72results about How to "Flexible flight" patented technology

The present invention discloses a quick three-dimensional sampling method for physical data of a building. The present invention adopts a miniature unmanned aircraft to load corresponding types of sensing devices, data recording devices and information returning devices, etc., so as to acquire the physical data (intensity of sound, audio, temperature, humidity, illuminance, light color, gas components, electromagnetic field intensity, air-ion concentration, radiation strength, etc.) and carry out round trip flight in space and continuously acquire the physical data at each point of the path, and position the miniature aircraft by a photogrametry technology. The method concretely comprises the steps of: selection of the miniature unmanned aircraft for indoor flight, selection of sensing devices or sensors for sampling the physical data of the building, establishment of a system synchronous clock, sampling of the physical data of the building and accurate spatial positioning for the sampling points by a close-range photogrammetry method. Since the aircraft is fast in moving speed and is not restricted by the ground movement condition, the isochronism of the data can be ensured even if the number of the spatial sampling is largely increased than that of the ground operations.

The invention discloses a bionic flapping-wing aircraft based on flapping-folding-torsion coupling movement. The bionic flapping-wing aircraft is composed of a fuselage, wings on the two sides and anempennage mechanism. When a wing motor is started, a crank gear on an output shaft of the wing motor rotates to sequentially drive first front-section wing rods, second front-section wing rods and third front-section wing rods to rotate, and the flapping movement of the wings is achieved; fixed gears swing up and down along with the second front-section wing rods to transmit the torque to driven bevel gears through planet gears, so that third wing face supporting plates rotate within a small range around the third front-section wing rods, and accordingly the torsion movement of the wings is achieved; and the flapping angles of front-section wing bodies, middle-section wing bodies and tail-section wing bodies are different, and accordingly the folding movement of the wings is achieved. Steering of the aircraft is achieved jointly through an empennage and a steering engine for adjusting the empennage direction. The bionic flapping-wing aircraft based on the flapping-folding-torsion coupling movement has the characteristics that the number of driving original motive parts is small, the flapping-folding-torsion coupling movement of the flapping wings can be achieved, flying is flexible, and generated effective lift force is large.

The invention discloses a mobile edge computing unmanned aerial vehicle group auxiliary communication method for explosive traffic, which is responsible for providing computing service for users withcomputing requirements on the ground when a network is congested. Firstly, in the prediction part, an improved PSO-BP neural network is used for predicting the calculation demand distribution situation of a target area, and unmanned aerial vehicles supporting mobile edge calculation are deployed as required; secondly, a demand partitioning part is calculated, a target area is partitioned based ona fairness principle, and each unmanned aerial vehicle serves users in a sub-area; and finally, the unmanned aerial vehicle energy optimization part in each sub-region performs joint optimization on the unmanned aerial vehicle calculation frequency and the unmanned aerial vehicle flight path on the premise of meeting the user calculation requirement, so that the energy consumption of the unmannedaerial vehicle in each sub-region is minimum, the energy consumption of the whole unmanned aerial vehicle group is minimum, and the service time of the unmanned aerial vehicle group is prolonged.

The invention belongs to the field of aircrafts, and provides an aircraft. The aircraft comprises a frame, a first power unit, a second power unit and a rotation power unit. The first power unit comprises a first rotor wing device and is mounted on the frame. The second power unit comprises a second rotor wing device and is mounted on the frame rotationally through a rotating shaft. The rotation power unit is mounted on the frame and drives the rotating shaft to rotate. The second rotor wing device comprises a first sub rotor wing and a second sub rotor wing which are distributed on two sides of the rotating shaft. The aircraft has the advantages that horizontal component force of the second rotor wing device is generated only through inclination of the rotating shaft to achieve yawing, inclination of the frame is not needed during yawing, flight resistance is not increased, and flight action flexibility is guaranteed; the first sub rotor wing and the second sub rotor wing are distributed on the two sides of the rotating shaft, larger gas bearing span can be provided for the aircraft without power increase of the second power unit, and accordingly, flight stability of the aircraft is improved.

