57 results about "Morphing wing" patented technology

An airfoil member (14) is provided including a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. A fiber mesh (34) is coupled to at least a portion of the exterior wall (32) and changes in shape according to fiber angle. Shape and size of the geometric morphing device (18) are adjustable by changing inflated state of the inflatable member (30). An airfoil member altering system (12) and a method of performing the same are also provided as well as a method of forming the geometric morphing device (18).

The invention relates to a self-adapting morphing trailing edge based on SMA, belonging to a self-adapting morphing wing which combines intellectual materials and structures. The wing is divided into 2-5 trailing edge segments, the adjacent trailing edge segments are connected by joints (5, 6 and 7) arranged at wing ribs, a deflection driving mechanism is arranged between the adjacent trailing edge segments, and the deflection of the entire trailing edge is realized by accumulative effects of the trailing edge segments. The self-adapting morphing wing is characterized in that the deflection driving mechanism comprises an upper SMA wire (10), a lower SMA wire (11) and a current excitation unit (15) which are respectively connected with the adjacent trailing edge segments. The self-adapting morphing trailing edge has the advantages of simple structure and easy control and achieves the goal of quick, stable and accurate pre-deformation of the trailing edge.

The invention discloses a skin for morphing wings, belonging to the technical field of design of morphing aircrafts. The skin for the morphing wings is made from fibre reinforced composites, and the cross section of the skin is in an isosceles trapezoid ripple structure. The invention also carries out analysis aiming at the chordwise and spanwise equivalent elastic modulus and flexural modulus ofthe skin structure with isosceles trapezoid ripples, provides a corresponding mathematical model and can further optimize the skin structure according to the mathematical model. The invention meets the requirements of the skin of the morphing wings of the morphing aircrafts for large deformation aerodynamic load bearing, can realize the design optimization of the skin structure under different load operating conditions according to the mathematical analysis model of the equivalent elastic modulus and the flexural modulus in two different directions of the skin structure, also has structure health monitoring and self-adapting deformation capability and can realize optimal aerodynamic characteristics by controlling the shape and the vibration of the skin.

An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.

The invention provides a skin of a morphing wing, which is made from fiber-reinforced composite material (1). The skin is characterized in that: a shape memory alloy driver (2) is arranged between the two layers of the fiber-reinforced composite material (1); the wave trough of the upper layer fiber-reinforced composite material is internally filled with silica-based rubber (3) for meeting the requirements of smoothness, continuity and whole gas tightness on the surface of the wing; the fiber-reinforced composite material (1) and the shape memory alloy driver (2) are jointly pressed into to a corrugated structure under room temperature; the shape memory alloy driver (2) is in the shape of a high-temperature memory straight line; and the silica-based rubber (3) can be solidified under normal temperature. The invention also provides a drive method of the skin of the morphing wing. The skin of the morphing wing has the corrugated structure, thereby having high flexibility, large morphing amount and fast morphing response speed on the morphing direction, having high carrying capability on the perpendicular morphing direction, and having simple structure, light weight and reliable performance.

The invention discloses a bionic morphing wing of a water-air amphibious aircraft and a diving control method of the bionic morphing wing. The bionic morphing wing of the water-air amphibious aircraft comprises a primary wing body, a secondary wing body, a primary controllable telescopic mechanism, a secondary controllable telescopic mechanism, a controllable rotating mechanism, folding skin, a fuselage and a control and driving system in the fuselage. One end of the leading edge of the primary wing body is connected with the controllable rotating mechanism through a hinge, and the other end of the leading edge of the primary wing body is connected with the secondary wing body through a hinge. One end of the primary controllable telescopic mechanism is fixed in the primary wing body, and the other end of the primary controllable telescopic mechanism is installed in a slideway on the surface of the controllable rotating mechanism through a pin. One end of the secondary controllable telescopic mechanism is fixed in the primary wing body, and the other end of the secondary controllable telescopic mechanism is installed in a slideway on the end face of the secondary wing body through a pin. The wing surface of the primary wing body and the wing surface of the secondary wing body are sewn through the folding skin, and the wing surface of the primary wing body and the fuselage are also sewn through the folding skin. The bionic morphing wing of the water-air amphibious aircraft and the diving control method of the bionic morphing wing can meet the requirements for conventional flying in air and rapid pitch-down diving of trans-medium aircrafts, and the effects that the diving process of the aircraft is stable and the water resistance and impact are reduced are guaranteed.

An airfoil member (14) includes a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. The exterior wall (32) includes a layer with one or more fibers embedded therein. The exterior wall (32) controls size, shape, and expansion ability of the geometric morphing device (18).

