1831results about "Wing adjustments" patented technology

A flow control device, having: a flow tube extending between upstream and downstream, and a neck region between the first and second ends, wherein the flow tube includes: a wall defining an outer boundary and extending longitudinally from a first end to a second end and transversely from a first side to a second side, wherein: the wall is nonmetal; the wall defines: a first segment extending longitudinally between the first and second ends and transversely from the first side to a segment junction; and a second segment extending longitudinally between the first and second ends and transversely from the second side to the segment junction; and the first segment has a first coefficient of thermal expansion (CTE) and the second segment has a second CTE that differs from the first CTE, to define a transverse CTE gradient.

An airfoil having: a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.

An airfoil, having: a body defining a leading edge and a trailing edge, wherein the body comprises: a base having an outer boundary extending longitudinally from a first end to a second end and transversely from a first side to a second side; and beads within the outer boundary, wherein each of the beads has a bead void, and wherein one or more of the beads includes: damping element within the bead void; or stiffening element extending across the bead.

An airfoil having: a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.

An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The clutch is coupled to the geared rotary actuator by a shaft and the shaft is fixed in rotation to a mass disposed radially outwardly from the shaft.

A variable-sweep wing for a tiltrotor aircraft includes a fuselage link coupled to the fuselage and a pylon link coupled to a pylon. A wing airframe has a root end pivotably coupled to the fuselage link and a tip end pivotably coupled to the pylon link. A driveshaft is coupled between the fuselage link and the pylon link and is positioned within the wing airframe. The driveshaft is operable to transmit torque from the main gearbox to a proprotor gearbox. A crank is coupled between the fuselage link and the pylon link and is positioned within the wing airframe. The fuselage link, the pylon link, the driveshaft and the crank form a linkage such that pivoting the crank relative to the fuselage link causes the wing airframe to shift between a substantially straight wing configuration for low-speed forward flight and a swept wing configuration for high-speed forward flight.

The invention discloses a folding wing structure of an unmanned aerial vehicle, which comprises a rotating shaft embedded in a vehicle body, wherein a lower wing elastic sheet and an upper wing elastic sheet are mounted in an inner cavity of the rotating shaft from bottom to top, a first locking block and a second locking block are respectively arranged at the free ends of the lower wing elastic sheet and the upper wing elastic sheet, the first locking block and the second locking block are respectively matched with a first notch and a second notch which are formed in the rotating shaft, the outer side of the rotating shaft is sequentially sleeved with a lower wing and an upper wing from bottom to top, the upper surface of the lower wing and the lower surface of the upper wing are each provided with a groove, the two grooves are oppositely formed to form a torsional spring groove, a torsional spring is arranged in the torsional spring groove, and the upper inner sides of the lower wingand the upper wing are provided with a first locking groove and a second locking groove correspondingly; and the outer side of the rotating shaft is further sleeved with a roller bearing, a baffle isinstalled at the top of the rotating shaft, and the roller bearing is located between the upper wing and the baffle. The processing cost of the unmanned aerial vehicle is reduced, the folding wing structure is insensitive to the structural size, and the folding wing structure can adapt to a more miniaturized barrel-shooting unmanned aerial vehicle.

The present invention comprises an aerodynamic profile body with an outer flow surface for flow by a fluid, wherein the aerodynamic profile body comprises: - an upper cover layer and a lower cover layer, which form at least part of the outer flow surface and are designed to be flexurally elastic in an end section of the aerodynamic profile body, and - an actuator device with at least one actuator provided in an interior of the aerodynamic profile body, which actuator interacts with at least one of the cover layers in the flexurally elastic end section in such a way that the cross section of the aerodynamic profile body in the flexurally elastic end section can be changed by the at least one actuator, characterized in that - the at least one actuator is fastened with a first actuator end to a first fastening point in the interior and with at least a second actuator end to a second fastening point in the interior, - wherein the second attachment point is arranged transversely to the span of the aerodynamic profile body at a distance from the first attachment point and on an inner side of one of the cover layers in the flexurally elastic end section, and - the at least one actuator is designed such that the linear distance between the first attachment point and the second attachment point can be changed in order to change the cross-section of the aerodynamic profile body.

