1121results about "Wing adjustments" patented technology

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.

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.

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.

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.

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.

An aircraft with a folding wing tip arrangement having a wing tip device mounted at a joint at the end of a fixed wing. It is desirable to transfer power and / or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and / or with changes in tensional loads. A wiring harness includes a plurality of conductors and is arranged to transmit electrical power and / or data to the wing tip device. A length of the harness is received in a protective sleeve, and the sleeve extends over a length of the wiring harness spanning the joint, the sleeve being removable from the wiring harness.

An aircraft with a folding wing tip arrangement and first and second wiring harnesses extending between a fixed wing and a wing tip device is disclosed. It is desirable to transfer power and / or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and / or with changes in tensional loads. The wiring harnesses include a plurality of conductors and are arranged to transmit electrical power and / or data to the wing tip device. The sleeve includes two channels to receive the harnesses, the position of the channels being fixed, relative to one another, such that the harnesses are held apart.

An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one precondition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one precondition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one precondition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

An aircraft includes a wing and a leading-edge aerodynamic surface coupled to the wing. An actuator is disposed within the wing and coupled to the leading-edge aerodynamic surface via a linkage system. Two or more hinge systems are coupled to the leading-edge aerodynamic surface and configured to rotate about a fixed axis internal to the wing to move the leading-edge aerodynamic surface between a retracted position and a drooped position.

Provided are computer-implemented methods for autonomously controlling an aircraft with vertical take-off and landing capabilities and folding wings that includes controlling a plurality of thrust producing components of an aircraft to cause the aircraft to rise vertically when wings of the aircraft are in a first folded configuration, where when the wings of the aircraft are in the first folded configuration, a leading edge of each wing is oriented in a vertical direction setting motor controller gains based on the wings of the aircraft being in the first folded configuration, and causing the aircraft to align with a direction of airflow when the wings of the aircraft are in the first folded configuration, and controlling thrust producing components and control surfaces and internal articulation mechanisms of the aircraft to cause the aircraft to transition from folded wing configuration to unfolded wing configuration. Systems and computer program products are also provided.

An aircraft wing includes a main wing and a high lift assembly which includes a high lift body and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body is movable between retracted and extended positions. The connection assembly includes primary and secondary connectors mountable to and engageable with the main wing via primary and secondary mount profiles, respectively. The primary connector is rotatable relative to the primary mount profile and at least one of the connection assembly and the main wing to configure the primary connector and mount profile between a decoupled configuration in which the primary connector may be moved into so as to be engaged with, and removed from so as to be disengaged from, the primary mount profile, and a locked configuration wherein movement between the primary mount profile and the secondary mount profile is restricted.

The invention relates to the field of aircraft wing design, in particular to a multi-stage telescopic wing for improving the flight performance of an aircraft, the extension length and the area of the wing are changed through multi-stage stretching of the wing, and different requirements of the aircraft for the wing in low-speed and high-speed flight states are met. When the aircraft takes off, lands and flies at a low speed, the telescopic wings stretch out to increase the area of the wings and enable the aircraft to obtain enough lift force, and when the aircraft flies at a high speed, the telescopic wings retract to reduce the extension length and area of the wings and enable the aircraft to obtain enough lift force and reduce the resistance of the wings, so that the extension length and area of the wings are changed through extension of the wings; and the aircraft can simultaneously meet different requirements on the extension length and the area of the wings in low-speed and high-speed flight states.

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 relates to the technical field of unmanned aerial vehicles, in particular to an inflatable wing type variable wingspan unmanned aerial vehicle. The unmanned aerial vehicle comprises a vehicle body, variable inflatable wings are arranged on the two sides of the vehicle body, the variable inflatable wings are connected with an inflation and deflation mechanism arranged in the vehicle body, each variable inflatable wing comprises a hollow fixed inflatable wing body and an extended inflatable wing body, and an inflatable part of each extended inflatable wing body is arranged outside a hollow cavity of the corresponding hollow fixed wing body; the uninflated part of the extended inflatable wing body is arranged in the hollow cavity, and the extended inflatable wing body is connected with the telescopic part of the extended driving mechanism. According to the inflatable wing type variable wingspan unmanned aerial vehicle, the variable inflatable wings are adopted, the wingspans of the whole wings are adjusted by lengthening the inflatable wing bodies, the unmanned aerial vehicle adapts to different flight states, and the unmanned aerial vehicle is of a relative folding structure, so that multi-stage adjustment is achieved.

The invention discloses a bionic shaddock peel vibration reduction and energy absorption structure and a preparation method thereof, and relates to the technical field of aircrafts, a gradient chiral shaddock structure GCCS comprises a contact layer, a transition layer and a supporting layer, each layer comprises three bionic chiral shaddock structures, the three structures comprise a bionic chiral grapefruit structure-L type, a bionic chiral grapefruit structure-Q type and a bionic chiral grapefruit structure-D type. Three bionic shaddock peel dot matrix structures with porous characteristics and chiral spiral characteristics are created on the basis of a shaddock peel surface microstructure and chiral spiral characteristics existing at tendrils of natural climbing plants; the three bionic chiral grapefruit structures are combined into the gradient grapefruit chiral structure with negative honeycomb gradient change by reference to a macroscopic gradient strategy, and compared with a traditional lattice structure, the gradient grapefruit chiral structure is more excellent in mechanical bearing performance and vibration reduction performance.

