60results about How to "Improve flight efficiency" patented technology

The invention provides an unmanned aerial vehicle multi-target tracking method and system based on visual and millimeter-wave radar information fusion, and the method comprises the steps: obtaining an association result through employing a space-time consistency model, constructing a self-adaptive joint probability data association frame according to the association result, so as to obtain an initial target state estimation value, and carrying out the recognition of the initial target state estimation value. A prospective path planning algorithm is adopted to obtain an optimal observation angle flight path, a Bayesian network is utilized to obtain initial observation data, based on the initial observation data, an optimal target state estimation value is generated, a distributed cooperative sensing mechanism is used to generate an initial tracking task allocation scheme, and an intelligent resource allocation strategy is implemented. Generating an initial resource allocation scheme, starting a quick response protocol to obtain an optimal tracking task allocation scheme, and generating an optimal resource allocation scheme based on the optimal tracking task allocation scheme; according to the technical scheme provided by the invention, the accuracy of target identification is improved, the environmental adaptability is enhanced, the tracking efficiency is improved, and the working time is prolonged.

The invention relates to the technical field of space positioning and path planning, in particular to a three-dimensional space positioning and path planning method for an unmanned aerial vehicle tower. The method comprises the following steps of performing accurate longitude and latitude height data acquisition based on a laser range finder to generate accurate longitude and latitude height data; obtaining tower equipment parameters; performing inspection point three-dimensional coordinate calculation according to the tower equipment parameters and the tower three-dimensional coordinate system to generate inspection point three-dimensional coordinate data; cruise point comprehensive constraint range data are obtained according to the unmanned aerial vehicle flight association data and the polling area terrain data, and cruise point comprehensive constraint range data are generated; performing cruise node three-dimensional coordinate design on the three-dimensional coordinate data of the inspection point according to the cruise point comprehensive constraint range data to generate cruise point three-dimensional coordinate data; and performing optimized cruise path planning processing according to the cruise point three-dimensional coordinate data to generate optimized cruise path data. According to the invention, more accurate unmanned aerial vehicle tower space positioning and path planning are realized.

The embodiment of the invention provides an unmanned aerial vehicle dynamic deployment method and equipment, and the method comprises the steps: introducing a flight plan, a flight path line and a space-time envelope of flight, predicting the flight path of an unmanned aerial vehicle at a specific time, mastering the full view of the flight process in the whole flight plan, and carrying out the management and control of the capacity of the flight path as a resource, thereby achieving the dynamic deployment of the unmanned aerial vehicle. According to the method, the flight plan is deployed based on the capacity control result, conflict detection is carried out on space-time conflicts possibly existing in the flight process in combination with the flight control area and the flight plans of other unmanned aerial vehicles, and the flight plan is further adjusted in combination with the conflict detection result, so that accurate deployment of the flight of the unmanned aerial vehicles is realized. And the flight efficiency and the airspace utilization rate of the unmanned aerial vehicle are effectively improved.

The invention relates to a vector propulsion spherical airship with an adjustable structure. The spherical airship is mainly composed of a vector propelling device, an airship capsule, an airship framework, a flight control module, a posture detection module, an environment monitoring module, a battery and the like. By adjusting the thrust direction of the vector propulsion device and the included angle between the airship framework and the capsule body, accurate control over the attitude and the flight path of the airship is effectively achieved. The design has the advantages of being small in size and compact in structure, and the propelling device is installed on the framework with the adjustable included angle, so that the control process is more flexible. Meanwhile, the propelling device achieves dynamic position adjustment through a framework structure and is prevented from being located in the airship movement direction, and potential safety hazards of a traditional external propeller are overcome. Although only two propelling devices are configured, the system can still provide fine control capability through seven controllable degrees of freedom, and the precision and flexibility of flight control are remarkably enhanced.

