77results about How to "Guaranteed normal flight" patented technology

The invention discloses an air safety monitoring method for an unmanned aerial vehicle. The method comprises the following steps that: firstly, an enterprise having the unmanned aerial vehicle applies for air route registration to a flight range management department; secondly, the flight range management department transmits a register account number and a password to the enterprise after approving the application; thirdly, the enterprise logs on an air route management server by using the applied account number and password to apply for a required flight range and the longitude and the latitude of a route; fourthly, the air route management server sends a license file to the enterprise after verification; fifthly, the enterprise receives the license file, makes confirmation and installs the license file in a control box of the unmanned aerial vehicle; and finally, the unmanned aerial vehicle acquires current data of the longitude and the latitude during a flying process through a global positioning system installed on the unmanned aerial vehicle, compares the current data with the longitude and the latitude applied in the license file, sends an alarm signal in case of deviation and returns to an original place. Due to the adoption of the method, the flight path of the unmanned aerial vehicle can be managed, monitored and controlled.

The invention discloses a method for aerially photographing a crop canopy picture for crop nitrogen analysis and soil fertilization guidance by using an unmanned aerial vehicle. The crop canopy picture is aerially photographed through the unmanned aerial vehicle, meanwhile, aerial latitude and longitude corresponding to the crop canopy picture are obtained, and crop nitrogen analysis and soil fertilization guidance are carried out by combining picture information and latitude and longitude information. According to the obtained method, large-area farmland information can be quickly obtained, influence and limitation of crop growth and farmland environments are avoided, a crop nitrogen state is diagnosed by using color parameters of the picture and the nitrogen fertilizer topdressing index is recommended, the method is accurate and reliable, accurate management of a nitrogen fertilizer is facilitated and better economical and ecological benefits are achieved. The method is fast and simple in operation, stable and reliable in structure, low in operation cost and beneficial to farmland application and popularization; and fine farming of the farmland can be significantly promoted. The aerial photograph equipment of the unmanned aerial vehicle is simple in structure and beneficial to efficient and stable aerial photographing of the crop canopy picture.

The invention provides a multiple-unmanned aerial vehicle collaborative area searching method under the communication constrains. The method comprises the following steps of: firstly setting an initial position of multiple unmanned aerial vehicles, parameters of the communication constrain condition and search finishing time, selecting a point with the minimum cost as a next way-point position of all unmanned aerial vehicles, and judging whether the way point meets the boundary constraint condition; when one unmanned aerial vehicle flies to the way point meeting the boundary constraint condition, judging whether other unmanned aerial vehicles are in the communication distance range of the unmanned aerial vehicle, and exchanging probability graph data with the unmanned aerial vehicle with closest distance; and finally, calculating the area coverage rate and judging whether the search finishing time is reached. The multiple-unmanned aerial vehicle collaborative area searching method has the advantages that the influence of the communication constrain on the multiple-unmanned aerial vehicle cooperative system can be eliminated or weakened, the multiple unmanned aerial vehicles can finish the search task at minimum cost and the coverage rate of the search area is increased.

The invention relates to a wireless charging system and a wireless charging method of an unmanned aerial vehicle. The wireless charging system comprises an electric-collecting unmanned aerial vehicle and a wireless charging device, wherein the electric-collecting unmanned aerial vehicle comprises a first communication module for transmitting charging request information to the wireless charging device; the wireless charging device comprises a second communication module and a plurality of electric-supply unmanned aerial vehicles; the second communication module is used for receiving the charging request information from the electric-collecting unmanned aerial vehicle, and is also used for transmitting a travelling command to an idle electric-supply unmanned aerial vehicle; and each electric-supply unmanned aerial vehicle is used for synchronously flying with the electric-collecting unmanned aerial vehicle and performing wireless charging on the electric-collecting unmanned aerial vehicle after the travelling command is received. According to the wireless charging system and the wireless charging method disclosed by the invention, the charging requirements of a plurality of electric-collecting unmanned aerial vehicles can be met at the same time; the electric-supply unmanned aerial vehicles adopt a charging manner of synchronous flying, so that charging delay of the electric-collecting unmanned aerial vehicle is greatly reduced; and the electric-supply unmanned aerial vehicles adopt a wireless charging manner to provide electric quantity for the electric-collecting unmanned aerial vehicle, so that the problem that electric leakage and electric shock are liable to generate caused by that a plug is exposed is effectively solved.