A flying vehicle with a flight part connected to a plurality of rotor wing parts and a main wing, wherein the main wing is configured such that the lift produced by the main wing during landing is reduced compared to the lift produced by the main wing during cruising. Furthermore, the main wing is fixed at a forward tilt with respect to the flight part. Furthermore, the rotor wing is connected at an angle that produces propulsion and lift during cruise. Furthermore, the rotor blades are connected at an angle that generates propulsive force during cruise.

The invention provides a semi-folding wing automatic unfolding and locking device and an unmanned aerial vehicle. The locking device comprises a fuselage wing and a locking device, the folding wings are hinged to the fuselage wings; the hinge mechanism comprises a hinge shaft and a hinge torsion spring, the folding wings are hinged to the fuselage wings through the hinge shaft, the hinge torsion spring is arranged on the hinge shaft in a sleeving mode, the hinge torsion spring is connected with the folding wings and the fuselage wings, and when the folding wings are folded relative to the fuselage wings, the hinge torsion spring is in a deformation state; the first locking mechanism is arranged on the fuselage wings; the first locking mechanism is arranged on the folding wing, the second locking mechanism is arranged on the folding wing, the first locking mechanism is movably connected with the second locking mechanism, and when the folding wing is unfolded relative to the fuselage wing, the first locking mechanism and the second locking mechanism are in a locking state. Due to the fact that the fuselage wings are hinged to the folding wings through the hinge mechanisms, the semi-folding wings can be placed in a launching box with small width and regular appearance to be stored and launched in the folded state, and storage and transportation of the semi-folding wings are facilitated.

In an aircraft wing structure where space and weight considerations are a principal concern, there may be significant challenges in providing a moveable slat and / or a spoiler, particularly in combination with one another. A control device for an aircraft includes upper and lower flaps pivotably mountable adjacent to a slot in a wing behind a leading edge, wherein the control device is operable in a lift configuration to move the upper and lower flaps towards each other to abut opposing surfaces of the slot, to permit airflow along the slot.

The invention provides a morphing wing integrating telescopic variable-elongation and rotary variable-sweepback functions and a morphing method. The morphing wing comprises an inner wing section, an outer wing section and an elastic skin, the inner wing section and the outer wing section are positioned in the same spanwise plane; the inner wing section stretches and retracts in the spanwise plane along the spanwise direction of the wing, so that the span length of the inner wing section is adjusted; the outer wing sections rotate in the chordwise direction relative to the inner wing sections in the spanwise plane, and then the sweepback angles of the outer wing sections are adjusted. By adjusting the extension length and the sweepback angle of the wings, the lift force of the aircraft during low-speed flight is improved, and the resistance of the aircraft during high-speed flight is reduced. Specifically, the extension length of the wings is increased during low-speed flight to improve lift force, and the extension length is reduced and the sweepback angle is increased during high-speed flight to reduce resistance. The optimal aerodynamic performance can be achieved no matter in a low-speed flight state or a high-speed flight state, and the adaptability and the flight performance of the aircraft are remarkably improved.

The invention discloses a foldable composite configuration vertical take-off and landing unmanned aerial vehicle which comprises a fuselage, a front wing, a rear wing, a control plane, an execution mechanism, a rotor wing motor and a propeller, the front wing and the rear wing are connected with the fuselage through a front folding mechanism and a rear folding mechanism respectively, and the front wing and the rear wing are in an X-shaped layout after being unfolded. Rotor motors and propellers are installed on the front wings, control surfaces and execution mechanisms are installed on the rear wings, and the front wings and the rear wings can be folded to be attached to the fuselage. According to the unmanned aerial vehicle, only one power system is used, the unmanned aerial vehicle has the vertical take-off and landing capacity and high flexibility of a multi-rotor unmanned aerial vehicle and the low-energy-consumption cruising and high-speed flying capacity of a fixed-wing aircraft at the same time, the wings can be folded to be attached to the fuselage, the outer contour is cylindrical after folding, and the unmanned aerial vehicle is compact in structure and more convenient to store, transport and carry; in addition, the device can support the modes of barrel type launching, ground takeoff, handheld takeoff, high-altitude spreading and the like for deployment.