The invention relates to a low-altitude unmanned aerial vehicle flight path planning method and system, and relates to the field of unmanned aerial vehicle navigation and control, and the method comprises the steps: carrying out the primary planning of a flight path according to the information of a plurality of obstacles, and obtaining a primary planning path domain; according to the obstacle information and the bird feature information, bird flight path density analysis between obstacles is carried out, and bird flight path density distribution is obtained; and performing secondary path planning optimization in the primary planning path domain according to bird flight path density distribution to obtain an optimal planning path. According to the invention, the technical problem that the existing method cannot effectively solve the problems of obstacle avoidance and bird interference in the flight process of the low-altitude unmanned aerial vehicle, resulting in insufficient flight safety and poor flight efficiency of the unmanned aerial vehicle can be solved; the flight path with the shortest distance can be selected on the premise of effectively avoiding obstacles and high-bird-density areas, so that the safety and the flight efficiency of the unmanned aerial vehicle during low-altitude flight are remarkably improved.

The invention relates to the technical field of pilot state monitoring, in particular to a pilot state monitoring and flight data real-time synchronous fusion system, which comprises an information acquisition module used for acquiring physiological state information of a pilot and flight data information of an airplane in real time; the intelligent control module is used for controlling the operation of the camera, the electroencephalogram acquisition device and the electrocardiograph; the information processing module is used for carrying out preprocessing operation on the collected pilot physiological state information and the collected aircraft flight data; and the data fusion module is used for fusing the physiological state information of the pilot and the flight data parameters of the aircraft. The early warning assistance module is used for immediately sending out an early warning signal when an abnormality is found; and positioning information and rescue guidance are provided for a pilot under the emergency condition that the aircraft encounters danger. According to the current attention state and the task requirement of the pilot, the system can dynamically adjust the collection frequency and the collection position of the electroencephalogram collection device so as to improve the efficiency and the pertinence of data collection.

The invention discloses an unmanned aerial vehicle self-adaptive inspection method based on multi-layer characterization learning, which comprises two stages of automatic coarse inspection and self-adaptive fine inspection, and learns the space structure, component characteristics and disease characteristics of a bridge layer by layer. In the automatic rough detection stage, in combination with a spatial clustering post-processing method and a point cloud semantic segmentation network, instance attributes of bridge components are quickly learned. Then, the point cloud space is compressed and converted by using a simulation view field model and a dimension reduction technology, and the unmanned aerial vehicle is guided to carry out efficient and comprehensive space patrol in plane geometry. In the adaptive fine detection stage, a space-channel two-dimensional optimized hybrid convolution structure Light-PVIT is utilized to learn and extract disease features in the automatic coarse detection stage as prior information. The information guides the unmanned aerial vehicle to carry out fine detection on a disease area in a small field of view. According to the unmanned aerial vehicle self-adaptive inspection method, the bridge inspection efficiency and precision are remarkably improved, and reliable technical support is provided for bridge maintenance work.

The invention discloses a flight-oriented fan wing trailing edge adjusting device, and relates to the technical field of aircrafts, the flight-oriented fan wing trailing edge adjusting device comprises a trailing edge angle adjusting mechanism, a rectification angle adjusting mechanism, a circular end plate and a rectification plate, the trailing edge angle adjusting mechanism comprises a steering engine, a first connecting rod mechanism, a trailing edge plate and a rotating shaft; the steering engine is fixedly installed on the circular end plate and controls the rear edge plate to move through the first connecting rod mechanism, the rotating shaft is arranged on one side of the rear edge plate, and the rear edge plate is hinged to the rectifying plate through the rotating shaft. By freely adjusting the trailing edge angle and the rectification angle, the aerodynamic force of the fan-wing aircraft is changed, the lift force and thrust distribution is improved, the aerodynamic effect is enhanced, the energy consumption is reduced, and the flight efficiency is improved. The fan wing trailing edge adjusting device is applied to a serial fan wing, forward coupling gain between two wings is achieved by changing the size of a trailing edge angle and a rectification angle, different flight conditions are met, various flight requirements are flexibly met, and the load performance and the endurance are optimized.