The invention discloses a transmission mechanism of telescopic morphing wing, which comprises a speed reducing motor, a steel cable, a winch and a pulley and is characterized in that: the speed reducing motor drives the winch to unwind and wind the steel cable wound on the winch; a telescopic section of the wing, the steel cable, the winch and the pulley are embedded in a main wing; the pulley is positioned at the tail end of a girder under a wing face skin on the wing tip of the main wing; and steel cable controls the telescopic change of the telescopic section of the wing in real time through the pulley. The transmission mechanism of the telescopic morphing wing has the advantages of simple structure, light weight, safety, reliability and the like, can relatively better meet the requirements on the structure of an aerocraft, takes efficiency and weight into account and fulfils the aim of the telescopic change of the wing.

The invention provides a morphing wing trailing edge driven based on shape memory alloy and a deflection method thereof. The trailing edge is partially wound on an insulating rod by utilizing an SMA wire; through heating the SMA wire, the rotation of the insulating rod is realized by utilizing the shape memory effect of the SMA wire; the insulating rod is connected with a worm, so that a traditional motor is replaced for driving; a trailing edge flap is divided into two parts: an upper part and a lower part; according to the deflection method provided by the invention, through the rotation of one worm, two worm wheels are simultaneously driven to rotate, so that upper and lower wing ribs simultaneously deflect from equilibrium positions to limiting positions, and through changing the transmission ratios of the worm wheels and the worm, the deflection of the upper and the lower wing ribs at different angles can be realized.

The invention relates to a drive-embedded dynamic folding morphing wing. The morphing wing comprises an inner wing, an outer wing, a fixed rotary shaft, a driven rotary shaft, an embedded inner wing rotation drive mechanism and an embedded outer wing rotation drive mechanism. The fixed rotary shaft is arranged at the junction of the inner wing with an airplane body, the driven rotary shaft is arranged at the junction of the inner wing with the outer wing, the embedded outer wing rotation drive mechanism is mounted on the inner wing, and the embedded inner wing rotation drive mechanism is installed on the airplane body. Under the drive of the embedded inner wing rotation drive mechanism, the inner wing rotates around the fixed rotary shaft; and under the drive of the embedded outer wing rotation drive mechanism, the outer wing rotates around the driven rotary shaft, and in a folding process of the morphing wing, the inner wing and the outer wing are opposite in rotary directions, and the wing chord plane of the outer wing is parallel with the airplane body horizontal plane. The drive-embedded dynamic folding morphing wing has the advantages of being flexible in operation, stable and noise-free and capable of bearing the airload imposed on a dynamic model during the wind tunnel test.

The invention provides a wind tunnel testing device for a deformable wing with an adjustable attack angle. The wind tunnel testing device overcomes the defects that an existing wind tunnel testing device is high in use cost, inconvenient to mount, inflexible in adjustment, complex in structure and the like. The wind tunnel testing device is mechanically composed of a wind tunnel frame, angle iron,a balance platform, a force measuring sensor, a rotary disc, a shaft sleeve, a deformable wing testing wing section and the like. The attack angle of the wing CAN be adjusted more conveniently and rapidly through the rotary disc with an arc-shaped groove. An experimental data measuring and collecting part is composed of a data collecting card, an industrial personal computer, an upper computer, amonitoring machine, an A / D converter, a D / A converter, a control system, a dynamic strain gauge, a steering engine, a low-pass filter and the like, and the data collecting card, the industrial personal computer, the upper computer, the monitoring machine, the A / D converter, the D / A converter, the control system, the dynamic strain gauge, the steering engine, the low-pass filter and the like are connected through a CAN-BUS. Compared with the prior art, the mechanical device has the advantages of being easy and convenient to mount, convenient and rapid to operate, high in reliability and the like, and the data collecting technology has the advantages of being efficient in transmission, visual in result, reasonable in storage and the like.

The invention provides an installation and use method of a corrugated plate skin for a variable-camber wing. According to the invention, the defects that the skin of the existing corrugated plate variable-camber wing cannot well maintain the airfoil profile, the continuity of the skin surface cannot be ensured, the driving load is difficult to load and the like are overcome. The variable-camber wing structure is composed of a variable-camber wing, a corrugated plate structure skin and the like, and the variable-camber wing drives a corresponding movable wing section to rotate through a steering engine so as to change the camber of the wing and the attack angle of relative incoming flow. The vertical strip-shaped supports on all the wing sections are connected with the corrugated structureskin, and collapse or separation of the skin is prevented. Compared with an existing deformed wing skin technology, the installation method of the corrugated plate skin for the variable-camber wing has the advantages that the smooth aerodynamic configuration surface of the deformed wing can be better maintained, aerodynamic force is borne, and therefore mechanical maneuverability is improved, aerodynamic performance is improved, and noise is lowered.