Disclosed are a coaxial two-propeller reverse rotor wing mechanism and an aircraft thereof. The coaxial two-propeller reverse rotor wing mechanism comprises an upper propeller, an upper rotor wing shaft, an upper cone gear, a lower propeller, a lower rotor wing shaft and a lower cone gear. The upper propeller is fixed at the upper end of the upper rotor wing shaft. The upper cone gear is fixed at the lower end of the upper rotor wing shaft in a sleeving mode. The lower propeller is fixed at the lower end of the lower rotor wing shaft. The lower cone gear is fixed at the upper end of the lower rotor wing shaft in a sleeving mode. The upper rotor wing shaft shares the same axis with the lower rotor wing shaft. The upper rotor wing shaft and the low rotor wing shaft are arranged in an over-the-air mode. The upper propeller is a variable pitch propeller. The upper propeller controls variable pitch through a variable pitch assembly. According to the coaxial two-propeller reverse rotor wing mechanism, angular momentum is low, machine arm shaking is low, flying of the aircraft is more flexible, and the wind resistance is high.

The objective of the invention is to provide an unmanned aerial vehicle used for panoramic photography. The unmanned aerial vehicle is particularly suitable for panoramic photography. The unmanned aerial vehicle includes a control device, a power supply, an electric actuator electrically connected to the power supply, and propellers connected to the electric actuator. The unmanned aerial vehicle is characterized in that the unmanned aerial vehicle also includes a shell and a vehicle main body connected to the inside of the shell; the electric actuator and the propellers are connected to the vehicle main body; the shell has a hollow structure, and is provided with photographing devices; the control device is electrically connected to the electric actuator and the photographing devices; theelectric actuator and the propellers are inside the shell; and a scheme including a middle frame and two hollow hemispheres is adopted, thus effectively protecting the vehicle main body of the unmanned aerial vehicle, preventing possible influences of collision on the unmanned aerial vehicle, improving safety and effectively avoiding possible harm to pedestrians when the unmanned aerial vehicle descends or falls.

The invention relates to a deformable flying vehicle. Two sides of the left and the right of a vehicle body of a fixed wing aircraft are provided with wings which can be folded into the body. The tail of the body is provided with a vertical empennage and a horizontal empennage. The vertical empennage is provided with a rudder or is not provided with the rudder, and the left and the right of the vertical empennage are provided with a compressed air spouts. The bottom of the vehicle body is provided with a plurality of wheels which are driven by a controllable motor. The vehicle body is internally provided with a vertical ducted fan and also is provided with a horizontal thrust engine with controllable rotation pause and rotation speed. The compressed air is introduced from the horizontal thrust engine to the sprout through a control valve. The deformable flying vehicle achieves running, elevating, hovering and flying by controlling the wheels, the vertical ducted fan, the horizontal thrust engine, the wings and the empennages. The deformable flying vehicle has performance for both the ground and the air, is safe, flexible, economical and environmental protective for running and flying and is convenient for using.

The invention relates to a miniature ornithopter with a wing twisting function and multiple flight motion functions and belongs to the field of miniature ornithopters. A flapping torsional mechanism, an empennage, a fuselage direct-current motor, an empennage supporting rod and an electronic control module are installed on an ornithopter frame body. Wings are connected to torsional panels. An adjusting and steering rotor is connected to a fan motor. An empennage transmission mechanism is connected to the empennage supporting rod. The empennage supporting rod and the empennage are fixedly connected together by an empennage supporting rod fixing structure through screws. The miniature ornithopter has the beneficial effects that the structure is novel, the design structure is simplified, and miniaturization is easy to achieve. The ornithopter can generate larger pushing-up force compared with an aircraft only flapping up and down under the condition that the flapping frequencies are the same, the flight performance of the miniature ornithopter is greatly improved, the ornithopter flies flexibly, the aerodynamic characteristics are improved, the flight efficiency is high, the size is small, the weight is small, practicality is higher, and more flight functions can be achieved.