The invention discloses a tilting folding wing and a vertical take-off and landing aircraft. Comprising a central wing (2), outer wings (3) capable of being folded / unfolded in a tilting mode are symmetrically connected to the two ends of the central wing (2), and tilting rotating shafts (501) of the outer wings (3) are located at the outer ends of the central wing (2) and located at the positions, close to the rear portions, of the front edges of the outer wings (3); the two outer wings are driven by the same folding driving mechanism (4) to be folded / unfolded in a tilting mode, and the connecting line of points on the outer wings (3) before and after tilting is perpendicular to the rotating shaft (501). The device has the advantages of being simple in structure, good in synchronism and high in safety.

The invention provides an airborne meteorological radar thunderstorm rapid identification method, and belongs to the technical field of airborne meteorological radars, and the method specifically comprises the steps: carrying out the ground clutter suppression of the obtained airborne meteorological radar three-dimensional echo data; carrying out reflectivity factor calculation on each piece of wave position data in the stereoscopic scanning process to obtain three-dimensional echo reflectivity factor data of the airborne meteorological radar after ground clutter suppression; processing the three-dimensional echo reflectivity factor data after the ground clutter suppression to obtain reflectivity factor data of a two-dimensional plane; extracting a potential thunderstorm region from the reflectivity factor data of the two-dimensional plane; the data of each potential thunderstorm area are traced back to the three-dimensional reflectivity factor data, and the features of a thunderstorm body are counted; and judging the potential thunderstorm area and the counted thunderstorm body features according to the thunderstorm identification feature threshold. Through the processing scheme provided by the invention, the speed and accuracy of thunderstorm identification are improved, and the perception ability of a pilot to a dangerous meteorological area on a flight route is improved.

The invention provides an automobile airplane with a vertical take-off and landing function and an efficiency improving method. The automobile airplane comprises a wing-shaped automobile body, two main thrust propellers and two wing end trapped vortex generators. The two main thrust propellers and the two wing end trapped vortex generators are symmetrically arranged on the two sides of the wing-shaped vehicle body. The rotating direction of a propeller vortex generated by rotation of the main thrust propeller is the same as that of the vortex of the wing end trapped vortex generator and is opposite to that of a wingtip vortex, so that an active reverse wingtip vortex generator is formed; during takeoff, even if no conventional long-wingspan wing exists, vertical takeoff or ultra-short-distance takeoff can be achieved on a single lane of a highway with the limited spanwise direction or an aircraft carrier deck only through the ultra-short chord ratio showing wing; the front part of the vehicle body is provided with a leading edge slat lease-reducing and lift-increasing device, so that the lift-drag ratio can be further improved, and during level flight, in order to improve the flight efficiency, wings with large span chord can be stretched according to actual conditions to form a fixed-wing flight mechanism type, so that the vehicle and the airplane can fly fast and far and carry more people, and the problem of traffic jam is effectively solved.

The invention discloses a foldable unmanned aerial vehicle rapid deployment system and method, and belongs to the technical field of unmanned aerial vehicle deployment. According to the system disclosed by the invention, the carrying system and the unmanned aerial vehicle storage device are arranged, the high-speed carrying system provides thrust and energy in the rapid deployment process, and the unmanned aerial vehicle storage device provides a protection function in the deployment process, so that rapid response and long-distance accurate and reliable deployment of the unmanned aerial vehicle are realized; the time for the unmanned aerial vehicle to arrive at the designated area is greatly shortened, the technical problem that an existing unmanned aerial vehicle deployment mode is poor in timeliness is solved, the time for the unmanned aerial vehicle to arrive at the designated area is greatly shortened through the high-speed and accurate deployment process, the burden that the unmanned aerial vehicle carries energy needed by take-off and climbing is avoided, and the unmanned aerial vehicle deployment efficiency is improved. And the task execution time of the unmanned aerial vehicle is prolonged.

