured to be disposed on a first rigid member and on a second rigid member. The second rigid member is movable with respect to the first rigid member and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member comprises first segments forming a first portion attached to the first rigid member and second segments forming a second portion attached to the second rigid member. The first and second portions are separated along a substantially linear seam in the absence of change in the distance and an orientation between the first rigid member and the second rigid member.

Abstract: A winglet for attachment to a wing portion of an aircraft including a winglet root. The winglet root defines a recess for receiving a connector of the wing portion in use and includes at least one protrusion for receipt into at least one corresponding hole of the wing portion in use. A portion of the winglet root that at least partially defines an upper or a lower side of the recess has at least one hole extending therethrough for receiving a fastener for fastening the winglet to the connector when the connector is located in the recess.

Abstract: Illustrative embodiments may provide for an apparatus and method of controlling the folding of a wing. The apparatus may include a sensor, an actuator, and a wing fold controller. The method may include receiving a status of at least one of an aircraft and a wing fold system of the aircraft by the wing fold controller of the wing fold system. The method may also include receiving an automated command by the wing fold controller in response to receiving the status. The method may also include operating the wing fold system by the wing fold controller based on the automated command and the status. The method may also include transitioning a wingtip of a wing of the aircraft to one of a flight position and an on-ground position by an actuator of the wing fold system in response to commands from the wing fold controller.

Abstract: An unmanned air vehicle (UAV) having a fuselage, a foldable propulsion means to generate thrust leading to the UAV movement, a driving means to drive the propulsion means and a plurality of flight control surfaces actuators are further included. The UAV further includes at least one pair of foldable wings where the rear portion of the wings is pivotally attached to the fuselage. The wings having at least one roll control surface hinged to at least one of the foldable wings. At least a pair of tail stabilizers having ruddervators flight control surfaces hinged to the tail stabilizers. In a fully extended position or in ready to fly state position, each of the foldable wings are deployed perpendicular to one another and perpendicular to the fuselage to form an offset-x shaped wings, and in a stowed position, each of the wings are positioned parallel to one another and positioned parallel to the fuselage.

Abstract: A shutter mechanism for covering a wing's spreading opening formed in an airborne body and a method for covering such opening while implementing the shutter mechanism, wherein the shutter comprises at least one flap assembly, and wherein from the instant that a deployed wing of the airborne body passed and moved over it, it is biased by traction of at least one springy element to an angular motion around an axis, unto a condition where the flap component of the assembly is positioned so that it is substantially conformal to the outline of the outer surface of the fuselage of the airborne body and while it covers the opening through which the wing passed in its motion; and from an instant that the wing returned and connected to the flap component of the assembly, the flap is biased to an angular motion counter the spring, to the state that the wing returns and is relocated on its top surface.

Abstract: A supersonic aircraft having unique structural, geometrical, electromagnetic, mechanical, thermal and aerodynamic configuration is described. Its design characteristics maximize aerodynamic performance, speed, efficiency, comfort and range in the operational affect of carrying passengers over long distances at very high flight speeds and Mach numbers, generally above Mach 4.0+. It has fully integrated-mated fuselage twin engine nacelle structures which reduce and stabilize wave drag, wherein engines sit forward of the sonic boom electrode swept aerospace but are integrated right through the sub-wing, the aero-spike and inlet just above the top surface of the central wing, and above and the major wing mating join, attached via a massive composite titanium keel structure, through the central wing box and fuselage.

Abstract: A airborne vehicle comprising a fuselage, a folding wing-like structure which is movable from a stowed position to a deployed position, and a hinge mechanism which couples the folding wing-like structure to the fuselage in a manner so that the folding wing-like structure displaces and rotates during movement from the stowed position to the deployed position. The hinge mechanism is housed within an outer mold line of the fuselage and folding wing-like structure to decrease the signature of the airborne vehicle.

Abstract: A manual wing-fold mechanism provides a means by which to reconfigure the wing of an aircraft between a flight configuration and one that can be easily stowed and transported. The folding mechanism includes an extension tube that enables the outboard portion of the wing to be extended away from the inboard section of the wing, rotated about the lateral axis of the aircraft and then pivoted rearward so that the wing is aligned with the longitudinal axis of the aircraft along side the fuselage. The wing-fold mechanism is independent of the structural components of the wing used to convey aerodynamic loads during flight and provides a means for the user to bring the outboard wing section into a near alignment position while the wing-fold mechanism thereafter assists to refine the alignment into its final flight configuration.