The invention relates to a front single unmanned aerial vehicle pushing a nanometer titania photocatalysis net to remove fog and haze, and belongs to the technical field of forest fire prevention. The single unmanned aerial vehicle which can remove fog and can also remove the haze is utilized for carrying out round trip flight operation. The current output by a lithium ion battery of the single unmanned aerial vehicle is input into an electric anti-fogging agent spraying device through a wire to drive the electric anti-fogging agent spraying device to eject the liquid nitrogen anti-fogging agent to perform cooling and remove fog, wherein the electric anti-fogging agent spraying device is installed at the tail of the unmanned aerial vehicle. The current output by the lithium ion battery of the single unmanned aerial vehicle is input into a shunt and then input into an ultraviolet LED lighting lamp through a wire, the electric energy in the ultraviolet LED lighting lamp is converted into light energy, and ultraviolet rays are emitted by the ultraviolet LED lighting lamp to activate the nanometer titania on the surface layer of the nanometer titania photocatalysis net to generate the high-activity perssad with a high oxidation function so that the organic pollutant in the air can be decomposed, the haze in the valley can be reduced, and the transparency of the air can be improved; cameras installed in the forest can be used for shooting and recording images on the forest ground, and the forest fire behavior can be prevented and controlled.

The invention discloses an underwater-to-air universal aircraft layout. The underwater-to-air universal aircraft layout comprises an aircraft body; the aircraft body comprises an aircraft body front section and an aircraft body back section; folding fixed wings are symmetrically arranged on the two side surfaces of the front end of the aircraft body; vertical lifting devices are arranged on the folding fixed wings; a rotor used for parallel propulsion is arranged right ahead the aircraft body front section; a horizontal tail and a vertical tail are arranged at the back end of the aircraft body; and a watertight compartment used for floating and diving in the water is arranged on the aircraft body. According to the underwater-to-air universal aircraft layout, the watertight compartment arranged at the lower part of a cabin is beneficial for realizing the function of being able to repeatedly diving and floating; due to larger dihedral angle of the wings, a propeller of the vertical lifting device can be separated from the water surface before being started and can also provide the rolling stability; both high and low speed flights in the air can be taken into account, the water-entryimpact load and underwater navigation resistance are reduced, the velocity of water-exit can also be increased, and conversion of multiple motion states can be finished.

The invention provides an ornithopter with elastic wings. The ornithopter comprises a main fuselage body, a flapping wing transmission mechanism, the left elastic wing, the right elastic wing, the elastic tail wing and an adjustable supporting three-point-type undercarriage; the flapping wing transmission mechanism is fixedly installed on the main fuselage body and coincides with the gravity center of the main fuselage body; the left elastic wing and the right elastic wing are installed in the positions, on the two sides of the axis of the main fuselage body, of power output interfaces of the flapping wing transmission mechanism and are in driving connection with the flapping wing transmission mechanism; the elastic tail wing is fixed to the tail of the main fuselage body; and the adjustable supporting three-point-type undercarriage is fixed to the lower portion of the main fuselage body. According to the ornithopter with the elastic wings, flight lift force, the gravity center of thrust and the gravity center of the overall ornithopter coincide, and the ornithopter can do unpowered gliding and can glide in a wide flat terrain and land safely even through the driving force is lost; and the structure of the ornithopter is simple, can be suitable for large-size man carrying and freight transporting aerial vehicles and can be also suitable for small and medium-size unmanned aerial vehicles. The ornithopter with the elastic wings is high in safety, good in flight flexibility and high in flight load capacity.