This invention provides a static parameter measurement device for overhead contact lines based on an unmanned aerial vehicle (UAV) platform, belonging to the field of railway overhead contact line inspection technology. It includes a UAV body with a laser measuring device mounted on its top and a telescopic support mounted on its side. The UAV body includes a processor chip, and the laser measuring device is connected to the processor chip. After takeoff, the telescopic support secures the UAV, and the laser measuring device measures the overhead contact line. The measured data is transmitted in real time to the processor chip for processing and analysis, ultimately achieving high-precision measurement of the static parameters of the overhead contact line. By linking the top-mounted laser measuring device with the processor chip, it is possible to conduct inspections and parameter measurements on conventional railway lines outside of designated maintenance windows, achieving high-precision, non-contact distance or terrain measurement, suitable for complex environments, and significantly improving data acquisition efficiency.

The utility model relates to the technical field of takeoff and landing protection equipment, and discloses takeoff and landing protection equipment for an unmanned aerial vehicle, which comprises an unmanned aerial vehicle body, and a display connection signal screen is fixedly mounted on the outer wall of the unmanned aerial vehicle body. The foldable light and thin mounting plate is rapidly folded and unfolded through the rotating hinge and the small hydraulic push rod, in the flight state, the mounting plate is folded and tightly attached to the fuselage, air resistance is effectively reduced, the flight efficiency is improved, before landing, the hydraulic push rod rapidly pushes the mounting plate to be unfolded to the horizontal position, and the supporting area is enlarged; the unmanned aerial vehicle is in direct contact with the ground in cooperation with an anti-skid balancing weight, the friction force between the unmanned aerial vehicle and the ground is increased, the unmanned aerial vehicle is effectively prevented from sliding or rollover after landing, meanwhile, an inflation pump is arranged in an inflation box to inflate a buffering air bag, a flexible protection layer surrounding the unmanned aerial vehicle is formed, falling impact is effectively relieved, and the unmanned aerial vehicle is protected from falling. And the effect of improving the protection safety is achieved.

A vector tilting coaxial twin-rotor UAV is provided, which is composed of a fuselage (101), a power device (102) and a vector tilting device (103), wherein the power devices (102) and the vector tilting devices (103) on the left and right sides of the UAV are symmetrical and have completely the same structure. The problem of the rearward blade stalling caused by the high-speed forward flight of the UAV can be solved by the characteristics that the upper and lower rotors rotate at opposite speeds and the rearward blades are symmetrically located relative to the body; the roll moment generated by one rotor is balanced by the roll moment of the other rotor.

The invention relates to the field of unmanned aerial vehicles, in particular to a tandem dual-rotor unmanned aerial vehicle structure which comprises an unmanned aerial vehicle body, a mounting plate slidably connected to the unmanned aerial vehicle body, spiral wings rotatably connected to the two ends of the unmanned aerial vehicle body and a driving device used for driving each spiral wing to rotate. The two spiral wings are located at the front end and the rear end of the unmanned aerial vehicle body correspondingly, the mounting plate slides in the width direction of the unmanned aerial vehicle body, and a plurality of mounting holes used for mounting an operation platform are formed in the mounting plate. The application has the advantages that the application range of the unmanned aerial vehicle can be widened, and the flight stability of the unmanned aerial vehicle can be guaranteed when different operation platforms are installed on the unmanned aerial vehicle.

The utility model relates to the field of ornithopters, in particular to a pure electric vertical take-off and landing high-capacity aircraft with double foldable flapping wings, which comprises an aircraft body, a cockpit is arranged at the top of the front end of the aircraft body, double rows of flapping wings are arranged on two sides of the top of the aircraft body in a front-back manner, and a plurality of side rotors are arranged on two sides of the aircraft body and positioned below the flapping wings. A plurality of tail rotors are arranged at the tail end of the fuselage, and a walking device is arranged below the fuselage. The double-row flapping wing aircraft is reasonable in structure, large in capacity, large in space and high in loading capacity, the aircraft body is made of light materials such as titanium alloy and carbon fibers, the dead weight can be effectively reduced, the loading capacity can be effectively improved, the double-row flapping wings fully utilize aerodynamic force, multiple functions of flight are improved, the flight efficiency is improved, and the double-row flapping wings are folded, so that the double-row flapping wing aircraft is more convenient to fold and unfold.

