52 results about "Wing membrane" patented technology

The invention relates to an inclined rotating wing aircraft with telescopic wing membranes. The inclined rotating wing aircraft comprises an aircraft body, a center shaft, a main transmission mechanism, first to third power units, an outer side rod, a support rod, a main wing membrane, a flight controller, and first to third undercarriages. The inclined rotating wing aircraft disclosed by the invention is improved on the basis of the structure of the traditional four-wing aircraft, and an inclined rotating structure of an inclined rotating four-rotary wing aircraft and a wing membrane structure of a flapping wing aircraft are added. According to the inclined rotating wing aircraft, the structural state of the inclined rotating wing aircraft includes a ground sliding state, a four-rotary wing flying state and a high-altitude cruising state; when the inclined rotating wing aircraft is in a ground movement state, the undercarriages contact with the ground, the main wing membrane is open, and the forward movement, backward movement, left rotation movement, right rotation movement, climbing movement and downgrade movement of the aircraft are realized by regulating the speed of four rotary wings; the movement state of the aircraft on the ground is realized under the action of the undercarriages, and the movement state is impossible to realize by the inclined rotating four-rotary wing aircraft and the flapping wing aircraft; and the climbing movement and the downgrade movement can be realized without changing the state of the aircraft, so that the energy consumption is reduced, and the complexity of a control program is prevented.

The invention discloses a flapping-rotating wing with an attack angle control device, and belongs to the technical field of micro aerial vehicles. The flapping-rotating wing comprises a flapping-rotating wing body, the attack angle control device and a limiting device, wherein the flapping-rotating wing body comprises a main beam, a short beam, an inclined beam and a wing membrane; the attack angle control device and the limiting device act commonly and comprise two modes, one mode is that the attack angle control device and the limiting device comprise a baffle plate, a limiter and an attack angle controller, a groove is formed in the attack angle controller, the baffle plate moves up and down in the groove, and the limiter is used for controlling the movement range of the baffle plate; the other mode is that the attack angle control device and the limiting device comprise a deform sheet and a limiting girder, the thickness of the deform sheet is changed or the distance from the connecting point of the short beam and the inclined beam to the main beam is adjusted to control the wing section attack angle when the flapping-rotating wing body flaps upwards, and the limiting girder is used for limiting the deformation of the flapping-rotating wing when the flapping-rotating wing flaps downwards; the attack angle of the flapping-rotating wing during flapping is controlled, while positive lifting force is maintained, negative lifting force is effectively reduced, and thus, average lifting force of the micro aerial vehicle with the flapping-rotating wing is increased and the energy utilization rate of the aerial vehicle is increased.

The invention discloses a self-adjustment deformation foldable wing mechanism for a foldable flapping wing micro air vehicle, and belongs to the technical field of micro air vehicles. The self-adjustment deformation foldable wing mechanism mainly consists of three folding wings, three connecting rods, a locking pin, a polyvinyl chloride wing membrane, fixing frames, a locking pin and electric artificial muscle, wherein the two sides of the middle folding wing are connected with the left and right folding wings through the locking pins respectively; the three connecting rods are movably connected with the folding wings and a sliding block through the locking pins respectively; the polyvinyl chloride wing membrane is glued on the lower surfaces of the three folding wings; the two fixing frames are glued on the lower surface of the polyvinyl chloride wing membrane and are fixed on the folding wings by the locking pins. According to the self-adjustment deformation foldable wing mechanism disclosed by the invention, under the control of a single chip microcomputer, all components can make accurate response to effectively finish the actions of wing spreading and wing retraction. Throughthe electric artificial muscle, the self-adjustment deformation foldable wing is kept in a folded state, the working efficiency is high, and the recycling and the carrying are facilitated.