The invention relates to a bionic unmanned scout for killing mosquitos, which belongs to the technical field of health and epidemic prevention, wherein an propeller thruster is mounted at the front of a scout body; a right wing, a right solar cell and a right high-frequency ultrasonic transmission device are mounted on the right side of the scout body; a left wing, a left solar cell and a left high-frequency ultrasonic transmission device are mounted on the left side of the scout body; a power output shaft, a motor, a right controller, a left controller, a wire and an energy storage cell are mounted at the front half part of the scout body; a high-frequency ultrasonic echo sonar, an echo locating system, an echo locating transmission antenna, a wireless remote control navigation system, a wireless remote control navigation receiving antenna and a wire are mounted at the back half part of the scout body; a tail wing is mounted at the tail part of the scout body; a mosquito information computer processing center, an analysis and storage system and a mosquito killing scouting command center are mounted on the ground; and a mosquito killing scouting instruction transmission antenna is mounted on the command center. In addition, a wireless remote control navigation transmission antenna, a computer system and an information storage system are mounted.

The invention discloses a drone with extending drone arms. The drone with the extending drone arms comprises a drone frame, a main drone arm, an auxiliary drone arm, a screw and a screw driving unit,wherein one end of the main drone arm is fixed to the drone arm and provided in a nested mode with the auxiliary drone arm and the screw, the screw driving unit is fixed onto the drone frame, one endof the screw if connected with the screw driving unit, the other end of the screw is threadedly connected with the auxiliary drone arm, the inner wall of the main drone arm is provided with a guide unit, and the screw driving unit is used for driving the screw to rotate to drive the auxiliary drone arm to extend and retract along the guide unit; the auxiliary drone arm bears rotors of the drone. The drone with the extending drone arms also comprises a landing frame, a connecting rod and a steering engine, wherein the steering engine is fixed at the bottom of the drone frame, one end of the connecting rod is connected with the rotating shaft of the steering engine, the connecting rod is fixedly provided with the landing frame, and the steering engine drives the connecting rod to rotate around the rotating shaft and further drives the landing frame to fold and unfold. The drone with the extending drone arms has the technical advantages of being simple in structure, flexible in flight, adjustable in attitude and table in flight.

This invention provides a kind of flying saucer, which pertains to aviation vehicles area. It includes capsule, operating and controlling system, energy electrical system, inner-cabin facilities, fuel system, start-up system and ignition system. On capsule there fix capsule motion direction regulating equipment and capsule whirling steadiness regulating system. On capsule there fix fuel tank. On fuel tank there is a fuel tube. On capsule there fix a flywheel jet engine also, which includes flywheel spindle, flywheel and jetting device. Flywheel spindle connects to capsule. Flywheel is fixed on flywheel spindle. In the peripheral region of flywheel there fix several jetting devices. It can realize vertically taking off and landing. Capsule motion direction regulating equipment and capsule whirling steadiness regulating equipment are fixed on capsule. It can be simply handled, and it flies smoothly and steadily. It is convenient to change directions. In flight, flying saucer produces a spiral airflow whirling around capsule and simultaneously spirally propelling toward the bottom of capsule, which can boost the propelling speed toward the bottom of capsule. This invention has advantages of its high flying speed; it's flexible in changing directions; its high security; its low fuel costs, and so on.

The invention relates to a flapping wing helicopter, belongs to the technical field of aircrafts and especially relates to a flapping wing aircraft. The flapping wing helicopter comprises a frame, a left wing, a right wing, a rotating joint, a tail wing motor and a tail rotor wing, wherein the frame is of cylindrical bar shape; a controller and a driving device are built in the frame; upward lifting force is generated by the two sides of a fuselage together with the left wing and the right wing in the manner of up and down flapping of the left wing and the right wing; the tail end is connected with the tail wing motor through one rotating joint; the tail rotor wing is arranged on the motor; the tail wing motor can be rotated for 180 degrees around the rotating joint; the flying state can be changed and quick ascending and landing can be realized in the manner of changing the inclined angle of the tail wing motor and the rotating direction of the tail rotor wing and changing the angle; the flexible change of the gesture can be realized. The flapping wing helicopter disclosed by the invention has a simple structure, is high in efficiency, has the flying advantages of the flapping wing helicopter, can solve the problem of flying gesture change of the flapping wing aircraft, can guarantee more flexible flying of the flapping wing aircraft and is beneficial to the popularization of the flapping wing aircraft.

