261results about How to "Reduce flight resistance" patented technology

The invention discloses an amphibious unmanned aerial vehicle which comprises a vehicle body and wings. Polygonal drivers are arranged in wing ribs of the wings. Each polygonal driver comprises a polygonal connecting rod mechanism and at least one pneumatic muscle driver. Connecting rods of the polygonal connecting rod mechanisms are connected with the wing ribs. The pneumatic muscle drivers are arranged in polygonal spaces formed by the polygonal connecting rod mechanisms, and the two ends of each pneumatic muscle driver are connected with the connecting rods of the corresponding polygonal connecting rod mechanism. The connecting rod mechanisms are used for connecting and fixing the pneumatic muscle drivers, the pneumatic muscle drivers are inflated and shrink in different directions, so that the connecting rod mechanisms output force in different directions, conversion of a concave wing profile and a convex wing profile is achieved, and the vehicle can meet the requirements for different flight speeds. The wings can intelligently and actively deform to meet the requirements for different navigation speeds, the amphibious unmanned aerial vehicle has the beneficial effects of being amphibious, quick to respond, long in time of endurance, capable of achieving formation flight and the like, and the vehicle can finish the tasks of naval vessel formation convoying, diver resistance, miniature submarine resistance and the like.

The invention provides a multifunctional unmanned plane launch and recovery vehicle which consists of a carrier, a lifting bracket, a gaseous catapult, recovery devices and an unmanned plane transfer box. The bottom of the lifting bracket is connected with the carrier, the gaseous catapult is arranged at the top part of the middle of the lifting bracket through a hinge, the recovery devices are arranged at the two sides of the lifting bracket, and the unmanned plane transfer box is arranged in the middle part of an upper bracket of the carrier. The recovery vehicle successfully solves launch and recovery difficulties which cannot be solved by an unmanned plane. The multifunctional unmanned plane launch and recovery vehicle has the following advantages that: (1) launch, recovery, storage and carrying in vehicle are integrated together, continuous launch and recovery of multiple planes can be achieved, no damage of planes is caused during transport in marching, planes can be launched and recovered at any time, the multifunctional unmanned plane launch and recovery vehicle can be suitable for bad field environment and can be free of ground environment influence; and (2) the flying resistance is low as the unmanned plane has no undercarriage, the unmanned plane does not need to carry a parachute and an anti-drop air sac, the characteristics of large fuel capacity, long cruising time, wide application scope and the like are realized, and good popularization and application values are achieved.

The invention relates to an intake and exhaust device of an air breathing supersonic / hypersonic aerocraft, comprising an inner flow passage arranged at the lower abdomen of the aerocraft; the inner flow passage comprises an intake passage, an isolating section, a combustion chamber and a spray pipe; the intake and exhaust device also comprises an aspirator connected between the intake passage and the spray pipe and a control device for controlling the opening or closing of the aspirator; the control device controls the suction device according to the working conditions of the aerocraft; when the air breathing supersonic aerocraft works on designed points, the control device sends an instruction to close the aspirator; when the air breathing supersonic aerocraft works on non-designed points, the control device sends instruction to open the aspirator; at the moment, an incoming flow is divided into a main flow and a secondary flow, wherein the main flow passes through the inner flow passage; and the secondary flow utilizes pressure difference between a front body and a rear body to form a suction airflow by the aspirator, thus leading the intake passage and the spray pipe to be coupled to a certain degree.

The invention relates to a flapping-wing micro aerial vehicle with renewable energy, and belongs to micro bionic aerial vehicles. A flapping-wing bionic support frame is connected with a motor and transmission mechanism, the motor and transmission mechanism and a control circuit module with an internal micro lithium battery are both fixed on a vehicle rack body, and a solar power generation film empennage is fixedly connected with the vehicle rack body; piezoelectric film flapping wings and solar power generation wing films are connected with a flapping-wing flexible wing frame which is located in the middle, the piezoelectric film flapping wings are located at the bottommost layer, the flapping-wing flexible wing frame is connected with the flapping-wing bionic support frame, and a power generation part is connected with the control circuit module through a wire. The flapping-wing micro aerial vehicle has the advantages that the structure is novel, optical energy can be converted into electric energy on the basis of a photoelectric effect of the solar films, an electricity charging and generating device made of the two materials is simple and has the advantages of being high in conversion efficiency, small in mass, wide in application range and the like.