An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.

The invention belongs to the technical field of aircraft design, and particularly relates to a morphing aircraft. The morphing aircraft comprises an aircraft body, an inner morphing wing section, an outer morphing wing section, a high-speed wing section and a morphing mechanism. The inner variable wing section is rotationally connected with the aircraft body; the wing sections are connected in a rotating mode. The inner variable wing section and the outer variable wing section form a variable wing section, and variant operation is achieved through a variant mechanism. Control surfaces are arranged on the inner variable wing section, the outer variable wing section and the high-speed wing section; the morphing aircraft provided by the invention uses a large aspect ratio at a low speed, realizes high-efficiency flight and shortens a skating distance; the aircraft is changed into an aircraft with a small aspect ratio at a high speed, resistance is reduced, the maneuverability is improved,and the high-speed and high-maneuverability target is comprehensively achieved; and the design configuration provided by the invention greatly improves the flight speed and maneuverability of the aircraft.

The invention provides a deformable wing driven based on a shape memory alloy. The deformable wing comprises a spar, ribs, a front wall, a rear wall, purlins, a flexible skin and a drive device. The drive device comprises a rigid box body, a sliding block, a conversion mechanism, a shape memory alloy wire, an air spring, a first connecting rod, a second connecting rod, a third connecting rod, a heating resistance wire and an electric insulation protective cover. According to the deformable wing driven based on the shape memory alloy, the shape of the wing is quantitatively changed through control over the temperature of the shape memory alloy wire, and the wing can obtain different lift-drag ratios. The deformable wing is simple in structure, meanwhile, through introduction of the shape memory alloy material, the shape of the wing type can be intelligently changed, and the wing type can obtain higher pneumatic performance.

The invention relates to a discrete sliding mode control method of a piezoelectric drive deformation wing. The discrete sliding mode control method comprises the following steps: (a) establishing a coupling kinetic model of piezoelectric suppression wing flutter according to a Lagrange equation; and (b) according to discrete control, sliding mode control and the coupling dynamic model, obtaining adiscrete sliding mode control law of the piezoelectric drive deformation wing, and if the input voltage is carried out according to the control law, converting the wing into a stable state from a flutter state within limited time. Numerical simulation is carried out on discrete sliding mode control. The method has the most important characteristics that a novel piezoelectric actuator is adopted,the driving strain is better, and meanwhile, the wing surface of the wing can be actively controlled, so that the weight of the wing is reduced, and the reliability of the wing is improved. In addition, a discrete sliding mode controller is designed by adopting a discrete sliding mode control method, and wing bending-torsion coupling flutter is effectively inhibited.

The invention provides a deformable wing device which comprises a fuselage central platform, a parallel driving mechanism, a transmission connecting mechanism, a left wing mechanism and a right wing mechanism, wherein the parallel driving mechanism comprises a fixed platform, a movable platform, and three driving branches connected with the fixed platform and the movable platform; the fixed platform is fixed on the fuselage central platform; the three driving branches share the same plane and are not parallel in pairs; each driving branch comprises two connecting rods which share the same line, one ends of the two connecting rods are respectively connected with the fixed platform and the movable platform by a revolute pair, and the other ends of the two connecting rods are connected with each other by a sliding pair; the transmission connecting mechanism comprises a linear guide rail, and a left sliding block and a right sliding block which are capable of sliding on the linear guide rail; the linear guide rail is fixedly connected with the movable platform; the left wing mechanism and the right wing mechanism respectively comprise a universal joint, an L-shaped transmission beam, a ball pair, a main beam and a support pillar; the short arm end of each L-shaped transmission beam is connected with the corresponding universal joint, and the universal joint is fixed on the sliding block arranged at the corresponding side; the long arm end of each L-shaped transmission beam and one end of each main beam are respectively fixedly connected with the corresponding ball pair, and the main beams and the long arms of the L-shaped transmission beams share the same line; the ball pairs are movably connected to the tops of the support pillars; the bottoms of the support pillars are fixed on the fuselage central platform.