The invention relates to a flapping wing device, in particular to a novel high-performance bionic bird flapping wing device capable of being applied to sports, entertainment and military science. The novel high-performance bionic bird flapping wing device comprises two sets of devices on the left and right sides, wherein each set of devices is composed of a gear, a crank, a connecting rod, a main wing and a stander. When the novel high-performance bionic bird flapping wing device works, the left gear rotates, the right gear meshed with the left gear also rotates; the rotating left gear drives the left crank to rotate, the left connecting rod swings along with the rotation, and the left main wing is then driven to swing vertically; a left auxiliary wing swings vertically under the driving of a left main wing side rod; the rotating right gear drives the right crank to rotate, the right connecting rod swings along with the rotation, and the right main wing is driven to swing vertically; a right auxiliary wing swings vertically under the driving of a right main wing side rod, and thus the integral flapping movements of the left and right wings are realized. For the novel high-performance bionic bird flapping wing device, the auxiliary wings and the main wings are organically combined, so that the size is small, the structure is compact, and the flying distance is long. The novel high-performance bionic bird flapping wing device is particularly suitable for the industries of sports, entertainment, military science and the like.

The invention relates to a four-rotor-wing indoor airship, which is designed by solving the technical problems of poor stability and flight control system complexity caused by the adoption of vector driving movement and posture height coupling of the existing indoor airship and particularly solving the technical problems of insufficient lifting force, static instability, poor safety, high noise, high cost and the like of an indoor special-shaped airship. The four-rotor-wing indoor airship comprises an airship capsule, four rotor wing assemblies and a hanging cabin, wherein the rotor wing assemblies are symmetrically distributed on the airship capsule, each rotor wing assembly comprises a rotor wing support arm, a rotor wing motor, a protecting ring and a propeller, the inner end of the rotor wing support arm is fixedly connected onto the airship capsule, the rotor wing motor is fixedly arranged at the outer side of the rotor wing support arm, the propeller is arranged on a rotating shaft of the rotor wing motor and is driven by the rotor wing motor, and the protecting ring surrounds the propeller and is fixedly arranged on the rotor wing motor. The four-rotor-wing indoor airship has the advantages that the structure is simple, the stability and the operability are high, the possibility for cooperatively completing various activities with people is provided, and because the stability enhancement control and flight principle similar to that of a four-rotor-wing helicopter is adopted, the four-rotor-wing indoor airship has the characteristic of adaptability to the insufficient lifting force and the static instability of a special-shaped airship structure. The four-rotor-wing indoor airship has the characteristics that the energy is saved, safety and reliability are realized, no pollution is caused, the noise is low, and the like, and the wide application of the indoor airship can be promoted.

The invention discloses a driving mechanism for a flapping rotor aircraft, and belongs to the technical field of aircraft design. The driving mechanism comprises wings, a fuselage, a transmission device and a power device; the fuselage is of a 3D-printed integrated structure and comprises a motor mounting side panel structure, a gear mounting side panel structure, a sleeve, a sleeve supporting frame, supporting rods, a supporting bridge and a flight control plate platform; the transmission device comprises a large gear, a double-layer gear, a motor gear, a cylindrical sliding rod, a sliding rail, an inner rod, wing mounting frames, wing connecting rods, a sleeve bearing, an inner rod bearing, an inner rod hinge support, a sleeve hinge support, a small bearing, rocker arms and flange bearings; and the power device comprises a micro power supply, a flight control plate, a micro brushless motor and a motor bearing. The complete machine stability is improved, and lift is greatly increased;and airfoils are driven to flap up and down through a sliding rail-sliding rod mode, thus transmission is smoother, and a larger load can be transmitted.