The invention discloses a full-active cooling hypersonic flight vehicle which comprises a transpiration cooling end, a transpiration cooling wing front edge, a transpiration cooling rudder front edge,a regenerative cooling rudder surface, a regenerative cooling windward side and a flight vehicle leeside, wherein porous structures are formed in the transpiration cooling end, the transpiration cooling wing front edge and the transpiration cooling rudder front edge, and the interiors of the porous structures are filled with liquid cooling media; the liquid cooling media can be supplied outwardsfrom the porous structures, flow through the porous structures to perform heat exchange, are heated and then flow out of the outer surface of the end in a gaseous form; and the regenerative cooling rudder surface and the regenerative cooling windward side are respectively used for cooling the rudder surface and the windward side of the flight vehicle in a regenerative cooling manner, and the liquid cooling media carried inside the flight vehicle are used for blocking, cooling and taking away pneumatic heating volume of the flight vehicle transferred into the flight vehicle in the hypersonic flight process, so that thermal protection requirements of the flight vehicle on high-speed, long-term and long-distance flight in the atmosphere are met.

Disclosed is a rear-placed combustor with an annular porous medium head for an ultramicro turbojet engine. An annular reflux structure is adopted for the combustor which is formed by a combustor box, a flame tube wall, a combustor outlet and the annular porous medium head. Air flow passes through a centrifugal compressor of the engine for compression, enters an annular cavity channel of the combustor, and then is mixed with gas fuel which is jetted in horizontally; premixed gas is pre-heated through the flame tube wall and then flows back to enter a flame tube through the annular porous medium head, and stable ignition is achieved; the whole mixed gas combustion process is finished in the flame tube, and high-temperature gas is discharged from the outlet of the rear-placed combustor; and then the high-temperature gas is discharged into air through a tail pipe after turbine blades of an impact engine does work. The combustor box, the flame tube wall and the combustor outlet are connected through bolts with high temperature glue sprayed on annular edges to guarantee the sealing. According to the combustor, features and advantages of stable flame of the annular porous medium head can be adapted to and played to the greatest extent, proneness to flameout of ultramicro combustors can be improved, so that the combustor can work for the ultramicro turbojet engine reliably and stably.

The invention discloses a truss type wing leading edge camber continuous changing structure, and belongs to the field of design of aircraft wing structure. The structure includes that a wing leading edge cavity enclosed by upper flexible skin and lower flexible skin is internally provided with a plurality of trusses, two ends of each truss are slidingly connected with the upper flexible skin and the lower flexible skin, and the plurality of trusses are mutually hinged and can be linked; each memory alloy rod assembly is composed of a first memory alloy rod and a second memory alloy rod, the first memory alloy rod is heated to extend, and the second memory alloy rod is heated to shorten; the memory alloy rod assemblies are arranged between each two adjacent trusses, and are respectively andevenly distributed along the upper flexible skin and the lower flexible skin; the memory alloy rod assemblies are heated to deform to drive the trusses to move, and make the upper flexible skin and the lower flexible skin deformed. The structure has the advantages of simple mechanism principle, direct stress efficacy and high reliability, and the wing leading edge deformation is flexible, controllable, reversible and repeated intelligent deformation which can continuously change the camber of the wing.

The invention discloses an aerial photography folding wing unmanned aerial vehicle which comprises an airframe and wings. The airframe is provided with an inner cavity; the left side and the right side of the inner cavity are communicated; a first motor is arranged on a front plate of the inner cavity and connected with a lead screw arranged in the same direction as the airframe; gears are symmetrically arranged on the two sides of the lead screw in a meshed mode; the centers of the gears are connected to the airframe through center shafts; rotating plates are connected to the side walls of the gears; supporting plates are perpendicularly connected to the outer ends of the rotating plates; first cylinders are connected to the front ends of the supporting plates; second motors are connected to the front ends of the first cylinders; output shafts of the second motors are connected with first threaded rods; the front plate of the inner cavity is further provided with first nuts screwed to the first threaded rods; the side walls, on the same side as the rotating plates, of the supporting plates are provided with second cylinders. According to the aerial photography folding wing unmanned aerial vehicle, the wings can be folded, storage is convenient, and practicability is achieved.