An aircraft is disclosed having a device and an aircraft wing. The aircraft wing includes a main wing element and a movable wing tip device attached to a tip end of the main wing element. The movable wing tip device includes an accumulator configured to store energy and the movable wing tip device can move relative to the main wing element to vary a span of the aircraft wing. The accumulator is configured to transmit power to the device. The accumulator enables energy to trickle between the main wing element and the movable wing tip device whilst still providing a suitable power source to the device. Additional embodiments include a method of maintenance, and a method of operating the aircraft wing to store energy in the movable wing tip device.

The present application discloses an aircraft. The present application discloses a method of assembling or disassembling an aircraft. The assembly method includes mounting a first engine nacelle to a first wing, mounting a second engine nacelle to a second wing, causing the first wing to be extended relative to a fuselage mount, causing the second wing to be extended relative to the fuselage mount, and mounting the fuselage to the fuselage mount.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The system may include a sweeping gearbox designed to deploy at least one wing from a compact to a deployed arrangement. A controller may be configured to detect launch conditions, monitor for conditions, and trigger the gearbox upon condition fulfillment. Activation of the sweeping gearbox may result in wing deployment, adapted to the detected conditions. The method may involve deploying wings using the sweeping gearbox, launching detection, monitoring for conditions, and activating the gearbox for wing deployment upon condition detection.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

The invention discloses a folding wing and rudder design method and an unfolding locking mechanism thereof. The locking mechanism comprises a connecting handle, an elastic torsional spring and a rotating shaft. A locking head and a connector are arranged on the two sides of the bottom of the folding wing or the folding rudder respectively; the design method comprises the steps of obtaining performance parameters, and determining specific indexes such as folding sizes and unfolding time of the folding wing and the rudder. And designing a structural model according to principles of generalization, reliability and the like, and determining geometric parameters of the wing and the rudder. Verifying the strength of parts of the locking mechanism, calculating a plurality of parameters of an elastic torsion spring, and analyzing the unfolding time and synchronism. Finally, consistency checking is conducted based on finite element simulation analysis, torque and bending moment are applied in ABAQUS software according to parameters, the structural strength of the folded rudder is analyzed, and it is ensured that the design meets the requirement. According to the folding wing and rudder design method, through the scientific design process and multi-principle comprehensive application, the high-performance requirement is met, meanwhile, the cost is effectively reduced, the reliability and maintainability of products are improved, and the remarkable beneficial effects are achieved.

Embodiments are shown for a machine and process to rotate and fix a second structure relative to a first structure via a hinge that may include a central axis, a lock-plate, and a moveable, a stationary, and a driving, member. The process may include: attaching a hinge to the first structure; moving a pin, extending parallel to the central axis through the stationary and driving members, out of a first notch of the movable member toward the central axis via rotating the driving member around the central axis; rotating the movable member via rotating the second structure around the central axis; fixing the movable member by latching the hinge via moving the pin away from the central axis and into a second notch in the movable member; and locking the latch by moving, along a length of the central axis, the lock-plate toward the driving member and the pin.