The invention provides a polymer-thickened non-Newton aircraft deicing / anti-icing liquid, comprising the following components based on weight percentages: 45%-65% of freezing point depressant, 0.05%-5% of thickening agent, 0.05%-5% of neutralizing agent, 0.05%-5% of viscosity control agent, 0.05%-5% of corrosion inhibitor, 0.05%-5% of surfactant, and the balance liquid. The preparation method of the invention comprises: sequentially adding the freezing point depressant, the thickening agent, the neutralizing agent, the viscosity control agent, the corrosion inhibitor and the surfactant to solvent, respectively stirring and dissolving to obtain the product. The polymer-thickened non-Newton aircraft deicing / anti-icing liquid has the characteristics of high apparent viscosity, slowly reduced viscosity after shearing treatment, excellent anti-icing property and good dynamic performance. After anti-icing treatment via the product, the outer surface of an aircraft can not be refrozen and frosted within a very long time range, thus effectively avoiding a refreezing phenomenon of the aircraft during the delay period in an airport, and guaranteeing normal flight of the aircraft under an ice and snow weather.

The invention provides a hybrid power tail sitting type vertical takeoff and landing long-endurance unmanned aerial vehicle and a flight control method thereof. The unmanned aerial vehicle comprises a fuselage, wings, a main driving motor, propellers, a piston power ducted propeller and tail wings mounted on a duct. According to the invention, two sets of power systems, namely a motor and a piston engine, are adopted; in a vertical takeoff and landing stage which is short in time and requires large power, the motor serves as driving power, the advantage of high power-weight ratio of the motor can be fully exerted, and thus the weight of the power systems is reduced; in a cruising flight stage, the tail piston engine and the ducted propeller system driven by the tail piston engine drive the unmanned aerial vehicle to fly forward, and the piston power and the ducted propeller system can be selected and designed according to the optimal cruising state without considering the vertical takeoff and landing state, so that the fuel consumption rate of the cruising state can be effectively reduced; in combination with high-aspect-ratio wings, long-time flight of the unmanned aerial vehicle can be ensured; and meanwhile, because the weight of the power systems is reduced, the empty weight ratio of the unmanned aerial vehicle can be reduced, and the loading capacity of the unmanned aerial vehicle can be effectively improved.

The invention discloses a manned unmanned aerial vehicle offline state automatic control method and a manned unmanned aerial vehicle, relates to the technical field of the unmanned aerial vehicle, andmainly aims at realizing autonomous flight control of the manned unmanned aerial vehicle, enhancing the safety of the manned unmanned aerial vehicle and guaranteeing the accuracy of flight schedulingof the manned unmanned aerial vehicle within the airspace. The method comprises the steps that when communication between the manned unmanned aerial vehicle and the ground control station is interrupted, the offline flight state is started and the flight height is adjusted to the preset safety flight height; hovering in the air corresponding to the preset safety flight height is performed and requesting to the ground control station for recovering communication; if stable communication with the ground control station is not recovered within the preset time period, autonomous return flight isstarted; and if stable communication with the ground control station is successfully recovered, the offline flight state is stopped and flight control of the ground control station to the ground control station is recovered. The manned unmanned aerial vehicle offline state automatic control system and method are suitable for flight control of the manned unmanned aerial vehicle.

The invention discloses a satellite dynamic and static balance test and adjustment device, comprising: a satellite body to be tested is fixed on a satellite connection disc. The satellite connecting disk is connected with the plane of the connecting disk of the dynamic balancing machine, and is fixed with positioning pins to form a transitional tooling. The transition tooling can move horizontally in X and Y directions on the dynamic balancing machine. The connecting disc of the dynamic balancing machine is fixed on the plane of the dynamic balancing machine with connecting bolts, and there is an adjusting gasket in the middle. A fixed support is installed on one side of the planar main table of the dynamic balancing machine, and an adjusting screw is arranged on it. The invention also discloses the test and adjustment method of the dynamic and static balance test and adjustment device, adopts the technical scheme of "torque-couple balance method", and achieves the problem of completing the satellite dynamic and static balance test and adjustment at one time, which not only improves the efficiency of test and adjustment Accuracy, and the adjustment time is reduced from 7 days to 2 days.

