1065 results about "Flapping wing" patented technology

A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear. When engine driven propellers or rotors are utilized, flapped wing panels are attached outboard of the forward and/or rearward propulsion units to provide yaw control during vertical flight.

The invention provides a flapping wing lift generating device, comprising a flapping wing mechanism, a flapping wing rotating mechanism and a flapping wing lifting mechanism, which are installed on an ornithopter. The flapping wing mechanism comprises two flapping wing blades and two flapping axles. Each flapping wing blade is a rigid rectangular plate with baffles at the ends. Each flapping axle is composed of two strip splints which clamp the flapping wing blades and allow the flapping wing blades to glide in the strip splints and two sections of coaxial axle heads positioned at the ends of the strip splints. The flapping wing rotating mechanism comprises a flapping gear fixed on an axle head at one end of the flapping axle, driving gears meshed with the flapping gear, a driving belt or a driving chain between the two driving gears. One driving gear is connected with a rotating motor. The flapping wing lifting mechanism comprises a lifting rod and lifting wheels. The lifting rod is an I-shaped member. The two lifting wheels clamp the web rod of the I-shaped member. One lifting wheel is driven by a lifting motor. The device has high efficiency and large lift and can be used as the propeller of air or water transportation.

The invention relates to a double-wing type miniature bionic ornithopter, which comprises a driving mechanism, a double-flapping-wing system, a spoiler mechanism and a principal arm, wherein the driving mechanism is just connected to the front end of the main arm, the double-flapping-wing system is positioned above the principal arm, and the spoiler mechanism is connected to the rear end of the principal arm. The driving mechanism comprises a diamond rack, a miniature direct current motor, a gear reducing mechanism and two crank-link mechanisms, the double-flapping-wing system comprises two symmetrical flapping wing racks, four flapping wing installation rods, an upper layer of flapping wing and a lower layer of flapping wing, and the spoiler mechanism comprises an electromagnetic rubber, a spoiler and a swing wing. The miniature direct current motor pulls two flapping wing racks to move up and down through the gear reducing mechanism and the crank-link mechanisms, so that the bionic flapping wings can be realized. The electromagnetic rubber in the spoiler mechanism can control the swing wing to swing from side to side by changing the current direction, so that the fly direction of the ornithopter can be controlled.

The invention relates to a micro dragonfly-imitating dual-flapping wing aircraft which mainly consists of a rack, a front flapping wing system and a rear flapping wing system. A pinion (17) and a large gear (16) are in meshing transmission; the large gear (16) is fixedly connected with a runner (14) through a transmission shaft (15) at an adjustable angle (36); the large gear (16), a connection rod a (23), a front right rocker (24) with a sector gear, a Y-shaped front bracket (18), a runner (14), a connection rod b (34), a rear right rocker (33) with sector gear and a Y-shaped rear bracket (20) form a crank rocker mechanism respectively; and the front and rear flapping wing systems are in meshing transmission through the sector gears to realize symmetric flapping. Compared with the prior art, the micro dragonfly-imitating dual-flapping wing aircraft provided by the invention has the advantages that: the two flapping wings are driven by a single motor in a simple and compact structure,the flapping of the front and rear flapping wing systems is completely symmetric, the flapping phase difference of the front and rear flapping wing systems can be adjusted as necessary to as to perfectly imitate the flexible flapping flying of dragonfly, and the like.

The invention relates to an aileron rotary folding and unfolding type flapping wing device, which includes aileron rotary folding and unfolding type flapping wings and a related drive device, wherein the wings are divided into main wings and ailerons along the wingspan direction, exterior edges of the main wings and exterior edges of the ailerons which are connected via butt hinge can relatively rotate on the wings plane with the butt hinge as an axis, and the aileron plane can be folded under the main wings plane, the drive device comprises a main wings drive device and an aileron drive device which are driven to be connected via a main drive shaft, the main wings drive device is positioned in the head section, and composed of two symmetrical crank rocker mechanisms which respectively drive the left wing and the right wing, and the aileron drive device is positioned in the middle-rear portion of the wings chordwise direction. The aileron rotary folding and unfolding type flapping wing device employs a bevel gear pair to realize rotation shaft changes, thereby multi-degree-of-freedom motion can be driven by single power, approximately saving one main drive shaft and related motors, and greatly reducing weight.

A drive mechanism for the wings of miniature ornithopter is composed of a worm-gear speed reducer and two sets of 4-connection-rod unit consisting of crank with one end fixed to the axle of worm gear, connection rod with one end linked to crank, and rocker arm linked between rocker arm and wing.

