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52 results about "Wing membrane" patented technology
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Inclined rotating wing aircraft with telescopic wing membranes
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.
Owner:CIVIL AVIATION UNIV OF CHINA
Flapping-rotating wing with attack angle control device
ActiveCN104590560AReduce negative liftAverage lift increaseOrnithoptersMicro air vehicleRange of motion
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.
Owner:BEIHANG UNIV
Self-adjustment deformation foldable wing mechanism for foldable flapping wing micro air vehicle
PendingCN108454852AImprove work efficiencyEasy to recycleWing adjustmentsOrnithoptersFlapping wingMicro air vehicle
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.
Owner:JILIN UNIV
Scheme for improving flapping intensity of flapping-wing aircrafts
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.
Owner:李维农
Self-adaption variable-rigidity bow wing for micro flapping-wing and flapping rotor crafts
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.
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY
Flat four-footed gliding robot provided with empennage
The invention discloses a flat four-footed gliding robot provided with an empennage and belongs to the technical field of mechanical design. The robot comprises a body module, a limb module, an empennage module and a flexible wing membrane, and is of a flat structure in the whole; the limb module comprises four same-structured portions, which are positioned on frame structures at the four vertex positions of the body module, and conducts up-down pitching motion relative to the plane on which the body module is located under the control of four corresponding steering engines A; the empennage module is installed at the rear end of the body module, and conducts up-down pitching motion relative to the plane on which the body module is located under the control of corresponding steering engines B; the flexible wing membrane covers the upper and lower faces of the body module and is fixedly connected onto the limb module and the shape of the flexible wing membrane is changed under the driving of the pitching motion of the limb module. The robot is convenient to install and compact in structure; the flat four-footed gliding robot is designed to be flatted in the whole, the gliding stability is better, the flat four-footed gliding robot is light in the whole, and the glide ratio is favorably improved.
Owner:BEIHANG UNIV
IPMC (Ionic Polymer Metal Composite) driven simulated dragonfly wing flapping robot
InactiveCN104229139AExcellent flight adaptabilityImprove transmission efficiencyOrnithoptersIonic polymer–metal compositesWing vein
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.
Owner:XIAMEN UNIV
Flapping aircraft scheme
InactiveCN105197239AEven by forceRigid strength requirements are reducedOrnithoptersFlapping wingWing membrane
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.
Owner:李维农
Bionic flapping wing flapping and twisting combined motion transmission device for miniature aircraft
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.
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY
Externally pressed six-wing tubular membrane and method for manufacturing same
ActiveCN104667752ASolve the problem of spatial three-dimensional distributionDoes not affect effective filtration efficiencySemi-permeable membranesBiological water/sewage treatmentEpoxyFiltration
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.
Owner:苏州市和源环保科技有限公司
Sail wing with high span efficiency and controlled pitching moment
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.
Owner:AURORA FLIGHT SCI CORP
Flapping-wing aircraft with eccentric wheels for pushing and pulling sliding boxes to do reciprocating linear motion to enable wing membranes to float
The invention relates to a helicopter, and in particular relates to a flapping-wing aircraft with eccentric wheels for pushing and pulling sliding boxes to do reciprocating linear motion to enable wing membranes to float. A plurality of eccentric wheels are connected in series on a main transmission shaft, the initial positions of the adjacent eccentric wheels on the main transmission shaft are opposite up and down, an upper sliding box and a lower sliding box are arranged on the periphery of each eccentric wheel, transmission rods in up and down motion are connected above the upper sliding box and the lower sliding box through transmission rod connecting pieces, a pair of flapping-wing booms is symmetrically connected to the transmission rods in up and down motion, transmission rod sliding connection points are arranged at the joints of the flapping-wing booms and the transmission rods in up and down motion, flapping-wing pivots are arranged at the joints of the flapping-wing booms and tilting wing main arms, and flapping-wing soft wing membranes are arranged on the flapping-wing booms. The flapping-wing aircraft provided by the invention is larger in capacity, capable of flying farther, very simple in structure, easy to manufacture, safe and reliable.
Owner:河南星汉矢量推力器制造有限公司
Membrane wing folding system and membrane wing aircraft thereof
PendingCN112874758AImprove running stabilityReduce resistanceWing adjustmentsRotocraftElectric machineryStructural engineering
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.
Owner:曾昭达
Power wingsuit
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.
Owner:李明珠
Wall climbing-gliding robot with retractable and extendable wing membranes
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.
Owner:BEIHANG UNIV
Bionic, inflatable and deployable structure
PendingCN106904294AImprove reliabilityLight in massCosmonautic vehiclesInflatable space structuresEngineeringMechanics
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.