The invention discloses a method for controlling double UAVs to cooperatively hoist a rod-shaped rigid load, and provides the modeling and control method aimed at a double UAV cooperative hoisting system in a plane. A complete system dynamic model is established by using a Lagrange modeling method, and the relative kinematic relationship between the two rotor UAVs and a load is analyzed. On the basis of the established model, a Lyapunov method is used for designing a controller, an outer loop stability analysis is carried out by combining a Lassalle invariance principle, and then a conclusionthat an expected balance point is asymptotically stable is obtained. According to the control scheme, the UAVs can be prevented from colliding with each other, a hoisting task is stably completed, fixed-point hovering is achieved, and swinging of the load is inhibited. According to an experiment result, the control objective can be completed, the two UAV are ensured to fly with respective expectedranges, and load swinging can be effectively inhibited.

The invention discloses a hybrid power long-endurance multi-shaft air vehicle. The hybrid power long-endurance multi-shaft air vehicle comprises a device installing platform. A fuel engine is fixed to the device installing platform, and a flight rotor wing used for producing lift force is arranged on a rotating outputting shaft of the fuel engine. A plurality of posture adjusting rotor-wing installing arms are arranged on the periphery of the device installing platform in a radial mode, the tail ends of the posture adjusting rotor-wing installing arms are fixedly controlled by reverse torsion adjusting steering engines of an air vehicle posture control system, direct current motors are vertically fixed to angle adjusting motor fixing supports of the reverse torsion adjusting steering engines, and posture adjusting rotor wings are arranged on rotating outputting shafts of the direct current motors. Air vehicle supporting foot frames are arranged below the device installing platform. The hybrid power long-endurance multi-shaft air vehicle has the advantages that the structure is reasonable, the weight is small, and cruising capacity is high.

The invention discloses a multifunctional plant protection unmanned aerial vehicle which comprises an unmanned aerial vehicle body and a pesticide application box. Arms are mounted on two sides of theunmanned aerial vehicle body, spraying rods are connected at the bottoms of the arms through telescopic hanging rods, a pesticide box mounting frame is fixed at the bottom of the unmanned aerial vehicle body, an anti-vibration inner frame is connected on the inner side of the pesticide box mounting frame through a buffer spring, the pesticide application box is arranged in the anti-vibration inner frame, and a hydraulic cylinder is mounted on the inner side wall of the anti-vibration inner frame and connected with a clamping plate through a hydraulic telescopic rod. The unmanned aerial vehicle is simple in structure, multifunctional and high in practicability, the hydraulic telescopic rod is matched with the clamping plate, the pesticide application box can be rapidly fixed into the anti-vibration inner frame and is conveniently assembled and disassembled, time and labor are saved, the anti-vibration inner frame is connected with the pesticide box mounting frame through the buffer spring, shaking generated by the pesticide application box in pesticide application process can be effectively buffered and reduced, unstable flight of the unmanned aerial vehicle caused by shaking of the pesticide application box is avoided, and stable flight of the unmanned aerial vehicle is ensured.

The invention relates to an energy-saving unmanned aerial vehicle with a protection function. The energy-saving unmanned aerial vehicle comprises a main body, a plurality of supporting units, a plurality of signal collecting units, a plurality of flying units, an wind plate rotating mechanism and a protection mechanism, wherein the multiple supporting units are arranged under the main body, the multiple signal collecting units and the multiple flying units are arranged on the main body, and the wind plate rotating mechanism and the protection mechanism are arranged on the main body. The signal collecting units are uniformly distributed on the main body in the circumferential direction. Each signal collecting unit comprises a camera and a wind direction detection unit. The flying units are uniformly distributed on the outer side of the main body in the circumferential direction. The energy-saving unmanned aerial vehicle with the protection function detects the wind direction through the wind direction detection units, according to the flight requirement, the wind plate rotating mechanism is utilized to adjust a wind plate to an appropriate position, and the wind direction is matched, so that the energy resource of flight consumption is reduced, and the practicality of equipment is improved; and besides, whether birds get close and invade or not is detected through the cameras, the protection units rotates flash lamps to be aligned to the birds to flash continuously, accordingly the birds are scared away, and normal flight of the unmanned aerial vehicle is guaranteed.