The invention discloses a flapping wing driving mechanism of two-level parallel gear reduction. The mechanism comprises a rack, a motor, a two-level parallel gear reducer and a four-bar mechanism, wherein a micro motor is fixed on the rack, which drives the two-level parallel gear reducer and the two rocker arms of the four-bar mechanism and converts the high-speed rotation of the micro motor into the up-down flapping of the rocker arm of the four-bar mechanism at proper frequency. The flapping wing driving mechanism disclosed by the invention has the advantages of simple structure, light weight, small space, high reliability, long service life and the like, and is suitable for micro flapping wing aircraft.

The invention discloses a cylindrical cam flapping wing driving mechanism. A motor is fixed on a rack and drives a driving gear of a gear speed reduction device; a driven gear of the gear speed reduction device is coaxially and fixedly connected with a transmission shaft; the rack is fixedly connected with a guide rail which is parallel with a transmission shaft; the guide rail is internally provided with a connecting rod which can slide; one end of the connecting rod is articulated with a sliding plate, and the other end of the connecting rod is fixedly connected with a strut; a cylindrical cam is coaxially and fixedly connected at the outer side of the transmission shaft; one or more cycles of periodic curves are wound on the circumference of a cam slot; the sliding pate can slide in the cam slot; a swinging rod mechanism comprises two swinging arms, the middle part of each swinging arm is articulated with swinging arm shafts which are fixedly connected at two sides of the guide rail; one end of each swinging arm is provided with a sliding chute; the strut can slide in a reciprocating mode along the slide chute, and the other end of each swinging arm is connected with a flappingwing beam. By utilizing the mechanism provided by the invention, the complex plane flapping type can be realized, the structure is simple, the weight is light, the reliability is high, complex control is not required, and the mechanism is applicable to a micro flapping aircraft.

The invention provides a method for driving flapping wings to rotate by thrust produced by the flap of the flapping wings instead of driving by an electric motor, and the method combines with flapping wing and rotary wing technology. An aircraft designed by the method of the invention comprises the flapping wings, an electromagnetic driving mechanism, a connecting shaft, a roller bearing, a power supply, useful load, an electric steering engine, control surfaces, an undercarriage, a controller, an aircraft shell, a slip ring and an electric brush, wherein the electromagnetic driving mechanism drives a pair of flapping wings to flap up and down. The aircraft shell is connected with a rotary connecting shaft through the roller bearing, three control surfaces are evenly distributed at the lower part of the aircraft shell, and simultaneously the control surfaces have the function of the undercarriage of the aircraft. The flapping rotary wings of the invention have high pneumatic efficiency and can satisfy the mission and requirements of vertical takeoff and landing and hovering stopping of the aircraft. Simultaneously, the rotation of the flapping wings of the aircraft is a self-driven rotation, and the rotation is not offset by a torsion resisting mechanism which is added additionally. The aircraft has the advantages of simple design structure, light weight and high flight efficiency and is suitable for miniaturization aircraft design requirements.

A method of controlling wing position and velocity for a flapping wing air vehicle provides six-degrees-of-freedom movement for the aircraft through a split-cycle constant-period frequency modulation with wing bias method that generates time-varying upstroke and downstroke wing position commands for wing planforms to produce nonharmonic wing flapping trajectories that generate non-zero, cycle averaged wing drag and alter the location of the cycle-averaged center of pressure of the wings relative to the center of gravity of the aircraft to cause horizontal translation forces, rolling moments and pitching moments of the aircraft.

The invention provides a high-frequency flapping-wing bionic insect aircraft with controllable passive torsion. The high-frequency flapping-wing bionic insect aircraft comprises an aircraft body framework, and a hollow cup power motor, a crank rocker transmission mechanism, a speed reduction gear group, bionic flapping wings, a controllable passive torsion mechanism and a ball bearing group which are arranged on the aircraft body framework, wherein the crank rocker transmission mechanism converts rotation of an output shaft of the hollow cup power motor into reciprocating flapping motion of the two flapping wings, to simulate flying of insects; the speed reduction gear group is used for lowering the rotating speed of the output shaft of the hollow cup power motor, so that the flapping action of the flapping wings finally keeps in a range; the controllable passive torsion mechanism ensures that the flapping wings can be twisted around rotating shafts, to generate uplifting force; meanwhile, repelling force between a limiter and an electromagnet makes the flapping wings return to the vertical positions. By the adoption of the ball bearing group, the crank rocker transmission mechanism and the controllable passive torsion mechanism, the aims of greatly reducing the transmission friction and effectively converting the power into lift force of the aircraft are fulfilled.