A bionic flexible morphing wing comprises a wing framework, a wing skin, a heat insulation layer, a fixing device, a temperature control system and a connecting device; and the framework comprises a transverse framework and a longitudinal framework. The wing skin is integrally molded and bonded on the wing framework by using an adhesive. The longitudinal framework is made of a shape memory alloy;and the embedded part of the transverse framework and the longitudinal framework are heat-insulated by using the heat insulation layer. The longitudinal framework adopts the shape memory alloy; different shape memories are trained for each group of shape memory alloys; and active driving morphing after given shaping can be realized under electrothermal excitation. In the flying process, a temperature control system adjusts the temperature of the longitudinal framework, controls the two groups of shape memory alloys with different parameters to correspondingly generate upward morphing or downward morphing, and the wing is driven to morph upwards or downwards to achieve the flying purpose. According to the bionic flexible morphing wing, the wing can morph upwards or downwards under a condition without a power device, the wing structure is simplified, the weight of the wing is reduced, and the flying performance of an aircraft is improved.

The invention discloses a deformable wing based on an intelligent driving device. A framework of the deformable wing comprises a wing leading edge, a middle partition plate, a rear partition plate andan empennage which are sequentially arranged from front to back. A front shape memory alloy driving device between the wing leading edge and the middle partition plate forms a lower surface I of thewing, and the skin I covering the wing leading edge and the middle partition plate forms an upper surface I of the wing; a rear shape memory alloy driving device between the middle partition plate andthe rear partition plate forms the lower surface II of the wing, and the skin II covering the middle partition plate and the rear partition plate forms an upper surface II of the wing; the upper surfaces and the lower surfaces of the wings are in smooth transition; the deformable wing upper surface and the deformable wing lower surface are intersected at the rear edge of the empennage; and the upper surface and the lower surface of the empennage are provided with an upper piezoelectric intelligent driving device and a lower piezoelectric intelligent driving device respectively. The deformablewing has the advantages of compact structure, few driving elements, high driving capacity and continuous deformable wing surface, and can be popularized and applied to the structural design of wing camber deformation.

The invention discloses a deformable wing and a deformation method, the deformable wing comprises a fuselage and two wing parts, each wing part comprises: a first wing, which is configured with a first driving rotation joint for driving the first wing to rotate; a second wing, which is provided with a second driving rotating joint for driving the second wing to rotate relative to the first wing; and an aileron, which is provided with a third driving rotating joint for driving the aileron to rotate, wherein in the low-speed flight mode, the ailerons are folded in the fuselage, and the first wing and the second wing are unfolded and form a flight wing structure adaptive to the low-speed flight mode; and, in the high-speed flight mode, the first wing inclines backwards, the second wing rotates and inclines towards the aileron with the second driving rotating joint as the center and is connected with the aileron rotating out of the fuselage, and the first wing, the second wing and the aileron form a flight wing structure suitable for the high-speed flight mode. The unmanned aerial vehicle can flexibly adapt to occasions of high-speed flight and low-speed flight by controlling the deformation state of the wing part.

The invention belongs to the technical field of aircraft structure static tests and particularly relates to a large-deformation wing multi-point coordination follow-up loading device and method. The device comprises a position control actuator cylinder and force control actuator cylinders, wherein a plurality of loading points are arranged on a large-deformation wing, one end of the position control actuator cylinder is fixed, a pulley block fixing support is arranged at the other end of the position control actuator cylinder, a plurality of fixing supporting rods with different heights are arranged on the pulley block fixing support, guide pulleys are arranged on the fixing supporting rods, the force control actuator cylinders are multiple, one end of each force control actuator cylinderis fixed, the other end of each force control actuator cylinder is provided with a steel cable, and the steel cable is connected with a loading point of the large-deformation wing through a guide pulley. The device is advantaged in that the loading force line is ensured to be always perpendicular to a surface of a wing in the whole loading process on the premise that the installation position of the loading point is not changed, moreover, multi-point follow-up loading is realized while follow-up loading is simplified, test load applying accuracy and loading stability are ensured, a test loading error is reduced, test design difficulty is reduced, and test cost is saved.

A distributed driven overall tensioning type morphing wing device disclosed by the present invention comprises two layers of three-unit distributed tensioning overall structures, a driver, a sensor and a control computer. A control method of the morphing wing device also disclosed by the present invention concretely comprises the steps of 1 building the overall tensioning type morphing wing device; 2 establishing a non-linear dynamic model of a morphing wing; 3 establishing the first layer of control structures to enable a nominal system to track the desired shapes; 4 establishing the second layer of control structures to enable an actual morphing wing system to track the nominal system and converge to the desired shapes finally. By the control method of the two layers of control structures, the aerodynamic configuration active change of an aircraft is realized, thereby providing an effective method for improving the aerodynamic efficiency. The device is concise in structure, and the control method is strong in robustness, so that the shape tracking control of the morphing wing can be guaranteed on a condition of larger uncertainty.