Abstract: A joint for coupling a wing tip to a wing base includes a linking member that extends from a first end to a second end. The linking member first end is coupleable to the wing base, and the linking member second end is coupleable to the wing tip. The linking member may be curved and may extend for a fixed distance between the wing tip and the wing base. The linking member defines first second hinge lines that are substantially parallel. The joint also includes at least two actuators. A first end of each actuator is coupled to the linking member, and a second end of each actuator is coupleable to one of the wing base and the wing tip. The actuators are operable to rotate the wing tip about the first and second hinge lines between a first orientation and a second orientation relative to the wing base.

Abstract: A retractable rotor blade assembly includes a rotor hub assembly having a rotor hub wall, a pitch disc mounted to the rotor hub wall for undergoing rotation about a longitudinal axis, and retractable rotor blades configured to be extended and retracted relative to the rotor hub assembly. Each of the rotor blades has an interlink assembly, a blade base, and a damper for dampening movement of the interlink assembly during extension and retraction of the rotor blade. The interlink assembly includes a plurality of interconnected link base subassemblies each configured to be translated along a span of the rotor blade such that each subsequent link base subassembly becomes stacked one atop the other while remaining connected to a next link base subassembly. The blade base is interconnected between the pitch disc of the rotor hub assembly and one of the interconnected link base subassemblies.

Abstract: An unmanned aerial vehicle (UAV) can be deployed from a small stowed package for flight and stowed back into the package after the flight is complete is disclosed. The UAV is retracted to a volume that is less than half of it's fully deployed volume. This allows the UAV to be transported to any desired field position on a truck or other convenient transportation. The UAV may also be launched from a ship deck. In a further aspect, the flexible deployment of the UAV will allow a single UAV to be used in place of multiple types of UAVs.

Abstract: An aircraft comprises a foldable wing, the wing comprising an inner region and an outer region, such as a wing tip. The outer region is moveable relative to the inner region between a flight configuration and a ground configuration in which the span is reduced. The aircraft comprises a control system and a control interface. The control interface comprises a selector for selecting the desired configuration of the outer region, and is arrange to provide: a first output, such as a light, when the flight configuration is selected and the outer region is in the flight configuration; a second output, such an amber light, when the ground configuration is selected and the outer region is in the ground configuration; and a third output, such as a red light, when the outer region is not in the selected configuration.

Abstract: An apparatus and methods for changing the shape of a wing using a trailing edge morphing beam. One example method includes coupling a trailing edge portion comprising a morphing beam to an elastic central portion of the wing. The morphing beam comprises a first portion formed of smart material and a second portion formed of elastic material. The method further includes actuating the smart material in the first portion of the morphing beam to change the shape of the elastic central portion of the wing and the elastic material of the morphing beam. The morphing beam can be configured to hold a first position corresponding to a minimum chord-length of the wing and a second position corresponding to a maximum chord length of the wing.

Abstract: A collapsible wing, methods of producing the collapsible wing, and an unmanned aircraft system that includes the collapsible wing are provided.

Abstract: A dual channel wing for an aircraft, comprising an inboard and an outboard portion, wherein each portion comprises a channel wing section. Each channel may include a propulsor and the propulsors of each of the channels may be offset relative to one another in the chordwise direction of the wing. The wing may be foldable upon itself about a chordwise axis such that the inboard and outboard channels overlap. At least one dual channel wing may also be located on an aerocar.

Abstract: A collapsible wing, methods of producing the collapsible wing, and an unmanned aircraft system that includes the collapsible wing are provided.

Abstract: An apparatus and methods for changing the shape of a wing using a plurality of morphing structures. One example method includes coupling a plurality of morphing structures to each other. Each morphing structure includes an anchor, a plurality of hinges, a plurality of shape-memory alloy members wherein each shape-memory alloy member extends from the anchor to a different hinge, a plurality of springs wherein each spring extends from the anchor to a different hinge, and a plurality of rigid members wherein each rigid member extends between two hinges. The method further includes actuating the plurality of shape-memory alloy members in at least some of the morphing structures wherein the shape-memory alloy members contract when actuated to pull against the hinges and anchors within the actuated morphing structures to rotate the rigid members and change the shape of the actuated morphing structure.

Abstract: An aerodynamic body that can be adjusted relative to a main wing of an aircraft by an adjusting device is provided. A gap between the aerodynamic body and another aerodynamic body or a component of the fuselage or the main wing is formed on one lateral end and said and the gap is variable due to the adjustability of the aerodynamic body. The body features a gap bridge-over device with a shell part that extends along the gap and overlaps the outer shell of the aerodynamic body in the wingspread direction on the front side thereof so that the shell part can be telescopically moved relative to this aerodynamic body in the wingspread direction. An airfoil for an aircraft with a main wing and a plurality of aerodynamic bodies that are arranged adjacent to one another transverse to the chord direction is also provided.