The invention discloses a small tandem wing unmanned aerial vehicle folding mechanism which comprises a pair of front wings, a pair of rear wings, a pair of vertical empennages and a fuselage, the front wings and the rear wings are in tandem wing layout on the fuselage after being unfolded, and in a folding state, the pair of front wings rotate backwards around a front rotating shaft to coincide with the back of the fuselage, and the pair of vertical empennages rotate backwards around a rear rotating shaft to coincide with the back of the fuselage. The pair of rear wings rotate forwards around the rear rotating shaft to coincide with the bottom of the fuselage, and the pair of vertical empennages rotate downwards to coincide with the side face of the fuselage. A front spring support is installed on the back of the fuselage and located at the front end of the front rotating shaft, and the pair of front wings is connected with the front spring support through tension springs. A rear spring support is installed at the bottom of the fuselage and located at the rear end of the rear rotating shaft, and the pair of rear wings is connected with the rear spring support through tension springs. The tandem wing layout is adopted, the front wings and the rear wings serve as lift wings, the area of the wings is increased, the size of the unmanned aerial vehicle is reduced, and combat maneuverability is improved.

An aircraft wing has a leading edge, a fixed wing portion and a leading-edge spoiler device. The spoiler device is hingedly mounted relative to the fixed wing portion adjacent the leading edge, moveable between retracted and deployed positions. In the retracted position a spoiler surface forms a continuous surface with a fixed wing portion upper aerodynamic surface, and in the deployed position the spoiler surface is rotated relative to the upper aerodynamic surface. In the retracted position the spoiler surface has a first portion forward of the hinge and a second portion aft of the hinge. A center of pressure of the local wing section acts on the spoiler surface providing a moment about the hinge in a first direction to bias the spoiler device to the retracted position and providing a moment about the hinge in a second, opposite direction, rotating the spoiler device to the deployed position.

The invention discloses a multi-degree-of-freedom morphing wing based on a zero poisson ratio superstructure, and belongs to the technical field of morphing wings. The wing comprises a front edge section, a wing body and a rear edge section which are sequentially connected, the front edge section comprises an inner side front edge plate, a middle front edge plate and an outer side front edge plate, the wing body comprises a plurality of zero-Poisson-ratio honeycomb structures, each zero-Poisson-ratio honeycomb structure is formed by arraying a plurality of zero-Poisson-ratio unit cell cubic structures, and the adjacent zero-Poisson-ratio unit cell cubic structures share a connecting rod; the rear edge section comprises an inner side rear edge plate, a middle rear edge plate and an outer side rear edge plate; the inner-side front edge plate and the inner-side rear edge plate, the middle front edge plate and the middle rear edge plate, and the outer-side front edge plate and the outer-side rear edge plate are respectively connected through zero-Poisson-ratio honeycomb structures which are arranged along the chord length direction of the wing; the two sides of the middle front edge plate are connected with the inner side front edge plate and the outer side front edge plate through zero-Poisson-ratio honeycomb structures arranged in the extension direction of the wing correspondingly, and the two sides of the middle rear edge plate are connected with the inner side rear edge plate and the outer side rear edge plate through zero-Poisson-ratio honeycomb structures arranged in the extension direction of the wing correspondingly. The wing has four deformation functions of variable elongation, chord length, dihedral angle and camber, so that the aircraft can adapt to different flight environments and tasks.

The invention discloses a deformable wing with the characteristics of large unfolding-folding ratio and high bearing capacity. The deformable wing comprises a bearing structure, a driving mechanism, a wing surface dimensional structure and an accessory structure, the bearing structure comprises a plurality of groups of telescopic mechanisms, wing ribs and corner boxes; the accessory structure comprises a mounting plate, and the mounting plate is connected with the machine body; each group of telescopic mechanisms comprises a plurality of stages of telescopic rods which are arranged along the chord length direction and are fixed on the mounting plate; the wing ribs are arranged in the wingspan direction and are connected with the multi-stage telescopic rods through the angle boxes to form a wing framework; the driving mechanism penetrates through the hollow parts of the wing ribs, and two ends of the driving mechanism are respectively connected with the mounting plate and the wing rib on the outermost side of the wing; the wing skeleton is externally coated with the wing surface dimensional structure to form a wing shape.

