57 results about "Morphing wing" patented technology

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.

The invention belongs to the technical field of numerical simulation and analysis of unmanned aerial vehicles, and relates to a rigid-flexible coupled variable-camber-range deformable wing optimization design method, which comprises the following steps of: obtaining working conditions of an aircraft, determining wing types and basic parameters of wings of the aircraft, and establishing a three-dimensional aerodynamic model of the wings; variable-attack-angle pneumatic simulation is carried out on working conditions of the aircraft in take-off and cruise, optimal camber values and corresponding pneumatic loads of wings under multiple working conditions are determined, and the positions of rotating joints of the deformed wing ribs are adjusted to obtain the deformed wing ribs after primary optimization; dividing the optimization range of the deformed wing rib after primary optimization into a fixed area and an optimizable area, loading an aerodynamic load under the optimal camber value in the optimizable area to perform aerodynamic simulation to obtain a deformed wing rib after secondary optimization, and optimizing the structure; and a deformed wing rib sample is made, performance testing is conducted, and the optimizable area is adjusted till the wing performance meets the preset requirement. The aerodynamic efficiency of the full flight envelope can be improved.

The invention discloses a semi-physical simulation system and method for an aircraft with variable wings, and belongs to the technical field of semi-physical simulation of variant aircrafts. The method comprises the steps that a PC upper computer builds a model and monitors the process; the real-time simulation computer is connected with all the devices through the optical fiber reflection memory network and executes trajectory calculation, pneumatic processing, airfoil profile reconstruction and deformation control strategy generation. The three-axis servo turntable loads inertial navigation equipment and tracks pose information; the wind tunnel applies an aerodynamic load to the deformed wing; the STM32 driving system realizes multi-stage motor cooperative control; the measuring system acquires deformation data in real time through a laser displacement sensor, a strain gauge array and a coding disc; the flight control system generates a rudder control and deformation instruction; and the annular cascade optical fiber network realizes multi-protocol conversion. Physical deformation wings are integrated into semi-physical simulation, collaborative testing of flight control, deformation control and an aircraft body structure is achieved, deformation interference resistance and flight safety research are supported, and a foundation is laid for optimization and test flight of the wing-variable-bending aircraft.

The invention discloses a deformable empennage applied to a bionic aircraft, and relates to the technical field of bionic flying robots. Through efficient cooperation of five-degree-of-freedom motion of the empennage and deformation motion of the wings, the maneuverability and adaptability of the aircraft are remarkably improved. The bionic aircraft comprises a motor, a fuselage, a deformation wing, an empennage and an empennage deformation driving mechanism. And flexible switching among a horizontal tail state, a positive V tail state and an inverted V tail state can be realized. When the state is switched to the positive V tail state, parasitic resistance can be effectively reduced, wingtip vortex interference is reduced, and the aerodynamic efficiency of the cruising stage is improved; when the inverted V-tail state is switched, the influence of wing wake flow can be avoided, the aerodynamic stability is obviously enhanced under the working condition of a large angle of attack, and the stall risk is effectively inhibited; and when the horizontal tail state is switched, aerodynamic lift force distribution in the low-speed stage can be optimized, and the aerodynamic response of take-off and landing control is improved. The flexible switching of the empennage among the three states provides better pneumatic suitability for the aircraft in different flight stages and task scenes.

The invention provides a structural design and dynamic simulation method of a wheel-track type variant telescopic wing. The structural design comprises a base; the fixed wings are symmetrically arranged on the base; the movable wing is provided with a walking wheel set, and the movable wing is used for moving along the fixed wing through the walking wheel set; the driving and transmission mechanism assembly is used for driving the movable wing to stretch out and draw back relative to the fixed wing, and the driving and transmission mechanism assembly is connected with the movable wing; the lift force area is changed through stretching and retracting of the movable wing relative to the fixed wing, so that the limitation of a traditional fixed-configuration wing is overcome, the display ratio and the lift force area of the wing are changed, and the multi-working-condition adaptation capacity of the aircraft is greatly improved.

The application discloses a flexible metal composite skin structure capable of regulating local out-of-plane deformation and belongs to the technical field of metal skin structures. The application introduces a paper-cut structure on the surface of a metal skin, regulates mechanical response by changing characteristic parameters such as a paper-cut pattern and a metal skin thickness, so that the structure has high ductility and small plastic deformation characteristics, and the structure can recover to original deformation after the expansion of a protrusion of a driving device, thereby ensuring the continuity of a wing aerodynamic shape. The application meets the basic requirements of application to a flexible skin of a deformation wing, provides a feasible selection for the fusion of a gasbag anti-icing mechanism and a deformation wing, and is expected to be widely applied in the fields of aircraft deicing, spacecraft deicing and deformation wings.