The invention belongs to the field of electromagnetic valves, and provides a pneumatic electromagnetic valve and a flight vehicle. A liquid outlet of the pneumatic electromagnetic valve is connected with the flight vehicle, the pneumatic electromagnetic valve comprises a gas inlet part, a liquid inlet part and a fixing part, the gas inlet part is provided with a gas inlet, the liquid inlet part comprises a first cavity and a first valve core, the first cavity communicates with the gas inlet through a first channel, and the first valve core can move in the first cavity so as to open or close aliquid outlet; the fixing part comprises a second cavity, a clamping rod, a first blocking piece and a second channel, the second cavity communicates with the first cavity through a third channel, andthe clamping rod and the first blocking piece are located at the two ends of the second channel correspondingly; a clamping groove is formed in the first valve core, when the first blocking piece isdetached, the clamping rod can move in the second cavity to penetrate through the clamping groove, and the first valve core is fixed to the first cavity so as to keep the liquid outlet to be open; andwhen the clamping rod is detached, the first valve core is introduced along with the gas so as to open the liquid outlet, or is discharged along with the gas so as to close the liquid outlet. The different demands of the flight vehicle under different states can be met.

The invention relates to a substation unmanned aerial vehicle tour inspection system and method. The substation unmanned aerial vehicle substation inspection system comprises an unmanned aerial vehicle body, a carrier-free communication positioning device, a preset icon, an icon recognition device and a ground control station. The carrier-free communication positioning device is arranged on the unmanned aerial vehicle body. The preset icon is laid at a preset position. The icon recognition device is arranged on the unmanned aerial vehicle body and used for recognizing the preset icon to obtainrecognition information. And the ground control station is in communication connection with the unmanned aerial vehicle body, the carrier-free communication positioning device and the icon recognition device, and is used for receiving position information and identification information and sending a control instruction to the unmanned aerial vehicle body according to the position information andthe identification information. According to the substation unmanned aerial vehicle tour inspection system provided by the invention, the unmanned aerial vehicle body can be precisely positioned, so that the unmanned aerial vehicle body can fly according to a preset flight path.

The invention discloses a dust removal unmanned aerial vehicle and a dust removal method, and belongs to the field of unmanned aerial vehicles. The dust removal unmanned aerial vehicle comprises an unmanned aerial vehicle body, and a dust collection device arranged above the unmanned aerial vehicle body, wherein the unmanned aerial vehicle body comprises a supporting frame and a plurality of rotorwings surrounding the circumference of the supporting frame; the dust collection device comprises a shell, an opening and closing assembly and a dust collection box, wherein the shell is arranged above the supporting frame and has a containing cavity; the opening and closing assembly is contained in the shell; the dust collection box is contained in the shell, wherein a plurality of dust collection holes are further formed in the periphery of the shell, and the opening and closing assembly and the dust collection holes are communicated with the dust collector box, wherein the rotor wings arecontained in the shell; and the dust collection box is communicated with the rotor wings. The rotor wings are used for forming negative pressure in the dust collection device to enable the dust collection holes in the shell to suck air, the air flow formed in the air suction process is utilized to achieve the dust removal effect, dust is collected by the dust collection box, dust is prevented fromfalling on the rotor wings, the supplemented air inlet amount of the rotor wings is controlled through the opening and closing assembly, and the effect of adjusting the dust suction power is achieved.

The invention relates to a power supply method for a drone with multiple battery packs. The drone includes a drone body, a drone power supply system includes a power module and a mainboard control module for controlling the operation of the power module, and the power module includes a plurality of battery assemblies which are connected in parallel. The method comprises the following steps that S1, the battery assemblies are numbered as the first battery assembly, the second battery assembly, ... and the nth battery assembly separately in a use order; S2, the motherboard control module startsthe first battery assembly according to the numbering sequence; S3, when the electric quantity of the first battery assembly is equal to or less than a critical electric quantity value, the mainboardcontrol module controls the first battery assembly to stop working and simultaneously starts the second battery assembly; S4, when the electric quantity of the second battery assembly is equal to or less than the critical electric quantity value, battery switching is performed according to the method in step S3 until the nth battery assembly is started; S5, when the remaining electric quantity ofthe nth battery assembly is equal to or less than a return electric quantity value, the mainboard control module controls the drone to automatically return.