An aircraft wing is provided having a fixed wing with a gulled wing tip rotatably mounted at the tip thereof, the gulled wing tip extending below a wing plane defined by the end of the fixed wing such that the centre of gravity of the gulled wing tip is located below the wing plane. Lowering the centre of gravity of the gulled wing tip has been found to reduce the onset of flutter. The gulled wing tip may be gulled about a hinge axis where it meets the fixed wing, or may be otherwise folded or curved to lower the centre of gravity of the gulled wing tip.

The orthotropic chiral superstructure comprises unit cells distributed in an array mode, a rib is a straight edge rib, two upper nodes are tangent to the upper rib, the distance between the circle centers of the two upper nodes is the node center distance a, a lower rib is a straight edge rib, two lower nodes are tangent to the lower rib, and the distance between the circle centers of the two upper nodes is the node center distance a. The left rib is a bent rib defined by a Bezier curve, the two ends of the left rib are connected and tangent to the upper node and the lower node on the left side respectively, the right rib is a bent rib defined by a Bezier curve, and the two ends of the right rib are connected and tangent to the upper node and the lower node on the right side respectively.

The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight.

The invention provides a tailstock type tailless layout amphibious aircraft adopting foldable wings and a design method, and relates to the field of amphibious aircraft design. According to the invention, aiming at a tailless-layout tailstock-type amphibious aircraft, by designing a foldable wing mechanism, the wings are unfolded to keep a high aspect ratio layout during air cruise, and the wings are folded to form an envelope layout for a fuselage during water surface dwelling and stopping; therefore, the aerodynamic performance requirement of the tailless layout tailstock type amphibious aircraft in an air cruising mode and the requirement of the tailless layout tailstock type amphibious aircraft in a water surface dwelling mode for the gravity center stabilizing distance and the floating stability are met, and the tailless layout tailstock type amphibious aircraft can take off quickly under the high sea condition. The problems that the relative positions of the gravity center, the pneumatic focus and the stable center of a traditional tailstock type fixed wing aircraft in the water surface floating state and the air cruising flight state are difficult to design, and the stability of the aircraft in the water surface floating state is difficult to guarantee through a traditional layout design are solved.

The invention relates to a device comprising an asymmetrical wing profile (2) and an adjusting device (15), which asymmetrical wing profile (2) has a profile thickness (q) and a profile chord (p) extending between a wing leading edge (n) and a wing trailing edge (e), which asymmetrical wing profile (2) has, in at least one longitudinal portion (L1-Ln), a three-part variable wing profile (21) in which a front and a rear wing segment (211, 213) are joined to a central wing segment (212) in an articulated manner by means of two hinges (214) having axes of rotation (z) and are designed to permit a rotational movement about the associated axis of rotation (z) with respect to the central wing segment (212).

The invention discloses a variable-elongation sweepback wing scaling wing deformation device and a deformation method thereof, and relates to the technical field of deformation mechanism design of variant aircrafts, the aerodynamic configuration of a variable-elongation sweepback wing scaling wing is composed of a fuselage section, a sweepback fixed section and a telescopic section, the fuselage section is composed of a fuselage shell and an upper hatch cover, and the upper hatch cover is composed of an upper hatch cover and a lower hatch cover. The sweepback fixed section is composed of an upper wing surface shell and a lower wing surface shell, the telescopic section is an independent telescopic wing shell, the fuselage section and the shell of the sweepback wing fixed section are fixed through a sunk screw, and therefore it is guaranteed that the aerodynamic shape meets the aerodynamic design requirement; the linear guide rail is fixedly connected to the lower wing surface shell, and the telescopic wing can move along the linear guide rail; electric push rods are used for driving and are fixed in the fuselage, and inner rods of the electric push rods are connected with the telescopic wings, so that the telescopic wings are controlled to move along the linear guide rails; according to the method, the aerodynamic configuration of the scaled wing is segmented, so that the aerodynamic configuration and internal movement components of the scaled wing are mounted, and the extension length of the wing is changed by driving the telescopic wing to move along the linear guide rail through the electric push rod, so that the lift-drag ratio of the aircraft in the flying process is changed; the method can provide an implementation method for the equivalent scaling experiment of the deformable wing.