The invention discloses a flexible metal composite material skin structure capable of regulating and controlling local out-of-plane deformation, and belongs to the technical field of metal skin structures. The paper-cut structure is introduced to the surface of the metal skin, the mechanical response of the paper-cut structure is regulated and controlled by changing characteristic parameters such as a paper-cut pattern and the thickness of the metal skin, so that the structure has the characteristics of high ductility and small plastic deformation, and the structure can recover to original deformation along with retraction of the driving device after expanding and protruding along with the driving device; and the aerodynamic configuration continuity of the wing is ensured. Basic requirements of flexible skin applied to the deformable wing are met, a feasible choice is provided for fusion of an air bag anti-icing and deicing mechanism and the deformable wing, and the method is expected to be widely applied to the fields of aviation, spacecraft deicing, deformable wings and the like.

The invention provides a smooth variable-sweepback wing based on an elastic rotation assembly and a variable-wing aircraft, belongs to the field of aerospace equipment, and solves the problems of low actuation driving efficiency, motion clamping stagnation and the like of the existing variable-sweepback wing at present. Wherein the supporting seat is fixedly arranged on the inner wing; the outer wing penetrates through the inner wing; the driving structure is arranged on the inner wing; the elastic variable sweepback structure comprises a plurality of first elastic rotation structures, the first ends of the first elastic rotation structures are fixedly arranged on the supporting base, the second ends of the first elastic rotation structures are connected with the outer wings, and the second ends of the first elastic rotation structures are further connected with the driving structure through first connecting ropes. The driving structure can pull the second end of the first elastic rotary structure to move through the first connecting rope so as to drive the outer wing to rotate relative to the inner wing; one side of the shape-maintaining structure is fixedly connected with the inner wing, and the other side of the shape-maintaining structure is elastically lapped on the outer surface of the outer wing. The smooth continuous deformation capacity of the variable sweepback wing can be achieved, clamping stagnation is avoided in the movement process, and the actuation driving efficiency is high.

The invention discloses a folding mechanical mechanism and a folding device and method of an intelligent morphing wing. The folding mechanical mechanism is composed of a folding wing fixing seat, a main wing fixing seat, an electric driving assembly and a wing lower eccentric shaft. The folding wing fixing seat is used for transmitting an aerodynamic force load of the outer-section folding wing to the main wing fixing seat; the main wing fixing seat is used for bearing an aerodynamic force load transmitted by the outer-section folding wing; the wing lower eccentric shaft is connected with the folding wing fixing seat and the main wing fixing seat; the electric driving assembly is used for driving the unfolding and folding states of the outer-section folding wing and comprises an electric driver, a limiting movable shaft, a thrust rod and a movement thrust shaft. According to the scheme, the folding angle and the unfolding function of the wings can be accurately adjusted and controlled in the flight stage of the unmanned aerial vehicle, optimal control folding system control parameters can be autonomously calculated and loaded according to mechanical energy and the model state, autonomous adjustment of the wing shapes in the flight process is met, and the flexibility and adaptability of the unmanned aerial vehicle are improved.

The invention relates to the technical field of aerodynamics, in particular to a precise regulation and control method for unsteady aerodynamic force of a continuously and rapidly deformed wing, and the method comprises the following steps: simulating the wing under various working conditions by using CFD software, and collecting simulation results to construct a working condition data set; performing double-model cooperative training on the ARX model and the PI hysteresis model based on the working condition data set; inputting the target lift coefficient into the trained PI inverse model to obtain a corrected deflection angle; and correcting the corrected deflection angle through an ARX model to obtain a final corrected deflection angle.