The invention discloses an ornithopter with combined flapping wings for performing flight control, which is classified as B64C33 / 00 according to international patent technology. The invention relatesto an ornithopter with combined flapping wings for performing flight control. The invention aims to provide a novel aircraft which is cheap, safe, energy-saving, noiseless, pollution-free and comparatively random to take off and land, and becomes more convenient for human medium and short-distance traffic. The ornithopter produces new cognition for the research of flapping wing flight, and uses the characteristic that the flapping wings flap the air to produce a lift force and a thrust and the characteristic that the flapping wings also control the flight at the same time as two aspects to besolved according to the cognition. According to a provided flapping wing combination solution, the continuity that the flapping wings flap the air to produce the lift force and the thrust is greatly improved; and meanwhile, the technical scheme of solving the flight control by using a control plane is provided. The flight principle and structure of the ornithopter determine the application range of a light airplane, and the ornithopter also can be made into a micro unmanned plane to finish aerial detection tasks.

The invention discloses a folding-wing unmanned aerial vehicle for a municipal garden. The folding-wing unmanned aerial vehicle comprises a vehicle body and wings, the vehicle body is provided with an inner cavity, the left side and the right side of the inner cavity are communicated, a first motor is arranged on a front plate of the inner cavity, a lead screw which is arranged in the same direction as the vehicle body is connected to the first motor, gear wheels are symmetrically meshed with the two sides of the lead screw, the center of each gear wheel is connected to the vehicle body through a center shaft, a rotating plate is connected to the side wall of each gear wheel, a supporting plate is vertically connected to the outer end of each rotating plate, a first cylinder is connected to the front end of each supporting plate, a second motor is connected to the front end of the first cylinder, a first threaded rod is connected to an output shaft of the second motor, the front plate of the inner cavity is further provided with a first nut which is screwed with the first threaded rod, and a second cylinder is arranged on the side wall, on the same side of each rotating plate, of the corresponding supporting plate. According to the folding-wing unmanned aerial vehicle for the municipal garden, the wings can be folded conveniently, storage is convenient, and the practicability is achieved.

The invention relates to a wing of an aircraft, in particular to a wing deformation structure of a water and air amphibious aircraft, aiming at solving the problems that the wing, adopting a vertical fin discontinuous deformation structure, of the existing antisubmarine aircraft is poor in stealth performance and aerodynamic performance, has influence on the flight speed and is not beneficial to reduction of radar return signals, and the wing, adopting a structure without a vertical fin, of the existing antisubmarine aircraft is poor in controllability and maneuvering characteristic. The wing deformation structure of the water and air amphibious aircraft comprises a rigidity-variable wing spar, two bending torsion deformation components and two wing ribs; two pneumatic muscle actuators of each bending torsion deformation component are arranged crosswise; the two bending torsion deformation components are respectively arranged at two sides of the rigidity-variable wing spar; two ends of each pneumatic muscle actuator are respectively connected with the two wing ribs; the rigidity-variable wing spar comprises a flexible bearing pneumatic muscle actuator and a wing spar main body; the flexible bearing pneumatic muscle actuator is inserted into a tubular elastic beam; two ends of the tubular elastic beam are respectively connected with the two wing ribs. The wing deformation structure is used for the water and air amphibious aircraft.

The invention discloses a flying robot with variable sweep angle launch tandem wings and aims to solve the problem that neither two front folding wings nor two rear folding wings of an existing launch flying robot can be unfolded respectively, so that moving attitude control of the flying robot is limited. The flying robot comprises a folding propeller, a fuselage, a left rear wing, a right rear wing, a left front wing, a right front wing, two vertical tails, two vertical tail pin shafts and four rotary hinges, wherein the folding propeller is installed on the head of the fuselage, the left front wing and the right front wing are symmetrically arranged on the two sides of the front end of the fuselage, the left rear wing and the right rear wing are symmetrically arranged on the two sides of the rear end of the fuselage, the left front wing, the right front wing, the left rear wing and the right rear wing are hinged to the corresponding rotary hinges respectively, each rotary hinge is connected with a corresponding helm gear in the fuselage, and the two vertical tails are symmetrically arranged on the two sides of the tail end of the fuselage and installed on the upper surface of the tail portion of the fuselage through torsional springs. The flying robot is used for attitude control.