The invention discloses a method for planning a trajectory of a UAV that completely avoids a no-fly zone, belongs to the field of UAV trajectory planning, and includes application scenarios of the method for planning a trajectory of a UAV in a no-fly zone, wherein the application scenarios of the method for planning a trajectory of a UAV in a no-fly zone include communication scenarios between the UAV and a terminal user in a no-fly zone. The invention supports the UAV to absolutely avoid entering any no-fly zone during flight. Multiple straight lines are used to approximate the actual flight trajectory of the UAV, and the distance between the intersection of two adjacent straight lines and the center point of the no-fly zone is calculated to achieve strict monitoring and planning of the flight path of the UAV, thereby improving the accuracy of trajectory planning as well as the flight efficiency and task execution effect of the UAV. The invention increases the constraints on the continuous trajectory between adjacent time slots, and further improves the safety and robustness of the system through multiple straight line approximation and accurate intersection calculation.

The invention discloses a basalt fiber unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the basalt fiber unmanned aerial vehicle comprises a basalt fiber unmanned aerial vehicle shell, a battery is arranged at the top of the basalt fiber unmanned aerial vehicle shell, supporting frames are uniformly arranged on the periphery of the basalt fiber unmanned aerial vehicle shell, and an adjusting assembly is arranged on one side of each supporting frame; a fan blade assembly is arranged on the side, away from the adjusting assembly, of the supporting frame. A mounting plate is arranged in the basalt fiber unmanned aerial vehicle shell, a controller is arranged on the inner top of the mounting plate, and a sensor is arranged on the top of the basalt fiber unmanned aerial vehicle shell. According to the invention, the environment sensing module and the flight path planning module are combined to extract the flight image of the unmanned aerial vehicle, the features of static and dynamic obstacles are accurately identified, and the scientific setting of the static path and the real-time tracking of the motion trail of the dynamic obstacle are realized.

The utility model relates to the field of rotor support arm folding discloses a kind of rotor support arm electric folding and locking mechanism, including fuselage, at least two groups of support arm components are equipped on the fuselage, and support arm component includes first support arm unit and second support arm unit;First support arm unit includes first fixed support arm, first rotor support arm and first driving part, and second support arm unit includes second fixed support arm, second rotor support arm and second driving part, first fixed support arm one end and fuselage connection, other end and first rotor support arm rotary connection, second fixed support arm one end and fuselage connection, other end and second rotor support arm rotary connection, first driving part is used to drive first rotor support arm to the direction of being close to second fixed support arm rotation, and second driving part is used to drive second rotor support arm to the direction of being close to first fixed support arm rotation.Compared with prior art, structure is more simple, and rotor support arm can be effectively gathered.

The present invention relates to a method for analyzing tailspin characteristics. The time history of tailspin characteristics is obtained by solving tailspin dynamics differential equations, and the tailspin characteristics of simulation examples under conditions of multi-parameter changes such as weight, moment of inertia, and entry mode are predicted, and the influence of multi-variable parameters on the tailspin characteristics is analyzed; a machine learning model is built using an XGBoost regression algorithm based on decision tree analysis, and the multi-variable parameters of the simulation example are analyzed for feature importance with tailspin characteristics such as average angle of attack, average rotation rate, and sinking speed as targets; the influence ratio of multi-variable parameters on the same tailspin characteristics is analyzed, and the influence of key factors on the tailspin is completed in a quantitative manner. The tailspin feature analysis method of the present invention takes tailspin characteristics as targets, performs feature importance analysis on three multi-variable parameters of weight, moment of inertia, and entry mode, gives the degree of influence of each variable parameter on the corresponding target in the form of quantitative weights, and completes the multi-dimensional global feature analysis of the simulation example.