The invention relates to an aircraft in fluid media (air or water), particularly to a scheme for improving the flapping intensity of flapping-wing aircrafts. The breakthrough on miniature flapping-wing aircrafts is realized, and however, except miniature flapping-wing aircrafts, high-efficient manned flight cannot be realized so far due to the rigorous requirements for materials. In order to improve the flapping intensity of flapping-wing aircrafts, the invention provides the scheme for improving the flapping intensity of flapping-wing aircrafts. The flapping-wing aircraft comprises an aircraft body, flapping wings, and a flapping mechanism, wherein each flapping wing consists of a wing bar and a wing membrane, and each wing membrane is attached to the corresponding wing bar; the flapping mechanism consists of double-crank hinge mechanisms, usually, the flapping wings of a flapping-wing aircraft or an insect are connected with bodies through one position (usually called wing root), and due to the low intensity of materials, artificial flapping-wing aircrafts cannot realize manned flight. The scheme provided by the invention has the benefits that at least two positions of each flapping wing are connected with the aircraft bodies through the double-crank mechanisms, so that the requirements for the intensity of the materials of the flapping wings are substantially reduced; motors mounted on the aircraft bodies enable the flapping wings to vibrate through the double-crank mechanisms, so that the high-efficient flight of the flapping-wing aircraft is realized.

The invention belongs to the field of aircraft design and relates to a bow wing for micro flapping-wing and flapping rotor crafts. The bow wing comprises a main beam, bow beams, bowstrings and a wingmembrane. The main beam is a beam in a spanwise direction of the wing, one side of the wing membrane is fixedly connected with the main beam, the bow beams are fixedly connected with the wing membranes, two ends of each bowstring are fixedly connected with two ends of the corresponding bow beam, and a required pneumatic appearance is formed through the wing membrane. The wing surface of the bow wing is cambered to some extent intrinsically, and high lift coefficient in a steady flow field is realized. The negative lift of bow wing in an upbeat stage is reduced while instantaneous lift is increased in a downbeat stage, and high energy utilization rate is realized. In material selection of the bow wing, a material low in Young modulus is selected for the bow wing, and high chordwise flexibility is achieved.

The invention discloses an IPMC (Ionic Polymer Metal Composite) driven simulated dragonfly wing flapping robot and relates to a simulated wing flapping robot. The IPMC driven simulated dragonfly wing flapping robot is provided with wing veins, wing membranes, wing IPMC driving parts, wings, a robot body, circuit controllers, copper sheet electrodes, robot body IPMC driving parts and fixing shafts; the wing veins are arranged on the wings; the two wing IPMC driving parts are arranged on the wings; deformation of the wings is achieved due to change of the wing shapes; the two robot body IPMC driving parts are arranged at the bottom of the robot body; one ends of the robot body IPMC driving parts are fixed on the robot body and the other ends are arranged on wing root portions of the wings; the wings are hinged to the robot body which drives flapping of the wings; the copper sheet electrodes enable the circuit controllers and the wing IPMC driving parts or the circuit controllers and the robot body IPMC driving parts to be connected through leads; the circuit controllers, the robot body IPMC driving parts and the fixing shafts are arranged on a robot frame; fixing shaft holes in the wings are hinged to the fixing shafts to achieve rotation between the wings and the robot body.

The invention relates to an aircraft in a fluid medium, in particular to a flapping aircraft scheme. In the field, breakthrough is achieved in minitype ornithopters, however, except minitype ornithopters, efficient manned flight can not be achieved so far due to the demanding requirement for materials. To overcome the demanding requirements of traditional flapping aircrafts for materials and make man-made flapping aircrafts have the flight function like insects, the invention provides a scheme according to which most rigid materials can be replaced with flexible materials. In the scheme, a flapping aircraft is composed of a pedal, a flapping wing and connecting ropes (or pull rods), wherein the flapping wing is composed of a wing rod and a wing membrane, and the wing membrane is attached to the wing rod. Through mechanism simplification, multi-point connection between the flapping wing and the pedal is achieved, and the flapping aircraft is stressed uniformly. Due to the fact that most rigid materials can be replaced with flexible materials, the requirement of the flapping aircraft for material rigidness is reduced greatly, and even the wing rod can be omitted so that popularization of manned flapping aircrafts can be achieved.