The invention relates to a layout and control method of a tilting rotor-wing vertical take-off and landing aircraft. Tandem wing layout is adopted; the wing tips of two sides of front wings and rear wings are each provided with one set of rotor wings, and altogether, four sets of rotor wings are adopted, so that a power system can be formed; the wings and the rotor wings can rotate around rotatingshafts penetrating through the interiors of the wings within a certain angle range, so that the respective tilting of the rotor wings and the wings is achieved. According to the control method, the vertical take-off and landing and high-speed level flight of the aircraft can be achieved; the angles of the rotor wings and the wings can be properly adjusted in all stages of flight, and the overallefficiency of the aircraft is optimized; the rotor wings and the wings can tilt respectively, resistance is small in vertical take-off and landing stages, and airflow interference between the rotor wings and the wings is small; when the aircraft is switched between a vertical take-off mode and a landing mode, the utilization efficiency of the wings is high, the burden of the power system is low; and flight control over a whole flight process is simple. The vertical take-off and landing aircraft has a wide application prospect.

The invention discloses an aerial cloud platform for shooting in all directions. The aerial cloud platform comprises a casing, a camera group and a controller used for controlling the operation of the camera group, wherein the camera group comprises a first camera fixedly mounted in the casing, more than one rotary camera movably arranged below the casing, and a driving mechanism used for driving the rotary cameras to rotate along a horizontal plane; the optical axis direction of the first camera is vertically downward; each rotary camera comprises a camera casing, and a second camera obliquely arranged in the camera casing; a shooting hole corresponding to the lens of the second camera is formed in the camera casing; the optical axis direction of the second camera is vertically downward and forms an included angle with the optical axis direction of the first camera; the driving mechanism comprises a motor, and a transmission mechanism connected with the motor and the rotary cameras. The aerial cloud platform has a simple structure, can flexibly control the shooting angle of the second camera, has good anti-vibration property, guarantees the shooting quality, and is good in leakproofness, waterproof and dustproof, and compact in structure.

An aerial wind-energy power-station aircraft relates to the technical field of engineering such as manufacture of power-driven aircrafts, aerial wind power and photoelectricity, aerial transportation and military affairs. The aircraft comprises an aircraft body (1) or a buoyancy lift body (20), a control system (4) and a propelling system (5). The aircraft is characterized in that the aerial wind-energy aircraft also comprises an aerial wind power generation system (2), a storage system (3) of power electric energy and a grounding and water-connecting system (6), wherein the power propelling system (5) comprises an electric propelling flight system (5.1). When the grounding and water-connecting system (6) is connected to an easy-to-connect ground object (12), an aerial fixation aircraft device (13) and a water body (14), the system stays at a stationary state and can start aerial wind-power generation. When the storage system (3) of the power electric energy is filled with aerial wind electricity, the electricity can then be supplied to the electric propelling flight system (5.1), so that flight can be driven. In this way, no fuel is consumed, and the flight can be implemented by ''aerial wind energy and wind electricity''. The aircraft has a very low cost; and by the storage system (3) of the power electric energy or the aerial fixation aircraft device (13), the aerial wind electricity with the very low cost can also be conveyed to the ground for utilization.

The invention discloses an intra-shaft operation rotor wing device, and belongs to the technical field of controlling rotor wings of helicopters. The intra-shaft operation rotor wing device comprises a rotating ring and fixed ring component, an anti-twist pull rod component, a steering engine, a support component, an upper collective pitch slide block, a lower collective pitch slide block, an upper collective pitch bolt, a lower collective pitch bolt, and a variable-torque pull rod component, wherein the variable-torque pull rod component is fixed on a main rotor wing shaft by virtue of the upper collective pitch bolt and the upper collective pitch slide block, and the upper collective pitch slide bock is inlaid at the upper end of the main rotor wing shaft and can slide up and down; the rotating ring and fixed ring component is fixed at the lower end of the main rotor wing shaft by virtue of the lower collective pitch bolt and the lower collective pitch slide block, and the lower collective pitch slide block is inlaid at the lower end of the main rotor wing shaft and can slide up and down; and the rotating ring and fixed ring component is arranged at the lower part of a main speed reducer and is connected with a rotor wing propeller hub by virtue of the variable-torque pull rod component, and the anti-twist pull rod component and the steering engine are fixed on the rotating ring and fixed ring component. The intra-shaft operation rotor ring device disclosed by the invention adopts an intra-shaft operation transmission mode to reduce sizes and weights of components, and is also beneficial for reducing flight resistance of a helicopter.