The application provides a deformable wing using a telescopic connecting rod mechanism, comprising: a plurality of frames; a plurality of connecting rod mechanisms, each of which is arranged on a frame, each of which comprises a telescopic first connecting rod, a non-telescopic second connecting rod and a connecting rod for connecting the first connecting rod and the second connecting rod; and a plurality of driving devices, each of which has a frame on the upper side and the lower side respectively, and each of which is connected with the first connecting rod in the two corresponding connecting rod mechanisms, so as to control the two first connecting rods to synchronously stretch and retract. The application can realize the length adjustment of the aircraft wing in the wing profile section direction, so as to change the wing profile area and the angle of attack, thereby enabling the aircraft to adjust the lift-drag ratio by controlling the movement of the four connecting rod mechanisms to adjust the wing area and the angle of attack when the lift needs to be adjusted. The application has the advantages of simple structure, stable control, high safety factor and the like.

This invention relates to an integrated variable camber wing based on a piezoelectric-driven torsional cubic superstructure, comprising a wing skeleton and a skin. The wing skeleton includes multiple torsional cubic superstructures arrayed along the wing chord direction. Each torsional cubic superstructure is a cube formed by an array of multiple unit-cell torsional superstructures. Adjacent unit-cell torsional superstructures in the wing length and thickness directions share a straight rod, while adjacent unit-cell torsional superstructures in the wing width direction share four Z-shaped piezoelectric rods. Each unit-cell torsional superstructure is a cube formed by an array of four cell units, with adjacent cell units sharing a straight rod. Each cell unit includes Z-shaped piezoelectric rods and straight rods. Two Z-shaped piezoelectric rods are connected to the two ends of two straight rods. Each Z-shaped piezoelectric rod at both ends of the torsional cubic superstructure is connected to the skin. When all the Z-shaped piezoelectric rods of the unit-cell torsional superstructure undergo compressive deformation in the height direction, the unit-cell torsional superstructure undergoes torsional deformation, thus causing the torsional cubic superstructure to undergo torsional deformation. By converting the compressive deformation of the cellular unit into the torsional deformation of the compressive-torsional cubic superstructure, the wing camber is changed, and the drive components are eliminated, thus realizing the lightweight design of the morphing wing.

The application discloses a morphing aircraft wing shape sensing and control method and system, and belongs to the technical field of aircraft flight detection and control. The actual angle of the wing and the state quantity of the sweepback angle and the span of the wing are determined. When the error between the actual angle of the wing and the required angle exceeds the preset error threshold, the motion state of the feature point is predicted through Kalman filtering, the sweepback angle and the span of the wing are updated to obtain the change quantity of the sweepback angle and the span, and the state quantity is time-stamped and synchronized, and then multi-source information fusion is performed to obtain the state estimation value of the sweepback angle and the span. The state estimation value, the current flight attitude information of the aircraft and the error between the actual angle of the wing and the required angle are used as the input of the controller to adaptively adjust the sweepback angle and the span until the error between the actual angle of the wing and the required angle meets the error threshold. The method can improve the accuracy and robustness of dynamic deformation monitoring and control of the morphing wing.

The application discloses a kind of torsion wing structure and aircraft, it is related to the field of morphing wing technology, including linear drive device, wing rib and pressure-torsion coupling cell, wing rib and pressure-torsion coupling cell are multiple, multiple wing ribs are arranged along the wing span direction interval, and pressure-torsion coupling cell is equipped between two adjacent wing ribs;Pressure-torsion coupling cell includes intermediate connecting component and the load-bearing end block fixedly connected with the two ends of intermediate connecting component, load-bearing end block is fixedly connected with adjacent wing rib, and all wing ribs and pressure-torsion coupling cell form wing main body;The first end wing rib of wing main body is used to be fixedly connected with fuselage;Two load-bearing end blocks of pressure-torsion coupling cell are connected with linear drive device;Linear drive device can make the two load-bearing end blocks of each pressure-torsion coupling cell approach each other or away from each other, to make intermediate connecting component torsion deformation and drive wing rib around wing span torsion by load-bearing end block.The application has the effect of "lightweight-structure simplification-aerodynamic efficiency-high life-low maintenance cost".

A fixed-wing aircraft (10) includes: a fuselage (14), a closed wing (16), a first actuator device (22), and a first connector device (24). The closed wing (16) is coupled to the fuselage (14) and has a wingtip (18) and a first deformable wing portion (20). The first actuator device (22) is arranged to supply a first input torque to the first connector device (24) when the first actuator device (22) is actuated, and the first connector device (24) is arranged to apply a first output torque to the first deformable wing portion (20) when the first input torque is supplied to the connector device. The first deformable wing portion (20) is arranged to elastically deform when the first output torque is applied to the first deformable wing portion (20). The closed wing (16) forms an outer support (26) at the wingtip (18), which is arranged to counteract the first output torque.