The invention discloses a throwing device applied to a water rescue unmanned aerial vehicle system. The throwing device comprises a support, a suspension assembly and a limiting assembly; the suspension assembly comprises a suspension part and a driving part, wherein the suspension part is used for suspending rescue materials; the suspension part is arranged at the lower end of the middle of the support; the driving part is arranged on the support, is connected to the suspension part and is used for driving the suspension part to be opened and closed; the limiting assembly comprises at least two limiting parts used for limiting shaking of the rescue materials; and the limiting parts are arranged at the lower end of the edge of the support. According to the throwing device, the suspension assembly is arranged at the lower end of the middle of the support, the at least two limiting parts are arranged at the edge of the support, the rescue materials can be fixed through the suspension part located in the middle and then are limited through the limiting parts located at the edge so as to prevent the rescue materials from shaking, so that only one driving part needs to be arranged to drive the suspension part to be opened and closed so as to complete suspension and throwing of the rescue materials, one suspension point and two limiting points are arranged, so that the rescue materials can fall stably in the throwing process, and therefore the flight of an unmanned aerial vehicle is guaranteed, and suspension of the rescue materials is also facilitated.

The invention discloses a rudder for rapidly turning the flight direction of an aircraft, the invention relates to the technical field of rudder, The left side of the inner wall of the cavity is fixedly connected with the left side of the placing block, the right side of the placing block is overlapped with the left side of the U-shaped plate through a buffer, and the left side of the U-shaped plate is fixedly connected with the right side of the placing block through two electric pushrods. The vertical tail comprises a vertical tail, a right side of which is provided with a cavity, and the left side of the cavity is fixedly connected with the left side of the placing block through a buffer. The rudder that quickly turns the plane 's flight direction, Through the electric push rod, Place blocks, U-plates, shaft, first bearing, The second bearing, the motor, the first gear and the second gear are matched, so that the heading of the aircraft can be controlled, the rotational amplitude ofthe moving wing surface can be enlarged, the contact area with the airflow can be enlarged, sufficient torque can be generated, the heading of the aircraft can be controlled conveniently, and the normal flight of the aircraft can be ensured to a certain extent.

The invention discloses a mining rescue unmanned aerial vehicle. The unmanned aerial vehicle comprises a vehicle body, a main controller, power devices, protective net covers, a storage box, a camera,and a battery, wherein the main controller is arranged in the vehicle body and is in wireless communication connection with an external wireless remote controller; the multiple power devices are evenly distributed on the two sides of the vehicle body and electrically connected with the main controller; the number of the protective net covers is multiple, the multiple protective net covers are allfixedly connected with the vehicle body, and each power device is arranged in the corresponding protective net cover; a top end of the storage box is fixedly connected with the bottom end of the vehicle body; the camera is fixedly mounted on the front side of the vehicle body and is electrically connected with the main controller; and the battery supplies power to electrical equipment of the unmanned aerial vehicle. By arranging the protective net covers, problems that the power devices are affected by falling stones and collide with the wall of an underground roadway are effectively solved,the unmanned aerial vehicle can fly normally, the storage box is arranged, rescue materials can be carried, and corresponding water sources, food and medicine are provided for to-be-rescued personnel.

The invention discloses an unmanned aerial vehicle target tracking system and method based on machine vision, relates to the related field of unmanned aerial vehicles, and aims at solving the problemsthat in the prior art, disturbance and time lag have more and more influences on an unmanned aerial vehicle along with increase of single flight time of the unmanned aerial vehicle, and the target tracking is influenced. A flight control single-chip microcomputer is in bidirectional data connection with the flight simulation module. The input end of a flight simulation module is connected with the output end of an attitude dynamics model establishing module. The input end of the flight control single-chip microcomputer is connected with the output end of the A / D converter. The input end of the A / D converter is respectively connected with the output ends of an acceleration sensor, a gyroscope and a barometric altimeter; the output end of the flight control single-chip microcomputer is connected with the input end of a position controller, the output end of the position controller is connected with the input end of a flight driving motor, and the output end of the flight driving motor is connected with the input ends of flight rotors.