The present invention discloses a laminated hybrid composite wing structure. The ribs, trusses and spars are located inside the wing skin shell, the ribs are evenly spaced on the spars along the length direction of the spars, the ribs are connected by trusses, and the outer periphery of the ribs is close to the inner side of the wing skin shell; the wing structure is installed on the fuselage of the aircraft through one end of the spar as the side wing of the aircraft. The wing structure of the present invention introduces hybrid composite materials into the optimized design of the wing, which can meet the comprehensive requirements of the cost, weight and performance of the wing structure, and can improve the strength and vibration characteristics of the wing structure without increasing the cost, and achieve the lightweight requirements, thereby improving the flight efficiency of the aircraft.

The invention relates to a power device of an unmanned aerial vehicle and the unmanned aerial vehicle. A power device of the unmanned aerial vehicle comprises a main shaft, a motor, a steering engine and a rotor wing assembly. The spindle is fixed to the top of the unmanned aerial vehicle body. The motor is arranged on the main shaft, the steering engine and the rotor wing assembly are both in driving connection with the motor, and the steering engine and the rotor wing assembly can both rotate around the axial direction of the main shaft under driving of the motor. The rotor assembly comprises a propeller hub and blades, the propeller hub is in driving connection with the motor, and the blades are connected with the propeller hub. An output shaft of the steering engine is provided with a first gear, the propeller hub is provided with a second gear, when the flight direction is changed, the steering engine is started and drives the first gear to rotate, and the first gear and the second gear are in meshing transmission, so that the rotor wing assembly rotates by a certain angle, namely, the pitch angle of the propeller blades and the propeller pitch of the rotor wing assembly are adjusted. Thus, a traditional complex and heavy automatic inclinator control system can be replaced, the weight of the unmanned aerial vehicle can be reduced, the control precision of variable pitch is improved, and accurate variable pitch is achieved.

The invention provides an airspace information obtaining method, an airspace information sending method, a communication sensing terminal, an airspace information sending device, a storage medium and a computer program product device. Acquiring flight airspace information corresponding to the base station and effective time information corresponding to the flight airspace information; or acquiring pre-configured flight airspace information and effective time information. The sensing range of the communication sensing terminal can be expanded, the available flight space range of the communication sensing terminal can be expanded on the premise of ensuring the sensing of the communication sensing terminal, and the flight efficiency and safety are improved.

The present invention relates to the technical field of aerodynamic loss, and is a method and system for reducing aerodynamic loss of a ducted fan with a lip shape, comprising: receiving a flight instruction of an aircraft, starting a turbopropeller engine of the aircraft, receiving initial flight power, calculating the amount of starting gas entering a power device and obtaining the gas, generating starting kinetic energy, using the starting kinetic energy to drive the propeller to work, using an airflow sensor to sense the real-time airflow speed, obtaining the real-time flight direction and real-time airflow density of the aircraft and calculating turbulent kinetic energy, if the turbulent kinetic energy is greater than a kinetic energy threshold, performing shape adjustment on the lip shape, and calculating and adjusting the turbulent kinetic energy, using the adjusted turbulent kinetic energy to start a gas energy engine, obtaining gas kinetic energy, calculating replacement kinetic energy of the starting kinetic energy, replacing the starting kinetic energy based on the replacement kinetic energy and the gas kinetic energy, and completing a stable flight of the aircraft. The present invention can improve the energy utilization efficiency of the aircraft and reduce aerodynamic loss.