The invention relates to the technical field of computer simulation, and discloses a rapid modeling simulation method and system for a deformed wing structure, and the method comprises the steps: recognizing wing section key points of wing section data, fitting an upper surface curve and a lower surface curve of the deformed wing structure, and determining a parameterized wing section of the deformed wing structure; analyzing key change parameters, corresponding to the wingspan direction, of the deformed wing structure so as to construct a parameter change curve in the wingspan direction, and fitting a wing geometric model of the deformed wing structure; determining a deformation mode of the deformed wing structure, calculating an airfoil variable quantity and a torsion angle variable quantity of the deformed wing structure in a deformation process, and fitting an initial deformed wing model of the deformed wing structure; carrying out simulation calculation on an aerodynamic coefficient of the initial deformation wing model, and determining aerodynamic performance of the initial deformation wing model; and optimizing the initial deformation wing model to obtain a target deformation wing model. According to the method, the modeling simulation accuracy and design efficiency of the deformed wing structure can be improved.

The application discloses a dynamic variable-wing bionic aircraft, which comprises a fuselage assembly, a speed reduction mechanism, a wing assembly, a wing vein driving assembly, a tail wing assembly, a receiver and a battery, the fuselage assembly comprises a nose and a fuselage plate, the nose is connected with the fuselage plate to form a nose cavity, and the fuselage plate is provided with a fuselage cavity, a first groove and a second groove; the wing assembly is arranged on the fuselage plate; the speed reduction mechanism is arranged in the nose cavity and is used for driving the wing assembly to flap up and down; the wing vein driving assembly is arranged in the first groove of the fuselage plate and is used for driving the wing assembly to move horizontally and longitudinally; the tail wing assembly is arranged at the tail of the fuselage plate and can flip up and down; the receiver is arranged in the fuselage cavity of the fuselage plate; and the battery is arranged in the second groove of the fuselage plate. The dynamic variable-wing bionic aircraft can adjust the structural state of the wing in the process of flight, and can adjust the shape of the wing in real time to achieve the best flight state.

The application provides a dynamic simulation method for a wheel-rail variable telescopic wing structure design. The structure suitable for the dynamic simulation method comprises a base, fixed wings symmetrically arranged on the base, a movable wing provided with a wheel set, the movable wing being used to move along the fixed wings through the wheel set, a driving and transmission mechanism assembly used to drive the movable wing to extend and retract relative to the fixed wings, and the driving and transmission mechanism assembly being connected with the movable wing. The change of the lift area is realized through the extension and retraction of the movable wing relative to the fixed wings, so that the limitations of the traditional fixed configuration wing are overcome, the aspect ratio of the wing and the change of the lift area are realized, and the multi-working condition adaptation capability of the aircraft is greatly improved.

The invention discloses a distributed thermoelectric element variant wing SMA driver and method and application, the SMA driver comprises an active cooling layer, an SMA wire driving structure and an elastic supporting layer which are sequentially arranged from top to bottom, each layer is embedded in a flexible material in a sealed mode, the active cooling layer is composed of a plurality of thermoelectric elements arranged in an array mode, and the elastic supporting layer is embedded in the active cooling layer. The thermoelectric element achieves refrigeration of the SMA wire driving structure through the Peltier effect. The cooling efficiency can be remarkably improved, heat accumulation is eliminated, the recovery time of the driver is shortened, the driving frequency is improved, and the service life of the shape memory alloy driver is prolonged. According to the algorithm, an adaptive thermoelectric element layout scheme can be automatically generated in combination with the structural characteristics of the driver, so that heat transfer is accelerated, the uniformity of a temperature field is improved, the application requirements under multiple working conditions and complex environments are met, the algorithm has good universality, the integration requirements of different types of wings are met, and the application prospect is wide. The design process is effectively simplified, and the manufacturing cost is reduced.