The invention relates to a foldable and unfoldable elastic wing in the field of aircrafts. The Foldable and unfoldable elastic wing comprises a wing connecting plate, a wing short plate, a wing long plate, a wing connecting rod, a wing rib, a thin wing sheet, an upper covering wing sheet and a lower covering swing sheet connected through axle holes; the wing connecting plate, the wing short plate,the wing long plate, the wing connecting rod and the wing rib are combined in a form of a planar four-connecting rod mechanism, the wing connecting plate is connected to a wing driving mechanism, thewing driving mechanism inputs a reciprocating thrust to push the wing short plate to swing around the axis, the wing short plate drives the a plurality of planar four-connecting rod mechanisms composed of the wing long plate, the wing connecting rod and the wing rib so as to fold and unfold the wing. The resistance of the wing lifted up in a flapping wing flying process can be reduced to the maximum extent, and meanwhile, the wing storage space can be saved to the maximum extent when an aircraft is parked.

The invention provides a biaxial tilting quad-rotor aircraft. A fuselage includes a plurality of power arms, a sensor unit, a controller unit, a control distributor unit, a vehicle dynamics system module, and a wireless communication module, wherein the power arms are uniformly located at the periphery edge position of the fuselage, the sensor unit, the controller unit, the control distributor unit, the vehicle dynamics system module, and the wireless communication module are arranged at the fuselage position; the wireless communication module can establish wireless communication with a groundcontrol station; the power arms comprise rotor wings and inclined mechanisms; rotor swings are driven by drive motors at motor fixing seats supported by the inclined mechanisms; the inclined mechanisms are connected with the controller unit; and the controller unit adjusts the positions and orientation of the rotor wings by the inclined mechanisms to adjust flight of the aircraft. According to the biaxial tilting quad-rotor aircraft, the rotation speed and the inclined rotating angle of the four rotor wings can be automatically adjusted according to an input instruction, stability of a systemis controlled by a closed-loop, the flight status of the aircraft is fed back, self flight adjusting and control work is automatically completed, and the purposes of flight pitching, rolling and yaware achieved; and the high efficiency and high reliability of flight adjusting control are ensured.

A jet flying vehicle with telescopic ring-shaped wing is composed of a semi-spherical or dished main body for carrying passengers or goods, engine on the top of main body, turbo-propeller connected to said engine, multiple air guiding blades arranged on the top circumference at intervals, the telescopic ring-shaped wing, and jet channel formed by guiding blades, ring-shaped ring and casing of main body. It can take off rertically, glide in sky, and fly near water surface or ground, or can be static in sky.

The invention discloses a long-distance perimeter security positioning and monitoring device and method. The device comprises a light source module, a sensing module, a detection module, a data acquisition and processing module and an unmanned aerial vehicle video information acquisition module. The invention further discloses a positioning and monitoring method applied to the device. The positioning and monitoring method comprises the following steps: detecting and acquiring signals, judging the polarization state of optical signals, executing a polarization control algorithm, executing intrusion behavior judgment, acquiring intrusion information, and acquiring intrusion point videos by using the unmanned aerial vehicle. A distributed optical fiber disturbance sensing technology and an unmanned aerial vehicle video monitoring technology are reasonably combined, and a polarization control algorithm, an intrusion point positioning algorithm and a mode recognition algorithm are used at the same time so that the system is suitable for perimeter security of a long-distance field environment; meanwhile, the advantages of the unmanned aerial vehicle video monitoring system are fully utilized, and real-time omnibearing video monitoring of invasion points and surrounding areas of the invasion points is achieved.