The invention provides a coaxial double-propeller vertical take-off and landing aircraft adopting moving core control and a control method. The aircraft comprises a machine body and a coaxial double-propeller mechanism; the machine body is of a columnar structure, and a flight control and communication device, and a task load and a power battery are contained in the machine body; and the power battery is arranged on a metamorphic core driving mechanism inside the machine body and can drive the power battery to move in the radial direction of the machine body, so that the gravity center of theaircraft is deviated from the center axis of the machine body; and the coaxial double-propeller mechanism comprises an upper and lower double-rotor motor, a foldable upper propeller and a foldable lower propeller. According to the aircraft, a propeller blade is small and portable after being folded, flight control is carried out by dynamically changing the mass center of the aircraft by adopting abuilt-in metamorphic core driving control device, no additional control device is additionally arranged outside the machine body during flight, and the flying resistance is small. The power battery is used as a moving mass of the metamorphic core without other additional weighting amount, the required operating force and torque required by mass movement are small, and the power requirement and the weight of a steering engine can be reduced.

The invention discloses an environment-friendly unmanned aerial vehicle for constructional engineering. The environment-friendly unmanned aerial vehicle for constructional engineering comprises a vehicle body, a tail wing and vehicle wings and is characterized in that the vehicle wings are connected with the vehicle body through a folding mechanism; an undercarriage is arranged below the vehicle body and comprises an installation seat connected to the position below the vehicle body, a third rotary shaft arranged on the installation seat, a supporting column, a buffer spring, a cross beam, a supporting beam, two supporting legs and two connecting rods; the upper end of the supporting column penetrates the cross beam and is fixedly connected with the third rotary shaft; the lower end of the supporting column is inserted on the supporting beam; the supporting beam can move linearly along the supporting column; the supporting column is sleeved with the buffer spring; and the buffer spring is located between the cross beam and the supporting beam. By the adoption of the environment-friendly unmanned aerial vehicle, due to the fact that the undercarriage is arranged below the vehicle body, a buffering effect can be achieved in the taking-off and landing processes, and the vehicle body is protected against damage.

The invention discloses a parallel thrust vector exhaust system based on a throat offset type pneumatic vector spray pipe. The system comprises the throat offset type pneumatic vector spray pipe and an adjustable Laval spray pipe arranged on the outer side of the throat offset type pneumatic vector spray pipe, through an inner and outer nested parallel structure, the thrust vector is generated by the throat offset type pneumatic vector spray pipe, and the flow regulation function is realized by the Laval spray pipe connected in parallel on the outer side. According to the parallel thrust vector exhaust system based on the throat offset type pneumatic vector spray pipe, different functions of the spray pipes are realized by utilizing different parts, so that the spray pipes have the characteristics that the thrust vector is efficient, the wide-range flow is adjustable, and infrared signals are reduced; and the smooth transition molded surface is designed, so that the exhaust system has relatively good thrust performance and vector performance at the same time in a wide working range, then the evolution of a fixed geometric thrust vector spray pipe is realized, the flight envelope of an aircraft is expanded, and the use requirements of the aircraft are better met.

The invention discloses an induction power take hook applicable to a micro unmanned aerial vehicle and relates to the technical field of electromechanical design. The induction power take hook comprises a connecting rod mechanism, a driving system and a control system. By reasonable design, the connecting rod mechanism can realize that the unmanned aerial vehicle can be hooked on a power transmission line to acquire power, the driving system is used for driving the connecting rod mechanism to fold and unfold, and the control system is used for controlling the working status of the driving system. By the foldable design, the induction power take hook can be folded at ordinary times and unfolded in use, and accordingly flight resistance is reduced beneficially; automatic hooking action and gravity-based self-locking can be realized. Meanwhile, the induction power take hook is compact and simple in structure, and structural weight is reduced beneficially. The unmanned aerial vehicle is supplemented with energy from the power transmission line through induction power take, and an airborne mission system can work normally; the connecting rod mechanism can be extended independently for use, and the capability of largely capturing the target power transmission line is realized.

The invention discloses an intelligent unmanned aerial vehicle for municipal landscaping, which comprises a body, wings and an empennage, wherein an inner cavity is formed in the body, the left and right sides of the body are through, a motor is arranged on a front plate of the inner cavity, the outlet end of the motor is connected with a vertical lead screw, a driving plate is installed on the lead screw in a rotating manner, two first through holes are symmetrically formed in the driving plate, a guide rod is installed in the first through holes, one end of the guide rod is fixed on the front plate of the inner cavity and is parallel to the lead screw, the motor drives the driving plate to move along the length direction of the guide rod via the lead screw, the wing is connected to the inner cavity through a rotary shaft, one side, close to the lead screw, of the wing is provided with a connection rod, and a sliding post is arranged at the outer end of the connection rod, and is installed in a first sliding groove of the driving plate. The intelligent unmanned aerial vehicle is convenient to put away as the wings can be folded easily, and thus has practicability.