The invention belongs to the technical field of unmanned aerial vehicles, solves the problems of poor stability, complex deformation structure and incapability of adjusting sweepback of a deformable wing in the prior art, and provides a deformable wing based on a flexible skin, which comprises a fixed wing rib, a movable wing rib, the flexible skin, a shear fork frame, a telescopic pipe and a reciprocating driving piece, the movable wing rib is located on the outer side of the fixed wing rib, and the flexible skin wraps the fixed wing rib and the movable wing rib; every two adjacent movable wing ribs as well as the fixed wing ribs and the movable wing ribs are connected through shear fork frames and telescopic pipes; the reciprocating driving piece is arranged between the fuselage and the fixed wing rib; the inner side end of the shear fork frame is connected with the reciprocating type driving piece, and when the reciprocating type driving piece moves towards the inner side, the shear fork frame enables the movable wing ribs to be unfolded; after the shear fork frame is unfolded, the reciprocating type driving piece moves inwards to enable the outer side end of the shear fork frame to swing backwards. The wings can be unfolded and folded, the sweepback angle can be adjusted, the structure is simple, and the stability is high.

The invention discloses a wing shape sensing and control method and system for a morphing aircraft, and belongs to the technical field of aircraft flight detection and control. When the error between the actual angle of the wing and the required angle exceeds a preset error threshold value, predicting the motion state of the feature points through Kalman filtering, updating the feature points to obtain the variable quantity of the sweepback angle and the span of the wing, performing timestamp and synchronization processing on the variable quantity and the state quantity, and performing multi-source information fusion to obtain the wing. State estimation values of the sweepback and the span of the wing are obtained; and taking the state estimation value, the current flight attitude information of the aircraft and the error between the actual angle of the wing and the required angle as the input of a controller, and carrying out self-adaptive adjustment on the sweepback angle and the elongation until the error between the actual angle of the wing and the required angle meets an error threshold value. According to the method, the precision and robustness of dynamic deformation monitoring and control of the morphing wing can be improved.

This invention belongs to the field of variable wing technology and discloses a lightweight integrated aerodynamic drive system and a deformable wing. The aerodynamic drive system includes: a double-acting cylinder integrated with the valve bodies of a normally open and normally closed electromagnetic directional valve via a cylinder head; a combined valve comprising an inflation valve and a pressure reducing valve; the inflation valve is located above the pressure reducing valve, with its valve body integrated with the pressure reducing valve's valve body, and its outlet flow channel directly connected to the pressure reducing valve's inlet flow channel; the pressure reducing valve is located on the top of the front cylinder head of the double-acting cylinder, and is connected to the normally open electromagnetic directional valve via a gas-sealed connection, directly docking with a gas cylinder. This system combines optimized gas path design and hardware integration, integrating energy and drive functions, resulting in a compact and lightweight structure. It can adapt well to the requirements of limited installation space, significantly improving the system's adaptability to various operating conditions, thereby enhancing the aircraft's flight performance.

The present application relates to the technical field of aerospace equipment, in particular to a smooth continuous repeatable telescopic variable-camber multi-dimensional deformation wing and a working method thereof, the deformation wing comprising: a fixed wing and a telescopic wing, the telescopic wing being arranged inside the fixed wing and being provided with a driving assembly on the fixed wing, the driving assembly being connected with the telescopic wing; a variable-camber wing, the root of the variable-camber wing being connected with the telescopic wing, the variable-camber wing comprising a variable-camber wing skin, a crank slider mechanism, a knuckle bionic mechanism, a variable-camber transmission mechanism and a passive slider; the variable-camber wing skin is connected with the telescopic wing, the variable-camber transmission mechanism is arranged in the telescopic wing and is connected with the driving assembly, and the crank slider mechanism is arranged in the variable-camber wing skin. The rigidity and load-carrying capacity of the deformation wing are improved; compared with another form of folding wing of out-of-plane deformation, the problem that the folding wing surface cannot be smoothly and continuously variable-cambered is avoided.

This invention discloses a bird-inspired wing-shaped deformable aircraft that can move across media. Using birds such as pelicans, which possess transmedia capabilities, as biomimetic prototypes, and based on research into their water-entry and exiting behaviors and morphological characteristics, an innovative structural design scheme for a biomimetic deformable wing aircraft is proposed. Based on the biomechanical mechanisms of multi-joint linkage in bird skeletons and the hydrophobic properties of feathers, the aircraft employs a deformable wing and tail design; combined with lightweight materials and a multi-degree-of-freedom actuation strategy, it achieves efficient coordination between dynamic morphological switching and transmedia motion.