The invention discloses a long-endurance hybrid power UAV (Unmanned Aerial Vehicle). The UAV comprises two propeller engines, double tail booms and a pair of wings, wherein the propeller engines are respectively and relatively arranged in the front or at the back of a UAV body; the double tail booms are arranged at the rear part of the UAV body and the pair of wings is arranged on the UAV body; the two propeller engines are a methanol engine and a motor and both are arranged on the axis of the UAV body. According to the UAV provided by the invention, by adopting a high mounted wing with high aspect ratio, double tail booms layout, and the power configuration that the methanol engine is behind the motor, the oil and electric hybrid power has the characteristics of long-endurance of an oil driven airplane and the reliability of an electric driven airplane; furthermore, the motor can ensure that the oil-driven airplane is capable of making a return voyage when an extinguishment-trouble is caused, so that the safety of the air-plane, surrounding buildings and personnel can be ensured, and the survival rate of the airplane can be improved; more powerful power can be provided when the motor and the methanol engine are operating at the same time, so that the maximum load of the UAV can be improved, and the take-off distance can be shortened, besides the requirements on a take-off site by the UAV can be reduced, therefore, the UAV can take a plurality of task equipment to implement tasks.

The invention relates to an intelligent unmanned aerial vehicle of a flexible and varied structure. The intelligent unmanned aerial vehicle comprises a main body, an air pump, a plurality of driving units and a plurality of flight units, wherein the number of the driving units and the number of the flight units are identical; the driving units and the flight units are in one-to-one correspondence; each driving unit comprises an air cylinder and a piston; the air cylinder is fixed on the main body; one end of the piston is arranged in the air cylinder; the other end of the piston is connected with the flight unit. The intelligent unmanned aerial vehicle of the flexible and varied structure is characterized in that during the flight, pulleys are collected into a first opening through the support unit, so that the flight resistance of the unmanned aerial vehicle is reduced so as to prevent the contact with an obstacle; during the landing, the pulleys extend to the outside to realize the support, so that the unmanned aerial vehicle can flexibly regulate the self structure according to the operation conditions; the requirements are met. In addition, the driving units pull the flight units to approach to the main body center, so that the integral dimension of the unmanned aerial vehicle is reduced; the unmanned aerial vehicle can pass through a narrow and small space during the flight; the normal flight of the unmanned aerial vehicle is ensured, so that the practicability of the equipment is improved.

The invention discloses an intelligent mine gas explosion disaster detection system capable of collecting disaster in time. The intelligent mine gas explosion disaster detection system comprises an overground control system, an intelligent unmanned aerial vehicle, an airborne device, an underground collection device, a detection robot and a relay device. The overground control system controls the intelligent unmanned aerial vehicle through a wireless transmission system, and the intelligent unmanned aerial vehicle loads the airborne device; and the intelligent unmanned aerial vehicle comprises a target tracking module, a calculation task segmentation module, an information fusion module and a motion detection module, and the airborne device comprises an airborne dust sensor, an airborne high-definition camera system, an airborne temperature sensor, an airborne humidity sensor and a wireless transmission system. The intelligent mine gas explosion disaster detection system capable of collecting disaster in time has the beneficial effects that the intelligent unmanned aerial vehicle, the airborne device, the underground collection device and the detection robot are arranged and matched with the overground control system, all-directional detection, investigation and rescue of a mine are achieved, so that the safety and automation degree of disaster detection are higher, and casualties and economic losses are reduced.

The invention discloses a multi-purpose mooring unmanned aerial vehicle, which comprises a shell, four folding jib booms connected to the shell, an airframe fixedly arranged inside the shell, an electronic governor mounted on the bottom of the shell, a main controller mounted on the airframe, a flight data collector, a parachute emergency device, a power module, a signal transmission module, and a four-axis eight-blade rotor connected to the four folding jib booms. The drive motor of the four-axis eight-blade rotor is connected with the electronic governor. The electronic governor, the flight data collector, the parachute emergency device, the power module and the signal transmission module are connected with the main controller. The jib booms are of a folding structure, thereby facilitating folding and transportation, the parachute emergency device is arranged, so that the unmanned aerial vehicle can make an emergency landing in the event of a failure, to minimize the damage of the unmanned aerial vehicle.