The invention discloses a bionic flapping wing flapping and twisting combined motion transmission device for a miniature aircraft, and belongs to the field of aircraft design. The device comprises a supporting rod, a transmission mechanism and a flapping wing main structure. The supporting rod is vertically arranged, the bottom of the supporting rod is fixedly connected with a fuselage of the miniature aircraft, and the middle and top end of the supporting rod are respectively connected with the transmission mechanism and a flapping wing main beam. The transmission mechanism comprises an uppersleeve, a lower sleeve, a driving rod, an L-shaped connecting rod and a limiting rope. The flapping wing main structure comprises the flapping wing main beam, a flapping wing outer beam, a flapping wing main rib, a flapping wing auxiliary beam and a wing membrane. The device can solve the technical problems that (1) under the condition that the maximum value of the lifting force at the time of downswing is guaranteed, the resistance at the time of upswing is effectively reduced; (2) the flapping wing torsion angle can be adjusted by adjusting the length of the limiting rope, and operation issimple and convenient; and (3) the resistance in the upswing is reduced, the resistance in the downswing stage has no obvious difference from that of a traditional flapping wing, and the advantage ofhigh energy utilization rate is achieved.

The invention discloses an externally pressed six-wing tubular membrane and a method for manufacturing the membrane. The externally pressed six-wing tubular membrane comprises a six-wing tubular membrane body, a six-wing lined pipe, a composite filter membrane, a depression bar, a core tube, an electrode lead, an external layer carbon net, an organic filter membrane, an internal layer carbon net, and a prefabricated membrane tube. The composite filter membrane is composed of the internal layer carbon net, the organic filter membrane, the external layer carbon net and the electrode lead. The six-wing membrane is composed of the six-wing lined pipe, the composite filter membrane, the depression bar, the core tube and an end cover; flow guide circular holes are arranged between adjacent wing boards outside the core tube; the composite filter membrane is fixed between two adjacent wing boards by the depression bar and distributed on the outer surface of the six-wing lined pipe in a rising and falling way; both ends of the six-wing tubular membrane are sealed and fixed by the end cover and an epoxy resin; the electrode lead is led out from the sealed position of the epoxy resin. According to the externally pressed six-wing tubular membrane, the high-efficiency filtration, and pollution-preventing and self-cleaning functions are realized, and the manufacturing process is simple, thus the externally pressed six-wing tubular membrane is applied to the large polluted water or waste water treatment engineering.

An aircraft comprising a fuselage, a sail wing appended to the fuselage, the sail wing having a sail wing root chord length, and wherein the sail wing includes a sail wing leading edge spar, a sail wing membrane attached to the sail wing leading edge spar, and a sail wing trailing edge wire located at a trailing edge of the sail wing membrane, the aircraft further comprising a wing surface extension, located aft and at an inboard area of the sail wing trailing edge wire, the wing surface extension having a wing surface extension root chord length, and wherein the wing surface extension includes a wing surface extension membrane attached to the sail wing trailing edge wire, and a wing surface extension trailing edge, and wherein the wing surface extension trailing edge is reflexed such that the wing surface extension trailing edge is positioned upwards at a first angle with respect to a plane formed along a centerline of the aircraft and along the lower surfaces of the sail wing. The wing surface extension is further configured to affect a reduced nose-up pitching moment, and to produce a more even coefficient of lift along the wing of the aircraft.

The invention provides a membrane wing folding system which comprises two inner cross beams fixedly arranged at the top of a machine body, the two ends of each inner cross beam are connected with outer cross beams through electric folding mechanisms, wing membranes are arranged between the two inner cross beams and between the two outer cross beams, and each electric folding mechanism comprises a rotating motor, a push-pull screw, a power spiral sleeve and a rotating connecting rod. The rotating motor is connected with and drives the spiral sleeve to rotate, the spiral sleeve is arranged on the push-pull screw in a sleeving mode and is in threaded connection with the push-pull screw, the push-pull screw is arranged in the inner cross beam in a sliding mode, one end of the rotating connecting rod is rotationally connected with the end of the push-pull screw, the other end of the rotating connecting rod is rotationally connected with the outer cross beam, and the outer cross beam is rotationally connected with the inner cross beam. Before taking off and landing, the wing membrane is folded and put away, namely the effect of reducing the resistance of the wing to the dual-mode aircraft in the vertical direction when the dual-mode aircraft ascends and descends can be achieved, and then the purpose of ensuring that the dual-mode aircraft applying the membrane wing folding system has high operation stability when the dual-mode aircraft ascends and descends vertically is achieved.