The invention belongs to the technical field of six-rotor unmanned aerial vehicles, and relates to a six-rotor unmanned aerial vehicle with self-adaptive bionic deformation wings, the six-rotor unmanned aerial vehicle comprises a fuselage, the fuselage is formed by mounting and buckling an upper cover and a lower cover through bolts, a rotating device is mounted in the fuselage, and the rotating device comprises a thrust ball bearing mounted in the upper cover; and the lower part of the thrust ball bearing is fixedly connected with a rotating fluted disc. Through collaborative design of the rotating device and the telescopic device, self-adaptive adjustment of the angles and lengths of the wings is achieved, the adaptability of the unmanned aerial vehicle to complex scenes is greatly improved, a servo motor in the rotating device drives a rotating fluted disc, bevel gears subjected to carburizing and quenching treatment are matched, and the angles of the six wings can be accurately and synchronously adjusted; the telescopic device is linked with the sleeve rod through the driving screw rod, so that the wingspan length can be flexibly changed, the wingspan is prolonged during high-speed cruising to improve the lift efficiency, the wingspan is shortened in a narrow space to enhance the flexibility, the angle is adjusted to reduce the wind resistance during headwind, and the problem that a traditional fixed wing is poor in adaptability is solved.

The invention belongs to the field of bionic deformation wing design, and relates to a three-section collaborative deformation high bionic wing. The bionic deformation wing is mainly composed of a driving assembly, an upper arm section, a front arm section and a hand wing section. The whole mechanism only has one degree of freedom and is driven by a servo motor, a deformation mechanism composed of three parallelogram fence type structures and a wingtip fan-shaped structure is pulled through a gear and a rack, and cooperative deformation of the three bionic wing sections is achieved. Cooperative movement of three joints of the shoulder, the elbow and the wrist of the bird wing is simulated, the wing is stretched and folded like the bird wing, the wing area change is large, transverse control over the unmanned aerial vehicle can be carried out instead of an aileron, and the overall bionic degree is high.

The application relates to the technical field of aircraft wing design, in particular to a variable wing of an aircraft, which comprises a leading edge, a wing body and a trailing edge connected in sequence, the wing body comprises a plurality of single cell structures, two adjacent single cell structures are connected to each other, each single cell structure comprises a chiral structure and a zero Poisson ratio structure connected to each other; all the chiral structures are arranged on a transverse section of the variable wing, each chiral structure has a tensile rotation characteristic, so that the variable wing changes the camber when subjected to tensile and compressive loads; all the zero Poisson ratio structures are arranged on a longitudinal section of the variable wing, each zero Poisson ratio structure has a tensile deformation characteristic, so that the variable wing changes the span when subjected to tensile and compressive loads. The scheme can solve the problems of small adjustable range and discontinuous shape change in the related art.

The application discloses a kind of multi-stable flexible deformation wing based on tension mechanism, including wing main body and deformation main body;Deformation main body includes two airfoil frames and multiple tension mechanisms sequentially arranged between two airfoil frames;Tension mechanism has spatial configuration and plane configuration, it includes a pair of deformable support components and driving rope components, the pair of support components presents plane cross structure when tension mechanism is in plane configuration, and presents spatial octahedron structure when tension mechanism is in spatial configuration;Support component includes two identical support rod members, two identical follow-up connecting plates and at least one spring;Two support rod members can be switched between V-shaped and linear under the driving of rope component;Support rod member has first end and second end, the first end of two support rod members mutually abuts and forms rolling joint.The application has the advantages of light weight, deployable and self-balancing.

The invention discloses a morphing wing capable of actively regulating and controlling chord length and thickness. The morphing wing comprises a front edge section, a wing body, a telescopic driving part, a rear edge section and a skin, the wing body is connected with the front edge section and the rear edge section, and the multiple telescopic driving pieces are embedded in the wing body; the wing body comprises a plurality of wing body units arrayed in the extension direction, each wing body unit is formed by arraying a plurality of anisotropic cubic superstructures in the chord length direction, the thickness direction and the extension direction, and inclined protrusions of special-shaped connecting pieces at the corresponding vertex positions of adjacent cubic cell elements of the adjacent anisotropic cubic superstructures in the chord length direction and the thickness direction are connected. The special-shaped connecting pieces at the corresponding vertex positions of the adjacent cubic cells of the adjacent anisotropic cubic superstructures in the extension direction are combined to form a cross-cell special-shaped connecting piece, and the wing body has the negative Poisson's ratio characteristic in the chord length and thickness directions and has the zero Poisson's ratio characteristic in the extension direction. The wing can stretch out and draw back in the chord length direction and the thickness direction at the same time, the stretching length is kept unchanged, and the diversified application requirements of the aircraft are met.