Abstract: An air vehicle wing includes foldable ribs coupled to a leading-edge spar. The ribs each have multiple rib segments which are foldable (hinged) relative to each other. Extension linkages, each with multiple extension linkage segments, pass through openings in the rib segments, and may be coupled to the rib segments with pin couplings, able to change relative angle between the individual rib segments and the extension linkage segments to which they are coupled. A skin may cover the ribs, to provide an outer surface of the wing that may be unfolded as the wing is expanded from a stowed, small-chord condition, to a deployed, large-chord condition.

Abstract: A flexible tip for integration in a wing trailing edge employs a wing structure rear spar. A flexible upper skin is attached at a forward boundary to the spar and a rigid lower skin is interconnected to the flexible upper skin at a rigid tail piece. At least one actuation link is attached to the rigid tail piece and has a hinge at a forward edge of the rigid lower skin. At least one positioning slider is attached to the hinge which is movable from a neutral position to a first extended position urging the hinge aft for rotation of the rigid lower skin upward and flexing of the flexible upper skin in an upward camber and to a second retracted position urging the hinge forward for rotation of the rigid lower skin downward and flexing of the flexible upper skin in a downward camber.

Abstract: An adaptive structural core includes a plurality of core members arranged in a repeating pattern, a plurality of actuator attachment points provided on the plurality of core members and at least one actuator engaging the plurality of actuator attachment points.

Abstract: A single slotted trailing edge flap arrangement for an aircraft wing, comprising a main flap element and an auxiliary flap element sealed to and supported by the main flap element for movement between a retracted and an extended position relative to the main flap element so as to vary the planform area of the flap. The auxiliary flap element remains sealed to the main flap element when in its extended position, and movement of the auxiliary flap element relative to the main flap element is solely translational. The auxiliary flap element may be translationally deployed from the main flap element by sliding the auxiliary flap element out from the underside of the main flap element. Also, a method of operating the flap arrangement.

Abstract: A system is provided for reducing aeroacoustic noise generated by an aircraft having wings equipped with trailing-edge flaps. The system includes a plurality of elastically deformable structures. Each structure is coupled to and along one of the side edges of one of the trailing-edge flaps, and is coupled to a portion of one of the wings that is adjacent to the one of the side edges. The structures elastically deform when the trailing-edge flaps are deployed away from the wings.

Abstract: A method and apparatus for improved aircraft control through the use of adjustable winglets. The adjustable winglets are located at the terminal ends of an aircraft's wings and may pivot about an axis parallel to the yaw axis of the aircraft. The adjustable winglets may also include outboard ailerons for improved control of the aircraft.

Abstract: A system and method to control flight of an aircraft. The aircraft having an engine with a rotatably nozzle assembly configured to create forward propulsion and yaw control of the aircraft. The engine exhaust passing through the nozzle is redirected with a valve disposed within the nozzle. Lift is created with a lift system carried by the wing of the aircraft. Additional lift is created during flight with a retractable wing extension disposed within the wing of the aircraft.

Abstract: The present invention relates to a method of reducing the vibration of a lift and propulsion rotor (5) of a rotorcraft (1), the rotor having a plurality of airfoil assemblies (10) that perform rotary movement around a drive axis (AX) of the rotor (5), each airfoil assembly (10) comprising a blade (20) extending longitudinally from a root (22) suitable for being fastened to hinge means (4) of a hub (6) of said rotor (5) to a free end (21), a first distance (D1) extending between said free end (21) and said hinge means (4). In the method, said first distance (D1) is caused to vary cyclically so that the projection (TR) of the center of gravity (Cg) of a blade (20) on a horizontal plane (P) perpendicular to said drive axis (AX) and containing said hinge means (4) describes a circle.

Abstract: A shape-change material includes a shape memory material layer with an electrically conductive layer on a surface of the shape memory material layer. The conductive material may be used to heat the shape memory material by electrical resistance heating. The conductive material may be a primary heater, providing the heating to cause softening or shape change in the shape memory material, or may be a secondary heater in conjunction with a greater amount of heating from a primary heater, such as a conductive plate that provides electrical resistance heating to a surface of the shape memory material on an opposite side of the shape memory material from the conductive material. One use for the shape-change material is as the skin material for a shape changing material.

Abstract: A method and apparatus may be present for moving a wing. A plurality of lifting assemblies may be attached to a first plurality of channels in a ring associated with the wing of an aircraft. A plurality of base assemblies may be attached to a plurality of fittings with a second plurality of channels associated with a fuselage of the aircraft. The plurality of lifting assemblies may be moved away from the plurality of base assemblies using a plurality of biasing systems such that the ring may move away from the fuselage.