The embodiment of the invention discloses a power wingsuit. The power windsuit includes a flight suit, two extension tubes horizontally arranged on the outer sides of two shoulders of flight staff, aholding frame, one or more power flight devices, two flight wing membranes, an empennage wing membrane and a control switch, wherein one ends of the extension tubes are opened, and the other ends of the extension tubes are closed; the holding frame sleeves the flight suit; the power flight devices are mounted on the holding frame, and the power ejecting ends face towards the foot position of the flight staff; the two flight wing membranes correspond to the two expansion tubes, the side edges of the flight wing membranes in the longitudinal directions of the outer walls of the expansion tubes are connected to the lower surfaces of the outer walls of the expansion tubes, and the ends, close to the flight staff, of the flight wing membranes are connected with the outer surfaces, correspondingto the armpit and the rib of the flight staff, of the flight suit; the empennage wing membrane is connected to the outer surface, between two legs of the flight staff, of the flight suit; and the control switch is mounted on the end, close to the hands of the flight staff, of the inner side of a chamber of one of the expansion tubes. Compared with a traditional wingsuit, the power wingsuit has the advantages that the flight speed is high, the auto-hover time is long, the safety is high, the comprehensive using cost is low, operation is easy and quick, and long-term complex training is not needed.

The invention discloses a wall climbing-gliding robot with retractable and extendable wing membranes. The wall climbing-gliding robot comprises a body module, leg modules, a retractable and extendablewing membrane module and a tail module; each leg module is composed of four telescopic joints with the same structure, wherein the foot ends of the telescopic joints are provided with hook thorns, each telescopic joint makes linear reciprocating motion through a gear and rack mechanism, and driving steering engines A of the leg modules are connected with a bottom plate of the body module throughleg steering engine supports; the retractable and extendable wing membrane module is composed of four sets of rocker sliding block mechanisms and the flexible wing membranes attached to connecting rods, and all the sets of rocker sliding block mechanisms can be driven by the telescopic joints to make plane motion to achieve retraction and extension of the flexible wing membranes; and the tail module is mounted at the rear end of the body module, and under driving of a steering engine B, through double rocker mechanisms, a tail membrane can make up-down pitch motion relative to a body to achieve the effect of air pitch attitude adjustment. Climbing-gliding integrated design is adopted, climbing-gliding mode driving multiplex is achieved, the wing membranes are retractable and extendable, modular mounting is achieved, the structure is compact, and the weight is low.

The invention relates to a bionic, inflatable and deployable structure. A trunk air chamber is contained in a central trunk. The upper portion of the structure is provided with a trunk end cover installed at the top of the central trunk. A main inflation inlet communicating with the trunk air chamber is connected to the central trunk in a sealed mode. An inflation switching valve is installed on the main inflation inlet. A plurality of branch inflation inlets communicating with the trunk air chamber are connected to the positions, on the two sides of the main inflation inlet, of the central trunk in a sealed mode correspondingly. Wing membrane sets on the sides each comprise a wing membrane, a main inflation vein and a linear main inflation vein, and the main inflation vein and the linear main inflation vein are embedded in the wing membrane. Each main inflation vein communicates with the corresponding branch inflation inlet on the same side. The linear main inflation veins are located in the main inflation veins. One ends of the linear main inflation veins communicate with the main inflation veins, and the other ends of the linear main inflation veins communicate with the branch inflation inlets in the same side. The main inflation veins and the linear main inflation veins are all embedded into the wing membranes. The bionic, inflatable and deployable structure does not need to be driven by a motor, and is ingenious in structure and low in weight, and a large deployable area can be obtained through a small folding size.

The invention discloses a flapping rotor wing capable of achieving lift enhancement through a hole. The flapping rotor wing capable of achieving lift enhancement through the hole comprises a flapping rotor wing body, the air hole and a hinge. The flapping rotor wing body comprises a main beam, a short beam, an inclined beam and a wing membrane. The wing membrane is adhered to a plane composed of the main beam, the short beam and the inclined beam. The air hole is a rectangular hole formed in the wing membrane by clipping, and one long edge of the air hole coincides with the leading edge of the wing membrane. The hinge is a rectangular resin film sheet, and the center of the hinge coincides with the center of the air hole; one long edge of the hinge coincides with the leading edge of the wing membrane and is adhered to the main beam, and the rest edges of the hinge are naturally attached to the wing membrane. The hinge is located under the wing membrane and above the beam structure. The flapping rotor wing capable of achieving lift enhancement through the hole has the advantages that when the wing moves upwards, the hinge is opened downwards, a high-pressure air current on the upper surface of the wing flows to the lower surface though the air hole, accordingly, the pressure difference of the upper surface and the lower surface of the wing is decreased, and unloading of the negative lift force is achieved; when the wing moves downwards, the hinge is attached to the lower surface of the wing, the air current cannot pass through the air hole, the positive lift force produced by flapping is maintained, thus, the average lift force is improved, and the energy utilization rate is increased.