An aircraft wing having a fixed wing and a moveably mounted wing tip device is disclosed. A first cable harness and a second cable harness which are received in a protective sleeve extend between the fixed wing and the wing tip device. The protective sleeve is in a secured configuration in which at least two opposing parts of the protective sleeve are secured together between the first cable harness and the second cable harness to provide the sleeve with a first channel in which the first cable harness is received a second channel in which the second cable harness is received, and a webbing region extending between the first channel and the second channel such that the first and second cable harnesses are held apart by the webbing region.

In one embodiment, a heat sink assembly includes a heat sink including a plate having a surface. The heat sink assembly also includes an array of fins extending from the surface, where each fin is elliptical in cross section such that each fin has a length that is greater than a width, and fins of the array of fins are aligned such that an axis defined by the length is in a common direction among the array of fins. The heat sinks may be provided on a baffle that can transition between a retracted state and an inclined state.

The invention relates to a steering engine and piezoelectric patch hybrid driven variable camber wing, belongs to the technical field of aerospace, and solves the problems of poor wing surface deformation continuity and poor transmission effect in the prior art. The plurality of flexible trailing edge deflection modules are arranged in the straight wing main body; the skin structure is arranged on the outer surfaces of the straight wing main body and the flexible trailing edge deflection module; the module connecting structure is connected with the plurality of flexible trailing edge deflection modules; wherein the straight wing main body comprises a front edge D-shaped structure wing box, a plurality of wing ribs arranged on the rear side of the front edge D-shaped structure wing box, and a bearing rear wall arranged on the rear sides of the wing ribs; each flexible trailing edge deflection module comprises a driving rib assembly fixed to the bearing rear wall, driven rib assemblies arranged on the two sides of the driving rib assembly, carbon rods sequentially connected with the driving rib assembly and the driven rib assemblies, an inhaul cable driving mechanism and a piezoelectric driving mechanism, and the driving rib assembly and the driven rib assemblies are sequentially arranged in the longitudinal direction of the variable-camber wing.

Actuation assembly for a trailing edge flap of an aircraft wing, comprising: a base unit configured to be fixated to a main body of the aircraft wing; an intermediate unit movably connected to the base unit and configured to be hingeably connected to the flap at a leading edge of the flap about a first hinging axis extending along the leading edge of the flap, wherein the movability provides adjustability of the flap between a retracted flap position and an extended flap position; and a second actuator configured to controllably rotate the flap with respect to the intermediate unit about the first hinging axis, the second actuator being configured to be movable along with the intermediate unit with respect to the at least one base unit.

A vehicle for travelling on a road and in the air is provided, comprising a fuselage extending from a forward to a rear end along a horizontal longitudinal roll axis, a pair of main wings mounted on the rear end of the fuselage, a pair of canard wings mounted to the fuselage forward of the main wings, a plurality of wheels configured to facilitate travelling on the road, and a rotor system comprising a plurality of rotors. Each of the main and canard wings extend from the fuselage in deployed positions, and are configured to be shifted to a stowed position in which it overlies the fuselage. The rotor system comprises a pair of tiltable main rotors mounted a main wing and configured to tilt through a plurality of positions between a forward position parallel with the roll axis, and an upward position parallel with the yaw axis.

The invention provides a trigger type folding-stretching linkage wing structure for a seaplane. The trigger type folding-stretching linkage wing structure comprises a wing assembly, a driving assembly, a linkage assembly and a limiting assembly. The wing assembly comprises a wing seat, two wing groups and two guide units, the wing groups can stretch out and draw back, the two ends of each wing group are connected with an inner connecting plate and an outer connecting plate correspondingly, and the inner connecting plates are rotationally installed on the wing seat; the guide unit comprises a telescopic rod and a reset spring, the two ends of the telescopic rod are connected with the inner connecting plate and the outer connecting plate correspondingly, and the telescopic rod is sleeved with the reset spring. The driving assembly comprises a first sliding block and a connecting rod; two ends of the connecting rod are respectively hinged with the first slide block and one end of the wing group close to the wing seat; the linkage assembly comprises a traction rope and a pulley block; the limiting assembly comprises a first limiting unit and a second limiting unit. The first sliding block moves in the direction away from the wing base, sweepback and contraction of the wing set are synchronously achieved, the cross sectional area and the wetted area of the wing can be reduced at the same time during underwater navigation, and fluid resistance is remarkably reduced.