The invention provides a flapping-wing aircraft belonging to the technical field of aircrafts. The flapping-wing aircraft comprises an airframe, a stationary shaft, a reversing frame, a half-rotating swing blade, a pin gear, a steering cam, a gearwheel, a driven gear, a driving gear, a control motor and the like, wherein the stationary shaft and the airframe are fixed, and the reversing frame is fixedly linked with the driven gear; the driving gear and the driven gear are meshed to form a main transmission mechanism of the aircraft to drive the reversing frame and the half-rotating wing blade to rotate to generate propelling force required by the aircraft; and the control motor is driven by a first-stage gear, the cam and the pin gear to form a maneuverable control mechanism of the aircraft, and the initial position of the half-rotating wing blade is changed, so that the direction of the propelling force is changed. The flapping-wing aircraft provided by the invention is flexible in adjusting the direction of the propelling force, stronger in maneuverability and beneficial to the control for taking off, landing and flying in a complex flying space; and the main transmission mechanism and the maneuverable control mechanism are simple, high in reliability and low in manufacturing cost.

The invention discloses a piezoelectric ceramic flapping-wing-type robot. The piezoelectric ceramic flapping-wing-type robot comprises a robot body support frame, robot wings, a piezoelectric driver, a driving electric cable, a transmission amplifying mechanism and driving feet, wherein the robot wings are based on a bionic design and are similar to a dipster hoverfly in shape; when the robot walks on land, a piezoelectric ceramic sheet is selected as the piezoelectric driver, and the piezoelectric ceramic sheet and a single-bent-end transmission amplifying mechanism form the driving feet; the driving electric cable inputs two common grounding sine wave signals for respectively driving the two driving feet, and the robot is driven to do controllable plane motion by utilizing a resonant oscillation principle. When the robot flies in the sky, the driving feet are taken down; a piezoelectric ceramic bimorph element is used as the piezoelectric driver to input a driving voltage signal; by a four-connecting-rod transmission mechanism, the oscillation is amplified and is converted into flapping of wings, thereby driving the robot body to fly. The robot is simple, light and convenient, and has certain adaptability to the environment.

The invention discloses a piezoelectric dragonfly-imitating micro flapping-wing aircraft. The piezoelectric dragonfly-imitating micro flapping-wing aircraft comprises an aircraft body, wing fixed plates, dragonfly-imitating wings and four twin-lamella piezoelectric actuators; the aircraft body comprises a fixing chamber, the wing fixed plates are fixed in a cavity of the fixing chamber, fixed orifices are arranged on opposite sidewalls of the fixing chamber, the dragonfly-imitating wings pass through the fixed orifices and are fixed on the wing fixed plate; the dragonfly-imitating wings comprise two front wings and two rear wings, one end of the twin-lamella piezoelectric actuator passes through the fixed orifices and is fixed with a wing root of the wing, other parts are suspended, and a cantilever beam structure is formed, and each twin-lamella piezoelectric actuator respectively controls one wing to generate flapping movement or adjusts deflecting direction under voltage excitation. The wings can bear high-frequency alternating stress, can bear different loads of various attitudes such as flapping, gliding and circling, and can obtain excellent balance stability and attitude control diversity; and more wings can obtain larger bearing capability.

An efficient flying device having flapping wings, an ornithopter, which uses many of the principles seen in bird flight, is presented herein. The wings are highly flexible, translationally stable and oscillate as a natural pendulum. Described as a springboard, the wings have a singular natural frequency, and a pumping means drives the wings at that frequency. Feedback means are described by which to accomplish this, whereby deflection of the wing affects an escapement mechanism which controls the timing and direction of the pumping means. Wing design is described whereby camber, flexure, torsion and directionality of wing components affect efficient propulsion, lift and differential reactivity with air during downstrokes and upstrokes. A crook element in the wing spar at a location proximal to the body of the device redirects vertical oscillation to horizontal. Other features are addressed, such as rearward vortex production and reaction, a double aerofoil wing construction, lateral and vertical wing curvature, rearward wing and featherlike element flexure to produce thrust, and connection of separate elastic elements to reduce power requirements.

The invention discloses a miniature bionic flapping aircraft based on a single-crank and double-rocker mechanism, and belongs to the technical fields of machine design and aircrafts. The aircraft adopts a single-crank and double-rocker mechanism, wherein the single-crank and double-rocker mechanism comprises a single-crank mechanism gear, a left wing rocker, a right wing rocker, a left wing connecting rod and a right wing connecting rod; the single-crank mechanism gear is fixed on a frame and forms a rotation pair; one end of each of the left wing connecting rod and the right wing connecting rod is connected with the single-crank mechanism gear through a pin; the other ends of the left wing connecting rod and the right wing connecting rod are respectively and rotationally connected with the left wing rocker and the right wing rocker, so as to transmit power; an extending section is formed at the second end point of each of the left wing rocker and the right wing rocker; the extending section is connected with a flapping wing structure, so as to drive the flapping wing to perform flapping. The aircraft can basically eliminate asymmetry of the aircraft during flight, has a function of switching various flight attitudes, and meanwhile has the characteristics of compact structure, high flexibility, high compactness and low weight.