The invention provides a novel aircraft and an aircraft system, and relates to the technical field of flight. The novel aircraft comprises a fuselage, a pitch-control motor, a roll control motor, a transverse adjusting mechanism, two longitudinal adjusting mechanisms and a four-propeller-supporting-wing adjusting dual-output-shaft motor. The two longitudinal adjusting mechanisms are symmetrically arranged on the two sides of the fuselage. The pitch-control motor is arranged on the longitudinal adjusting mechanisms to control movement of the longitudinal adjusting mechanisms. The roll control motor is arranged on the fuselage and connected with the longitudinal adjusting mechanisms through the transverse adjusting mechanism. The transverse adjusting mechanism controls the longitudinal adjusting mechanisms to move in the transverse direction of the aircraft. Two output shafts of the four-propeller-supporting-wing adjusting dual-output-shaft motor are in transmission connection with four propeller supporting wings to control axial movement of the propeller supporting wings. According to the novel aircraft, the technical problems that a shooting scene is not comprehensive, the aircraft crashes easily in a complex space, and the aircraft takes off and lands on all terrains are solved.

The invention discloses aerodynamic layout of a flapping-wing matrix aircraft, comprising a body and large-aspect-ratio wings arranged on the two sides of the body in symmetric manner. Each large-aspect-ratio includes a wing framework that is formed by serially connecting a plurality of wing frames perpendicular to the body; a plurality of flapping wing frames along the body are included in each wing frame; an independent flapping wing is arranged within each flapping wing frame and is controlled independently; cooperative control of the multiple fapping wing sets helps implement vertical take-off and landing, aerial hovering, flapping flying and glide flying for the aircraft and also helps implement longitudinal and course control for the aircraft. Joint flapping of the flapping wing setshelps significantly improve the loading capacity of the aircraft, aerodynamic efficiency of the flapping wings is further improved, and the aircraft has a wider flying range and extended flying time.

The embodiment of the invention discloses a ducted unmanned aerial vehicle, which comprises a main body (9), a first duct (1), a second duct (2), a third duct (3), a fourth duct (4), a front landing gear and a rear landing gear, wherein the first duct (1) is connected with the first side of the main body (9); the second duct (2) is connected with the second side of the main body (9); the third duct (3) is connected with the third side of the main body (9); the fourth duct (4) is connected with the fourth side of the main body (9); the front landing gear is arranged below the head of the main body (9), and the rear landing gear is arranged below the tail of the main body (9); each of the first duct (1), the second duct (2), the third duct (3) and the fourth duct (4) is internally provided with a paddle and an engine for driving the paddle to rotate. The unmanned aerial vehicle is flexible in flight, high in safety, convenient to operate and long in flight duration.

The invention relates to a vibration type pine cone picking machine which comprises a machine body, a movement mechanism, a vibration device (9) and a clamping device (13). The machine body comprisesa machine body upper cover (6) and a ventilating device (7). A rubber damping cushion (15) is arranged on the lower side of the ventilating device (7). The movement mechanism comprises a first propeller (1), a second propeller (17) and a rotating motor for driving the first propeller (1) and the second propeller (17). The first propeller (1) is used for providing perpendicular lifting force. The second propeller (17) is used for providing lateral driving force. The ventilating device (7) is arranged on the lower side of the rubber damping cushion (15) and internally provided with a vibration exciter (14). The clamping device (13) is arranged on the lower side of the vibration device (9) and comprises a clamping jaw composed of two rows of hinges. Compared with the prior art, the vibrationtype pine cone picking machine has the advantages of being simple in structure, flexible in operation, high in picking efficiency, capable of adapting to a complicated environment, small in flight resistance and the like.

The invention relates to an aircraft with wind ball driven wind wheels at wing leading edges, belonging to the technical field of aviation aircrafts. The aircraft comprises a fuselage, a power device, a left wing, a right wing, an empennage and an undercarriage. The left wing and the right wing are the same in structure and size and are symmetrically arranged at the left and right sides of a longitudinal symmetric plane of the fuselage. The left wing comprises a left wind wheel, a left wind ball, a left fixed wing, a left flap and a left aileron; the right wing comprises a right wind wheel, a right wind ball, a right fixed wing, a right flap and a right aileron. Under the action of forwards-coming flow, the left wind ball and the right wind ball can rotate, a majority of the forwards-coming flow is lifted to the upper surfaces of the left and right wings and is accelerated to run back, and thus, a lifting force generated by the left and right wings is greatly increased. The aircraft disclosed by the invention can achieve STOL (Short Take Off and Landing) and is maneuverable and flexible in flight.