Owner:SHENYANG INST OF AUTOMATION - CHINESE ACAD OF SCI
Lift force and rolling torque control method for bionic micro flapping-wing air vehicle
PendingCN114104283ADoes not affect structural changesLarge control torqueOrnithoptersLeading edgeFlapping wing
The invention discloses a lift force and rolling moment control method for a bionic micro flapping-wing aircraft, and aims to solve the problems of generation and control of lift force and rolling moment of the aircraft. When the aircraft needs to generate lift force and rolling torque, the deflection angles of wing rods at the front edges of flapping wings on the two sides around wing roots are controlled through steering engines, the flapping plane positions of the wings and the tightness degree of wing membranes are changed, then the lifting force of the wings is changed, the left side and the right side generate different lift force, and expected rolling torque is obtained; the rolling control of the bionic micro flapping-wing air vehicle is realized. According to the lift force and rolling control method, wings of the bionic micro flapping-wing aircraft are directly operated, a control mechanism is easy to implement, large deformation of a wing membrane can be caused by controlling movement of a leading edge wing rod, large control torque is generated, and in addition, the control mode that the two wings are controlled through the two steering engines respectively is adopted, so that the lift force and rolling speed is greatly improved. And the generation and control precision of the lift force and the rolling moment is also obviously improved.
Owner:BEIHANG UNIV
Flapping rotor wing capable of achieving lift enhancement through hole
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.
Owner:BEIHANG UNIV
tilt-wing aircraft with retractable membrane
Owner:CIVIL AVIATION UNIV OF CHINA
Miniature flapping wings capable of realizing large deformation and high control moment generation
ActiveCN112141331AImprove controlImprove anti-disturbance abilityOrnithoptersAttitude controlFlapping wingFlight vehicle
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.
Owner:BEIHANG UNIV
Spar for sailwings
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.
Owner:AURORA FLIGHT SCI CORP
Sail wing with high span efficiency and controlled pitching moment
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.
Owner:AURORA FLIGHT SCI CORP
Spar for sailwings
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.
Owner:AURORA FLIGHT SCI CORP
Manpower-wing-flapping air vehicle
The invention discloses a manpower-wing-flapping air vehicle. The manpower-wing-flapping air vehicle comprises a body, flapping wings, a power mechanism, a manned device and a tail wing. The power mechanism comprises a driving shaft, a driving connecting frame with the left side and the right side which are symmetrically arranged, driving crank arms and shoes. The flapping wings comprise large arms, small arms and a wing membrane, wherein the large arms, the small arms and the wing membrane are symmetrically arranged in a left-right mode; one ends of elastic pulling locks are fixed to frame rods, and the other ends of the elastic pulling locks are fixed to the middles of large arm bodies. The manned device is fixed to a fixing frame and arranged above the shoes and between two stretchable rods, and comprises an upper-body safety belt and a lower-body safety. A reversing mechanism is a gear reversing mechanism. The tail wing is triangular and is fixed to a tail-wing frame. By means of the manpower-wing-flapping air vehicle, the taking-off movement, flying, gliding, the turning-in-air movement and landing of a single person can be really completely by manpower with the flapping wing technology, the void of the project is filled, and the manpower-wing-flapping air vehicle can be applied to the competitive sports field, the tour and sightseeing field, the person rescue field, the video shooting field and the like.
Owner:宋兆会
Rigid-flexible coupling active and passive deformation flapping wing mechanism and attack angle adjusting method
ActiveCN114148518AImprove aerodynamic performanceImprove energy efficiencyWing adjustmentsOrnithoptersLeading edgeFlapping wing
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.
Owner:SOUTHEAST UNIV
Water guide enclosure
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.
Owner:NANJING INST OF GEOGRAPHY & LIMNOLOGY
A flapping rotor with an angle of attack control device
ActiveCN104590560BReduce negative liftAverage lift increaseOrnithoptersFlight vehicleClassical mechanics
The invention discloses a flapping rotor with an angle of attack control device, which belongs to the technical field of micro-aircraft. Including flapping rotor, angle of attack control device and limit device; flapping rotor includes main beam, short beam, inclined beam and wing membrane; Stopper and angle of attack controller; a groove is made on the angle of attack controller, and the baffle moves up and down in the groove; the stopper is used to control the range of motion of the baffle. The other includes deformation sheets and limit beams. By changing the thickness of the deformation sheets or adjusting the distance between the connection point of the short beam and the inclined beam and the main beam, the angle of attack of the airfoil when the flapping rotor is shot up is controlled. The limit beam is used to Limit the deformation of the flapping rotor when the flapping rotor is down; by controlling the angle of attack of the flapping rotor during the flapping process, on the basis of maintaining the positive lift, the negative lift is effectively reduced, and the average lift of the micro flapping rotor aircraft is improved. The energy utilization rate of the aircraft is improved.
Owner:BEIHANG UNIV
Design scheme and preparation method of composite material wing for micro ornithopter
PendingCN114872894ALight in massImprove aerodynamic performanceAircraft assemblyDrag reductionAdhesive beltWing vein
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.
Owner:BEIHANG UNIV
A biomimetic dragonfly flapping wing robot driven by ionomer-metal complexes
InactiveCN104229139BImprove transmission efficiencyImprove energy efficiencyOrnithoptersIonic polymer–metal compositesWing vein
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.
Owner:XIAMEN UNIV
An external pressure hexagonal tubular membrane
ActiveCN104667752BChemically stableRadiation resistantSemi-permeable membranesBiological water/sewage treatmentEpoxyFiltration
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.
Owner:苏州市和源环保科技有限公司
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