The flapping wing for ornithopter is one double-layer inclined truss structure, and has the end connected to the ornithopter with greater thickness, low layer separated with the truss into homogeneously distributed square frames, and wing sheets fixed to the frames and capable of sealing the square frames. The flapping wing is connected to the ornithopter body via the connecting rotation shaft. The wing sheets are slightly opened normally, when the flapping wing is raised, the wing sheets are opened to reduce resistance, and when the flapping wing moves downwards, the wing sheets seal the square frames to form great upward support force. When the flapping wings swing up and down, great 'differential force' may be produced to reduce power consumption.

The invention relates to a biomimetic micro air vehicle with 8-shaped flapping tracks, which makes use of a flexible carbon fiber rod and a parylene film as an aerofoil framework and an aerofoil covering skin respectively for a palm-sized micro air vehicle. Even through a flapping (gear connecting rod) driving mechanism is only designed into a single degree of freedom four-bar (mechanism), the linkage of the upward and downward flapping is successfully coupled to flow direction forward and backward vibrations through the material and the shape design of a flexible aerofoil, thus three-dimensional 8-shaped flapping tracks are assembled at the aerofoil tip; and the flapping frequency of the generation of the 8-shaped tracks is close to or even more than 20 Hz, thus a micro air vehicle with a simple structure is formed and can generate the 8-shaped tracks automatically according to the essence of aeroelasticity without getting help from the design of a complicated delicate movement mechanism with multiple degrees of freedom.

The invention relates to a miniature flapping wing air vehicle with wings capable of performing active deformation and with multiple freedom degrees, and belongs to miniature bionic air vehicles. A transmission device fixing frame, an electronic control module and an empennage are fixed on an airframe body, a direct-current motor is mounted on the transmission device fixing frame, a regulating steering fan is fixed on a vertical tail of the empennage, a flapping wing torsional pendulum mechanism is fixed on the transmission device fixing frame, the end part of the flapping wing torsional pendulum mechanism is fixedly connected with flapping wing flexible main wings, a group of pre-bent elastic wing feather frameworks are fixed to the rear edge ends of the flapping wing flexible main wings, and wing feather piezoelectric thin films of solar lamellas are stuck to the upper surfaces of the pre-bent elastic wing feather frameworks. The miniature flapping wing air vehicle disclosed by the invention has the advantages that torsion actions are realized through composite motions adopting an eccentric ball structure and a crank and rocker mechanism, the size of a torsion angle can be correspondingly changed along with different positions of the miniature flapping wing air vehicle in the flight process, the miniature flapping wing air vehicle has high smoothness, the flight is more stable, and the practicality is high.

The invention discloses a flapping wing and turning device of a micro aerial vehicle. The flapping wing and turning device comprises a flapping wing rocking rod, a round pin, a connecting plate, a driving motor, a connecting rod, an installing frame, a gear, a turning rod, a tail wing supporting plate, a turning motor, a swinging arm, a rotating component and a swinging frame, wherein the driving motor drives a first-grade pinion to rotate, and the first-grade pinion drives a double-layer gear to rotate, and the double-layer gear drives second-grade gears at two sides to rotate, and the second-grade gear drives the connecting rod to move, and the connecting rod drives a left wing connecting plate, a right wing connecting plate and a flapping wing rocking rod to swing up and down so as to achieve the flapping of the wing. The turning motor drives a rocking frame to rock, the rotating component in the rocking frame drives the rocking arm to rotate around the round pin, so that the angles of two turning rods are deviated, and as a result, the aerial vehicle can be turned. According to the flapping wing and turning device, the flapping wing and the turning device are integrated, so that the benefit is brought to the microminiaturization of the flapping wing aerial vehicle; and meanwhile, the flapping wing and turning device has the characteristics of being simple in structure, flexible and small.

The invention discloses an electromagnetically-driven flapping wing type micro aircraft based on flexible hinges, which comprises chest cavities, cylindrical permanent magnets, a spiral coil, wings, a tergum and flexurally-deformed flexible hinges, wherein the two flexible hinges are passively twisted; the pair of wings is symmetrically mounted on both ends of the tergum; the flexible hinges are sandwiched between the two chest cavities to form a sandwich structure, the tergum is fixed on the flexible hinge, and both ends of the tergum are symmetrically positioned in free regions of the chest cavities; the spiral coil is fixedly mounted in the central position of the chest cavities; and the permanent magnet is fixed in the center of the tergum. Though the machining based on an MEMS (Micro Electronic Mechanical System) process, the invention realizes the flapping wing type micro aircraft of which the wingspan is smaller than 3cm, and driving force can be obtained through the interaction of the energized spiral coil and a magnetic field between the permanent magnets. Besides, the invention has the advantages of very simple structure, small input voltage and large output force, is convenient and flexible to control, and is easy to realize portable operation.