The invention discloses miniature flapping wings capable of realizing large deformation and high control moment generation. The fixed connection mode of flapping wing root elastic rods and a rack is changed into two-way hinge connection, and the transverse and longitudinal movement range of the flapping wing root elastic rods is increased, so that the wing membrane deformation degree and attack angle change are more obvious in the forward and backward flapping process of the flapping wings, therefore, the change range of the rolling moment and the pitching moment is greatly increased, the control steering effect is enhanced, and the control effect, the disturbance resistance and the maneuvering flight capacity of a flapping-wing aircraft are greatly improved. Besides, the flapping wings are designed in a modular mode so that the whole bidirectional hinge device can be decomposed into simple independent units, disassembly, assembly and maintenance are facilitated, and the cost is saved.

A sail wing for a lightweight aircraft comprising a membrane; a front spar; and a tensioned rear wire attached to a trailing edge of the membrane, such that when the front spar is bent to match a curve of the tensioned trailing edge of the sail wing membrane, the sail wing membrane has substantially little or no twist, and results in substantially little or no induced drag.

The invention discloses a rigid-flexible coupling active and passive deformation flapping wing mechanism and an attack angle adjusting method. The rigid-flexible coupling active and passive deformation flapping wing mechanism comprises a rack, a flapping wing driving mechanism, a variable damping flapping wing deformation mechanism, a flapping wing deformation amplitude adjusting mechanism, a sensing control module and the corresponding attack angle adjusting method. The variable damping flapping wing deformation mechanism comprises a threaded shaft speed reducing motor, a wing film, a front edge rod, an adjustable damping rotating shaft, a spring piece and a wing supporting rod; the flapping wing deformation amplitude adjusting mechanism comprises a body I, a body II and a fastening screw; the sensing control module comprises an angle sensor, a wireless communication unit and a control processing unit; according to the active and passive deformation flapping wing mechanism, the problem that the amplitude and speed of passive deformation of the flapping wing mechanism cannot be adjusted is solved, the aerodynamic performance of a flapping wing robot is effectively improved, and automatic adjustment of the attack angle of a flapping wing in flight is achieved; the method is of great significance to improvement of flexibility of the flapping-wing robot and research of aerodynamic characteristics of birds and insects.

The invention discloses a water guide enclosure which comprises a float tow assembly, a guide wing membrane spoke and a bottom anchoring piece, wherein the float tow assembly is arranged underwater and has a certain buoyancy force; the guide wing membrane spoke is arranged below the float tow assembly and is towed and suspended in water by means of the float tow assembly; and the bottom anchoringassembly is connected to the bottom end of the guide wing membrane spoke and is acted to the upper and lowers of the guide wing membrane spoke through the float tow assembly and the bottom anchoring piece, so that the water guide enclosure can be unfolded in the water bottom. The water guide enclosure disclosed by the inventio0n the beneficial effects that the water guide enclosure can block partof pollutants crossing the bottom end of a defense line water underwater after blocking the defense line, so as to further reduce the content of cyanobacterial bloom in water, and the water guide enclosure is relatively low in cost and simple to mount.

The invention discloses a design scheme of a composite material wing for a micro flapping-wing air vehicle. The composite material wing for the micro flapping-wing air vehicle is composed of a wing membrane, a sleeve, a wing vein and an adhesive tape for protecting the wing membrane and fixing the composite material wing, compared with the design scheme of the wing used by the existing flapping-wing micro-aircraft, the design of the wing vein is changed, and the adhesive tape for protecting the wing membrane is added. The composite material wing for the micro ornithopter has the advantages of light weight, excellent aerodynamic performance, long service life and strong designability. The preparation method of the composite material wing for the micro flapping-wing air vehicle comprises seven steps, and the preparation method is simple to operate, good in processing consistency and very good in engineering application value.