A wing-fuselage truss joint assembly for an aircraft includes joining members secured to the aircraft's wing and fuselage structures. The joining members each include forward and aft wing joints and forward and aft fuselage joints connected by an upright member. The forward joining members are pivotally connected using interconnecting members and the aft joining members are connected using aft truss members. The forward-right and aft-right joining members and the forward-left and aft-left joining members are connected by truss link members and diagonal truss link members. The wing-fuselage truss joint assembly is configured to reduce forces experienced by the wing from being transferred to the aircraft fuselage.

A flying vehicle with folding wings that drives well on the ground and flies well in the air; controlled from inside, it changes from automotive to aircraft configuration without the operator needing to get out of the vehicle. The balance point of the vehicle is located midway between the front and back wheels, providing good handling on the road. In the aircraft configuration with wings unfolded, there is a front wing and a back wing. The incidence of the front wing is controllable, enabling the craft to rotate and take off with a center of gravity located well ahead of the rear wheels. The back wing is fitted with foldable vertical stabilizers near its wing tips. In automobile configuration the wings are folded on top of the body; the wings resemble a roof rack with large surfboards on it. Driven wheels provide motive power on the ground; ducted fans provide thrust for air travel. An autopilot system provides stability and navigation aid, particularly in bad weather or poor visibility. In the roadable configuration, filling water ballast tanks provides additional crosswind stability and crash protection. Also in a roadable configuration, the present invention may be licensed as a three-wheeled motorcycle towing a two-wheeled trailer. In its flying configuration, the invention can be licensed as a Light Sport Aircraft.

An apparatus for deploying the wings of a movable-wing aircraft includes a spherical four-bar mechanism. The spherical four-bar mechanism has a first bar to which a first wing is attached, a second bar to which a second wing is attached, a third, movable bar rotatably or movably linking the first bar to the second bar at a first respective point on each bar, and a fourth bar grounding the first and second bar at a second respective point on each bar. The spherical four-bar mechanism may be mathematically optimized for space, size, and movement by a system of kinematic equations to allow the first and second wing to open at substantially the same time without colliding with one another. The wings of the aircraft may further include a mid-wing hinge with a movable stiffening spar to allow the wings to fold to a more compact size during storage.

A convertiplane (1) is described, which comprises a fuselage (2) extending along a first axis (A), a pair of half-wings (3) projecting cantilevered from respective sides of the fuselage (2), a pair of nacelles (4) housing respective engines and operatively connected to the half-wings (3); and a pair of rotors (5) associated with the half-wings (3), rotatable around respective second axes (B) and tiltable so as to arrange the convertiplane (1) in an airplane configuration or in a helicopter configuration. Each half-wing (3) further comprises a wingbox (20) and an appendage (21) articulated on the wingbox (20) and selectively movable between a relative first neutral operating position taken when the convertiplane (1) is in the airplane configuration and in which it defines an extension of the wingbox (20) and a relative second position taken when the convertiplane (1) is in the helicopter configuration and in which it defines with the wingbox (20) a compartment (50) through which the air flow generated by the respective rotor (5) can pass. The convertiplane (1) comprises a closing system (60) configured to elastically preload each appendage (21) towards the respective first neutral operating position.

An aircraft including an aircraft wing wherein the aircraft wing includes a fixed wing, a wing tip device at an end of the fixed wing, and a wing tip device actuator configured to move the wing tip device between a flight configuration and a ground configuration. The wing tip device actuator includes a shaft which is rotatable about a shaft axis to selectively displace respective first and second elbows of the wing tip device actuator towards or away from the shaft. The first elbow is connected to the wing tip device and the second elbow is connected to the fixed wing such that movement of the respective elbows away from the shaft causes the wing tip device to move away from the flight configuration and such that movement of the respective elbows towards the shaft causes the wing tip device to move towards the flight configuration.

A wing assembly for an aircraft is disclosed having an actuation assembly configured to move a wing tip device between a flight configuration and a ground configuration. The actuation assembly includes at least two linear actuation devices mounted within the wing assembly. A wing and a wing tip device for the wing assembly, and an aircraft comprising the wing assembly, wing or wing tip, are also disclosed.

A wing assembly for an aircraft, the wing assembly having a fixed wing and a wing tip device moveably mounted at the end of the fixed wing. A wiring harness extends between the fixed wing and the wing tip device, a length of the wiring harness being encased in a length of protective sleeve. The protective sleeve is pre-shaped, for example pre-molded, to follow a path along a helical curve.

The present invention provides an extreme STOL airplane comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with top and bottom surfaces, leading and trailing edges, and a span, i.e., the distance between a wing section tip and root connected to the fuselage, and flap coves. Aerodynamic elements integrated into the wing sections include Fowler flaps, having leading and trailing edges and a span, flap tracks, wherein the flap tracks are external to the wing section body, extend aftward beyond the trailing edge of the wing section, and are configured to enable the Fowler flaps to rotate or deflect and to translate or extend and retract, Frise ailerons, wherein the Frise ailerons are located outboard of the Fowler flaps, and spoilerons located over the leading edge of the Fowler flaps when the flaps are in the fully extended position.