The invention belongs to the technical field of unmanned aerial vehicles and discloses a system and method for predicting a remaining electricity quantity of a general lithium battery for a multi-rotor unmanned aerial vehicle. A general lithium battery remaining electricity quantity prediction device is turned on, control parameters are set according to the battery being detected, a lithium battery pack being detected is connected with the general lithium battery remaining electricity quantity prediction device, and operation off the system is started after a detection button is pressed. Via the system and method disclosed in the invention, an accurate remaining electricity quantity of the lithium battery can be obtained; the system is a piece of communication equipment, the remaining electricity quantity can be accurately predicted via detection of a chosen lithium battery pack model, prediction precision can reach as high as over 90% of a measured electricity quantity, and currentlyno such product for predicting the remaining electricity quantity of the battery is available. The system and method can help fill in market gaps, and flight of the unmanned aerial vehicle can be wellensured.

The invention discloses a novel unmanned aerial vehicle which comprises a main support. Flight arms are arranged in the four directions of the main support. A motor is installed at one end of each flight arm. A motor shaft of each motor is provided with a wing. A control panel and a receiver are arranged at the upper end of the main support. A battery box is arranged at the lower end of the main support. Storage batteries are arranged in the battery box. A shell is arranged on the outer side of the main support. The periphery of the side faces of the shell is fixed to the four flight arms through flanges. Charging sockets are arranged on one side of the shell. A photovoltaic panel is arranged at the upper end of the shell. A supporting board is arranged at the lower end of the shell. Supporting rods are installed on the two sides of the lower end of the supporting board. A damping block is installed in the middle of the lower end of the supporting board. The control panel is controlledthrough a remote control unit so that the flight speed and the flight direction of the unmanned aerial vehicle can be controlled, the photovoltaic panel can convert luminous energy into electric energy, the electric energy is stored in the storage batteries, meanwhile, the storage batteries can be directly charged through the charging sockets, a camera is used for aerial photography, the direction of the camera can be adjusted through a cradle head, and all-directional aerial photography is achieved.

The invention discloses an air cooling heat dissipation system of a soft package battery pack for an unmanned aerial vehicle and a control method thereof. The air cooling heat dissipation system comprises a shell, a plurality of battery cell monomers, a plurality of heat conduction silica gel pads, a temperature sensor, an air inlet fan, an air outlet fan and a controller, wherein the battery cellmonomers, the heat conduction silica gel pads and the temperature sensor are arranged in the shell; the air inlet fan and the air outlet fan are arranged outside the shell; and the temperature sensor, the air inlet fan, the air outlet fan and the battery pack are all connected with the controller. The air cooling heat dissipation system is reasonable in structural design and good in heat dissipation effect, the rotating speed of the fan and the output power of the battery pack can be controlled according to the temperature of the battery pack, the battery pack is cooled and located within a temperature suitable range, and normal flight of the unmanned aerial vehicle is guaranteed.

The invention relates to the technical field of fire-fighting unmanned aerial vehicles, in particular to a fire-fighting unmanned aerial vehicle arrangement platform which comprises an unmanned aerial vehicle body, a supporting mechanism is installed on the unmanned aerial vehicle body, a locking mechanism is installed on the supporting mechanism, a limiting mechanism is connected to the supporting mechanism, and a clamping mechanism is connected to the supporting mechanism. A driving mechanism is mounted on the supporting mechanism, a rolling mechanism is mounted on the supporting mechanism, and a pressing mechanism is mounted on the supporting mechanism; the unmanned aerial vehicle body can be supported and damped under the action of the supporting mechanism, meanwhile, a water tank can be conveniently placed and installed, fire extinguishing work can be conducted conveniently, the supporting mechanism is protected under the action of a limiting mechanism and a locking mechanism, and the supporting mechanism works on a driving mechanism and a clamping mechanism through rising and falling of the unmanned aerial vehicle body; conveniently, clamping, assembling and disassembling of a water tank are realized; and under the cooperation of the rolling mechanism and the pressing mechanism, the unmanned aerial vehicle body can conveniently move on the ground and control braking.