The invention discloses a throat offset type pneumatic vector spraying pipe with a parallelogram section. A spraying pipe inner runner comprises a spraying pipe inlet, an equal straight segment, a first-throat front convergent section, a first throat, a second-throat front expanding segment, a second-throat front convergent section and a second throat which communicate in sequence; an inclined side wall face begins to be arranged on a certain position in the inner runner, the circulation section from the inner runner to the second throat is in a parallelogram shape, through the shape design ofthe parallelogram circulation section, the good airflow mixing effect is obtained, the spraying pipe infrared hidden property is effectively improved, meanwhile, the large thrust vector angle is provided for an aircraft still, the inclined side wall face has the offset effect on the airflow, under the vector and non-vector state, the initial pitching and yaw vector angles exist, the requirement of pneumatic-hidden integrated layout of the future aircraft can be met, and the purpose is wide.

The invention discloses a variable-area canard forward-swept wing morphing aircraft which adopts a canard layout. The plane shape of an airfoil is quadrilateral, and when wings are completely retracted, the wings and a canard wing are connected to form a delta wing. The canard wing is arranged at the head of a fuselage. The wings on the two sides of the tail of the fuselage can be synchronously folded forwards towards the inner fuselage side around a wing body connecting rotating shaft or unfolded backwards towards the outer side. When the wings are folded forwards, the wings are gradually folded forwards to reduce the sweepforward angle, the wings are completely attached to the fuselage, and the whole aircraft is of a curved streamline aerodynamic configuration. When the wings are completely unfolded into forward-swept wings, the wing span of the aircraft is greatly increased, so that the aircraft can ensure large lift force. Double vertical tails are symmetrically arranged on the rear portion of the fuselage, lifting ailerons are installed at the rear end of the fuselage and located on the rear portions of the two vertical tails, and an air inlet channel is located below the fuselage. Through reasonable cooperation of the variable-area canard forward-swept wing variants, the aircraft has small flight resistance when the wings are in the unfolded state and the folded state, and the flight flexibility of the aircraft is improved.

The invention relates to the field of unmanned aerial vehicles, in particular to a flight control system of a wing-layout-hidden unmanned aerial vehicle and a control method of the flight control system, aiming to solve the problems of poor flight stability and low operation efficiency of an existing wing-layout-hidden unmanned aerial vehicle. First control surfaces respectively arranged at rear edges of a left first wing section and a right first wing section, a second control surface and a third control surface respectively arranged at rear edges of a left second wing section and a right second wing section, and fourth control surfaces respectively arranged on upper surfaces of the left second wing section and the right second wing section cooperatively act, so control on various flight attitudes of the unmanned aerial vehicle is realized, the flight stability is good, and the operation efficiency is high.

The invention provides a system and method for controlling feathering mode of a multi-rotor electric propeller in a hybrid aircraft and belongs to the field of hybrid aircrafts. The system comprises a flight control system, two rotor arms, photoelectric sensors symmetrically mounted at two ends of the rotor arms, direct-current brushless motors, and a direct-current brushless electronic speed control; a rotor propeller is fixedly mounted above each direct-current brushless motor; the rotor propellers rotate with the direct-current brushless motors; the photoelectric sensors judge whether the rotor propellers are in feathering position or not according to whether light emitted is reflected or not, and output high and low level signals to the flight control system in order to perform detecting and logic computing, the flight control system outputs a corresponding control signal to the direct-current brushless electronic speed control, and the speed of the direct-current brushless motors is further controlled. Through the system and method, the positions of the rotor propellers can be adjusted fast, power loss due to poor blade position is reduced, flight drag is reduced, and flight efficiency of the aircraft is improved.