The invention provides a folding mechanism suitable for a folding morphing wing. The folding mechanism has the characteristics of lower driving torque and modularization in installation and maintenance. The folding mechanism comprises a sun wheel shaft (1), a gear ring (2), a planet wheel bearing (3), a planet wheel (4), a hinge shell (5), a gear box sealing cover (6), a planet carrier shaft (7),a hinge bearing (8), an oil-proof cover (9), a planet carrier (10), a sun wheel shaft bearing (11), a dust cover (12) and an outer sleeve (13). According to the folding mechanism, a planet gear systemis adopted, torque is transmitted through a gear meshing higher pair, and the driving torque of the mechanism for achieving the folding action is reduced by utilizing the characteristic of high reduction ratio of the planet gear system. When the wing load is large, the load of each folding mechanism can be reduced in the mode that a plurality of folding mechanisms are connected in parallel. The folding mechanism has the advantages of easiness in installation, the compact structure, large torque and high adaptability and is suitable for wings of various kinds of shipboard aircraft and foldingmorphing aircraft.

The invention discloses a multi-mode conversion micro-miniature unmanned aerial vehicle which comprises a fuselage, deformable wings, a wing flapping system, a main shaft, a main shaft rotation control system and an empennage. The main shaft is vertically installed at the gravity center position of the fuselage through the main shaft rotation control system, and the deformable wings are distributed on the two sides of the top end of the main shaft and flap up and down through the wing flapping system. The empennage is mounted at the tail of the fuselage; when the deformable wings on the two sides are of a central symmetry structure, a flapping rotor wing mode is formed, and the main shaft rotates under the control of the main shaft rotation control system; the deformable wings are in an axial symmetry structure to form a flapping wing mode after being deformed, and the main shaft stops rotating under the control of the main shaft rotation control system. According to the invention, vertical take-off and landing, spot hovering and rapid take-off can be realized.

The invention provides a rigid-flexible coupling unmanned aerial vehicle morphing wing and an additive manufacturing method thereof. A shape memory alloy strip / wire for controlling a wing to be morphed upwards and a shape memory alloy strip / wire for controlling the wing to be morphed downwards are arranged in a crossed and spaced manner; multiple reinforcing ribs are arranged on the shape memory alloy strip / wire for controlling the wing to be morphed upwards and the shape memory alloy strip / wire for controlling the wing to be morphed downwards in a spaced manner; the shape memory alloy strip / wire for controlling the wing to be morphed upwards and the shape memory alloy strip / wire for controlling the wing to be morphed downwards are arranged in a flexible base body; and insulating and heatinsulation coating bodies coat the external surfaces of the morphed shape memory alloy strip / wires. Electric heating elements are arranged on the shape memory alloy strip / wire for controlling the wingto be morphed upwards and the shape memory alloy strip / wire for controlling the wing to be morphed downwards. According to the additive manufacturing method, the unmanned aerial vehicle morphing wingis prepared by using the additive manufacturing method. According to the rigid-flexible coupling unmanned aerial vehicle morphing wing and the additive manufacturing method thereof, a characteristicthat the wing is morphed upwards and downwards and morphed forwards and backwards in the case that the unmanned aerial vehicle morphing wing is electrified is realized.

A bridging structure for a deforming foil, such as a morphing wing, that provides a fluid-dynamic surface throughout foil deformation that forms a curved fluid-dynamic surface with a relatively low drag. A high extent of foil deformation can be provided, with lower actuation force, providing a fluid-dynamic surface with a simple or complex curve in one direction, by providing a set of rail-mounted members that are joined at one end to a deforming sheet. By coupling the members with high elongation, resilient bodies, adjacent members can support each other, while permitting extension, and accommodating curvature.

The invention discloses a variable-camber deformable wing based on the connecting rod driving. The deformable wing comprises a wing body, a connecting rod driving assembly and a rotating shaft connecting assembly, the wing body is composed of multiple sections of wing modules, the wing modules are rotationally connected through the rotating shaft connecting assembly at a time, and the connecting rod driving assembly organically combines all the wing modules; all the wing modules can be driven by linear motion to form knuckle type bending deformation, the adopted connecting rod driving assemblyis high in driving efficiency, and large-range bending deformation of wings can be achieved.