The invention relates to an ornithopter flying in a swinging mode, which can effectively solve the problem that people fly in the air and is characterized in that both sides of the ornithopter body of the ornithopter are provided with symmetrical wings; the ornithopter body is internally provided with a battery at the lower part of an ornithopter shell; a transverse supporting plate is arranged on the upper part of an ornithopter frame at the both sides of the battery; the supporting plate is provided with an electrical machine, a rotating shaft of which is provided with a gear wheel; an upper bracket at the both sides of the gear wheel is provided with a reduction gear and a rocker; both sides of the supporting plate are provided with a movable supporting rod which is matched with the rocker; a wing spar is arranged on the both symmetrical sides of the ornithopter shell in a slant way; the lower part of the movable supporting rod is provided with a controller which stretches out of the front side part of the ornithopter shell; the battery is connected with the electrical motor; the wing comprises a limiting stopper on the wing spar and a flexible wing surface connected with the wing spar; the wing spar and the flexible wing surface form a bird-wing shape; the limiting stopper limits the turning position of the flexible wing surface; and the ornithopter has novel and unique structure, integrates bird flying and ship scull swinging principles in one body, is creative for people flying, has small volume, light weight, low energy consumption, is flexible to fly, and has tremendous significance.

The invention discloses a portable small unmanned aerial vehicle which comprises an unmanned aerial vehicle body and a directional remote handle. Four corners of the unmanned aerial vehicle body are provided with vehicle arm connectors which are tightly welded to the unmanned aerial vehicle body, the ends of the vehicle arm connectors are provided with connecting arms and propellers, and the connecting arms are embedded into the vehicle arm connectors; the propellers are movably connected with the connecting arms through screws, and one ends of the connecting arms are provided with symmetrical storage batteries; an ultrasonic generator is applied so that the distance between the unmanned aerial vehicle and a barrier can be judged through ultrasonic waves, and the application range and the user group of a remote controller receiver can be enlarged; by using a solar electricity generating board, solar energy can be converted into electric energy to be transmitted to the storage batteries, so that a power supply is supplied to flight of the unmanned aerial vehicle, long-time flight of the unmanned aerial vehicle is facilitated, and energy saving is facilitated; and meanwhile, landing supporting feet are applied so that the unmanned aerial vehicle can land whenever and wherever possible.

The invention discloses an air energy high-speed helicopter. According to the air energy high-speed helicopter, a helicopter body is made into a stream-line casing; a storage battery, a controller and instruments and meters are arranged in a cabin in the helicopter body; air pressure, temperature and humidity sensors stretch into the helicopter body; a connection box is connected just above the helicopter body; wings connected with a control motor in the box are arranged on the left and right sides of the connection box; a propeller is respectively arranged on the tip of the left and right wings; hollow shafts of the left and right propellers are connected by using a horizontal hollow shaft and a bevel gear pair which penetrate through the connection box and pass through a middle hole of a rotating shaft of the control motor; the interior of the helicopter body is communicated with the interior of the connection box, each hollow shaft and air ducts in paddles of the propellers through solenoid valves; outlets of the air ducts in the ends of the paddles are perpendicular to rear edges of the paddles; the sensors, the instruments and meters, the storage battery, the control motor and the solenoid valves are all connected with the controller; the propellers rotate by ejecting compressed air injected into the helicopter body from air outlets of the paddles; a vertical swing, a rudder, a horizontal swing and an elevating rudder are arranged at the tail. The wings and propellers thereon are controlled to tilt, and the helicopter can vertically ascend and fly forwards at high speed.