The invention provides a self-adaptive rhombic wing layout of air vehicles. According to the self-adaptive rhombic wing layout of the air vehicles, a nose, a tail, four wings, an engine, a task bin, four connecting arms, hinges and control vanes are involved. The four wings are arranged in a rhombic mode from front to back. The four connecting arms can be telescoped and are transversely or longitudinally arranged in a crisscross mode. The nose and the wings are connected through the hinges, the tail and the wings are connected through the hinges, and the engine and the wings are connected through the hinges. The task bin is connected with the nose, the tail and the engine through the telescopic connecting arms and can be changed according to task requirements. The wings are provided with the control vanes used for controlling flight attitudes. The sweepback angle and the sweep-forward angle of the wings can be changed by telescoping the connecting arms so as to obtain rhombic wing layouts adapting to different flight speeds and improve the aerodynamic performance. The self-adaptive rhombic wing layout of the air vehicles has the advantages of being simple and reliable in structure, low in cost and multiple in function.

The invention discloses wings and a transmission mechanism of an ornithopter. Each of the wings of the ornithopter is divided into an inner wing panel, a middle wing panel and an outer wing panel; the transmission mechanism drives a crankshaft through a motor; the crankshaft drives a linkage; one end of a stator passes through a gap at the middle of the linkage, and the other end of the stator is fixed onto a body; the front end of the linkage is connected with certain ends of inner sides of inner wing panel rear skeletons respectively; the inner wing panel rear skeletons pass through the body outwards and take the body as a pivot; the certain ends of outer sides of the inner wing panel rear skeletons are connected with lower end vertexes of inner sides of rectangular skeletons, which can be changed into rhombuses, of the middle wing panels; certain ends of inner wing panel front skeletons are fixed on the body, and the other ends of the inner wing panel front skeletons are connected with upper end vertexes of the inner sides of the rectangular skeletons, which can be changed into the rhombuses, of the middle wing panels, and under the combined action of the inner wing panel front skeletons and the inner wing panel rear skeletons, forms can be changed continuously; outer wing panel shape-preserving wings are connected with the outer sides of the middle wing panel through hinges, and angle limitation devices on the hinges of the outer wing panel are used for limiting the oversize lifting angle of the outer wing panel; through adoption of the way, the movement of the ornithopter can present the states of birds in a flying process.

The invention discloses a miniature vertical take-off and landing flapping-wing aircraft, and belongs to the technical field of flapping-wing aircrafts. The aircraft comprises an aircraft body, a flight control system, a steering engine, a double-wing flapping wing device and a tail vane. The double-wing flapping wing device is arranged at the upper part of the aircraft body, and the tail vane isarranged at the lower part of the aircraft body. The double-wing flapping wing device comprises a flapping wing driving part and a flapping wing synchronous movement mechanism which are mounted on a rack. The flapping wing driving part comprises a motor and a reduction gear set, the motor is in meshed connection with an input end gear of the reduction gear set through a motor shaft gear arranged on a rotating shaft of the motor, and the flapping wing synchronous movement mechanism comprises a flapping wing and a pair of flapping wing driving structures of the same structure. The flapping wingcomprises a flapping wing rocker arm and two pairs of flexible flapping wings. The flapping wing driving structure comprises an eccentric shaft mounting gear, an eccentric shaft and a connecting rod.The cross-shaped supporting tail vane comprises a longitudinal fixed rudder plate and a transverse adjusting rudder plate, and the longitudinal fixed rudder plate and the transverse adjusting rudder plate are vertically downward and are arranged in a cross mode. The aircraft has the characteristics of convenient take-off and landing, low energy consumption and the like.

The invention discloses an engineering investigation unmanned aerial vehicle system based on satellite positioning and navigation and an investigation surveying and mapping method. The engineering investigation unmanned aerial vehicle system comprises an unmanned aerial vehicle body, supporting arms, propellers, undercarriages, a transportation device, a sampling device, a power supply, a monitoring device and a workstation. The unmanned aerial vehicle body internally comprises a navigation positioning module, an environment detection module, a survey lofting module, a survey work monitoring module, a wireless communication module, a transportation module, a sampling module, a text image recognition module, a flight control module, an anti-collision protection module, a power supply module, a memory and a loss finding module. According to the invention, an advanced positioning navigation technology, a remote sensing image technology, a radar technology, a flight control technology, a real-time aerial image voice communication technology, an intelligent investigation technology, a text image recognition technology and a wireless transmission technology are adopted; geotechnical engineering investigation and high and new technologies are combined, and multiple important functions such as investigation automatic measurement and lofting, coordinate elevation remeasurement, drillingmachine navigation reminding, investigation work quality progress deviation rectification, automatic transportation and sampling, man-machine interaction, text image automation and unmanned aerial vehicle loss finding are achieved.

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.