The utility model discloses a kind of height integration control flight cabin suitable for unmanned aerial vehicle, including cabin table, display, throttle push rod, joystick, integrated control panel, display is installed on bracket, bracket is set in cabin table rear side;Throttle push rod, joystick and integrated control panel are all set in the top of cabin table, integrated control panel is set below display, throttle push rod and joystick are all located in the front side of cabin table.The technical effects reached are as follows: using integrated design, pilot completes relevant operation in a centralized control area, accelerates take-off preparation speed, improves flight efficiency.Each subsystem's operating state can be better monitored and managed through integrated design, reduce human error, centralized control interface can clearly present each key parameter and operation option, so that pilot will not miss important information due to frequent shift of sight between multiple instruments and control devices, ensure operation accuracy, so that it can better cope with flight condition.

The utility model belongs to the technical field of shape design and control of aircrafts, and relates to an electric tilt-rotor aircraft. Comprising a fuselage, two wings located on the two sides of the fuselage, an empennage, a plurality of supporting rods arranged below the wings and rotors arranged at the two ends of the supporting rods. The rotor wings comprise a plurality of tilting rotor wings and a plurality of fixed rotor wings; the number of the supporting rods is even, and the supporting rods are divided into two sets with the same number and are symmetrically arranged on the two sides of the machine body. A tilting rotor wing is arranged at the front end of each supporting rod; a fixed rotor wing is arranged at the rear end of each supporting rod; the tilting rotor wings are connected with the front ends of the supporting rods through tilting mechanisms, and the tilting mechanisms are used for adjusting the orientation of the tilting rotor wings. The electric tilting rotor aircraft provided by the utility model can realize the functions of vertical take-off and landing, tilting transition and cruise flight.

The application provides an updating method and system for aircraft icing identification based on real-time detection of aircraft. The method comprises obtaining real-time data of the aircraft to determine icing occurrence information; constructing an icing report membership function based on the icing occurrence information, which is used to represent the spatial and temporal distribution of icing occurrence probability; and combining the icing report membership function with a basic icing index to calculate an icing potential index, which is used to identify the three-dimensional distribution of the icing area. The above method realizes accurate positioning, dynamic prediction and real-time warning of icing, and improves aviation safety and flight efficiency.

The invention discloses a tailstock type fixed wing remote control aircraft. The aircraft comprises an aircraft body; the fixed wings are arranged on the two sides of the middle of the aircraft body and can provide lift force for the remote control aircraft in a flying state; and the multiple sets of rotor power assemblies are arranged at the tail of the aircraft body, are sequentially arranged at intervals in the circumferential direction of the aircraft body and can provide driving force for taking off and flying of the remote control aircraft. Through the combined design of the fixed wings and the rotor power assemblies, the fixed wings can be used for providing lift force in the flight process, so that the remote control aircraft can fly at a high speed, the flight efficiency of the remote control aircraft is improved, the rotor power assemblies are used for providing enough driving force, and the remote control aircraft can vertically take off and land without depending on a runway; and the application range is expanded. Due to the design of the tailstock type layout and the multiple groups of rotor power assemblies, the gravity center of the remote control aircraft is close to the rear, pitching, rolling and yawing of the remote control aircraft can be effectively controlled, and the flight stability of the remote control aircraft is improved.

The present invention discloses a method and system for controlling a UAV flight based on a target image, and relates to the field of UAV flight control. The method comprises: obtaining the relative position of the UAV in the flight area based on the target image and the position calculation algorithm, and judging the yaw state of the UAV by the position comparison method; determining the flight yaw angle of the UAV by analyzing the target image using the recognition processing technology based on the yaw state judgment, and generating a yaw control amount according to the flight yaw angle to control the flight state of the UAV; collecting the real-time target image of the UAV after the flight state is adjusted, and analyzing the flight altitude of the UAV according to the real-time target image, and planning the landing trajectory of the UAV based on the flight altitude; generating an autonomous landing control instruction according to the landing trajectory of the UAV and the preset flight requirements to complete the autonomous landing flight control of the UAV. The present invention can accurately plan the landing trajectory of the UAV by collecting the target image in real time and analyzing the flight altitude.