49results about How to "Improve flight safety" patented technology

The invention relates to an unmanned aerial vehicle path planning method and device, electronic equipment and a readable storage medium. The method comprises the steps that environment information of a task area and constraint parameters of an unmanned aerial vehicle are acquired; initializing a population of the improved beaver optimization algorithm; determining a fitness value for each individual in the population based on a preset cost function; based on the fitness value, dynamically allocating a role to each individual in the population, updating the position of the individual by adopting a corresponding updating strategy according to the allocated role, and executing information exchange between roles in the updating process; and based on a preset termination condition, determining an individual with the lowest fitness value from the population after iteration updating, and outputting a path point sequence represented by the individual as a planned unmanned aerial vehicle flight path. Through the method provided by the invention, the local optimal escape ability and the quality of the solution are enhanced, the flight safety and the terrain adaptability are improved, and the overall performance and the reliability of unmanned aerial vehicle path planning are improved.

This invention provides an active flow control method and system based on intelligent algorithms. The method includes: determining the number of inlet parameter sets for a typical flight state point, constrained by simulation economy and sampling efficiency; performing numerical simulations according to the number of inlet parameter sets to obtain dataset 1, with inlet parameters as independent variables and flow field characteristics as dependent variables; obtaining dataset 2, with flight state as independent variables and flow field characteristics as dependent variables, through numerical simulation for a certain set of inlet parameters; constructing a proxy model of inlet flow field characteristics for a typical flight state point using deep learning based on dataset 1; constructing a proxy model of inlet flow field characteristics for a wide-speed-domain flight state based on the proxy model of inlet flow field characteristics for the flight state point, using a transfer learning algorithm and dataset 2; constructing an environment-agent interaction model based on a deep reinforcement learning algorithm, using the proxy model of inlet flow field characteristics for a wide-speed-domain flight state as the environment model for deep reinforcement learning; setting optimization termination conditions based on the environment-agent interaction model, and obtaining a control sequence with continuously optimal inlet performance under different flight states through deep reinforcement learning. This invention can stably adapt to flight scenarios with a wide speed range and a large airspace, and achieve real-time optimal control of the air intake flow field under a wide speed range, solving the problem of poor generalization ability of traditional methods under different operating conditions.

The utility model discloses an unmanned aerial vehicle-mounted radar hanger structure with a damping function, which relates to the technical field of unmanned aerial vehicles and comprises an unmanned aerial vehicle body, a base net rack and a pull net rack. The base net rack is connected to the bottom surface of the unmanned aerial vehicle body through bolts, and the lower part of the base net rack is provided with a sunken upper mounting groove; the pull net rack is arranged below the base net rack, the edge of the pull net rack is connected with the base net rack through a plurality of elastic connecting pieces, the upper portion of the pull net rack is provided with a sunken lower installation groove, and the lower installation groove corresponds to the upper installation groove and is used for being connected with the airborne radar in a clamped mode. Through the elastic connecting pieces between the base net rack and the towing net rack and the elastic supporting pieces on the towing net rack, vibration and impact generated in the flying process of the unmanned aerial vehicle can be effectively absorbed and buffered, precise equipment such as airborne radar can be protected, the performance of the unmanned aerial vehicle is improved, and the service life of the unmanned aerial vehicle is prolonged.

The invention discloses a lifting decision-making method, device and equipment for an unmanned aerial vehicle and a storage medium, and relates to the technical field of unmanned aerial vehicles. The method comprises the steps that first energy is determined according to task information of a hoisting task and the current position of the unmanned aerial vehicle, and the first energy is energy needed by the unmanned aerial vehicle to arrive at a target unloading point from the current position; determining a homeward voyage starting point of the unmanned aerial vehicle based on the first energy and residual energy of the unmanned aerial vehicle; based on the homeward voyage energy corresponding to the homeward voyage starting point, a homeward voyage strategy of the unmanned aerial vehicle is determined, and the homeward voyage strategy comprises on-load homeward voyage or no-load homeward voyage of the Through the above technical means, the homeward voyage starting point for safe unloading of the unmanned aerial vehicle can be determined according to the energy required by the unmanned aerial vehicle to arrive at the unloading point and the current residual energy, and the homeward voyage strategy for safe homeward voyage of the unmanned aerial vehicle can be determined according to the energy required by homeward voyage of the unmanned aerial vehicle from the homeward voyage starting point. The air crash of the unmanned aerial vehicle due to insufficient electric quantity in the hoisting or returning process is avoided, and the flight safety of the unmanned aerial vehicle is improved.

The invention relates to the technical field of automatic driving, in particular to a collision coordination method and device for flight equipment, equipment and a medium. According to the method, flight data of all flight devices are acquired, a relative position relation is determined for a target flight device in combination with data of other flight devices, a corresponding collision area type is obtained according to a mapping relation between preset N threshold division intervals and collision area types, and if the type indicates that a potential collision risk exists, the collision risk is determined. If yes, a coordination intervention signal indicating the flight equipment to execute the avoidance strategy is sent to the other flight equipment. Therefore, collision coordination between the flight equipment is realized by analyzing the flight data, and the flight safety degree is improved.

The invention relates to the technical field of water quality monitoring, in particular to an unmanned aerial vehicle water quality sampling device for environmental monitoring, which comprises an unmanned aerial vehicle body, a lifting assembly is arranged at the bottom end of the unmanned aerial vehicle body, the lifting assembly comprises a mounting plate mounted at the bottom end of the unmanned aerial vehicle body, a winder body is mounted at the bottom end of the mounting plate, and a sampling assembly is arranged at the bottom end of the lifting assembly. The sampling assembly comprises a sampling bin installed at the bottom end of the connecting rope, a plurality of water inlet holes are formed in the top end of the sampling bin in a penetrating mode, a bearing round frame is fixedly connected to the bottom end of the sampling bin, multiple sets of sliding round frames are slidably clamped to the inner end of the bearing round frame, and lower pressing blocks are fixedly connected between the sliding round frames located at the lower end. The top end of the pressing block slidably penetrates through a sliding rod at the top end of the sampling bin, the top end of the sliding rod is fixedly connected with a filter screen plate, and the bottom end of the filter screen plate is fixedly connected with a plurality of conical rods. By means of a linkage structure of the sliding round frame, the pressing block and the conical rods, integration of water entry resistance reduction, accurate sampling and sealing pollution prevention of the sampling bin is achieved.

The application relates to a force couple balance and longitudinal array push-pull vertical take-off and landing high-speed aircraft, belonging to the technical field of aircrafts, which comprises a fuselage, a rotor, a fixed wing, a steering controller and a propeller. The rotor is installed at the top of the middle part of the fuselage through a rotor shaft, and a clutch is arranged between the rotor and a power system and / or a transmission system matched with the fuselage, so as to be controlled to be disconnected or to transmit power to the rotor. The steering controller comprises a fixed base and a rotating base, and each of the nose and the tail has a set of the rotating base. The propeller is provided with two propellers which are respectively installed on the rotating bases of the nose and the tail, and are controlled to rotate with the rotating bases relative to the fixed base. The force couple formed by the front and rear thrust vectors is used to balance the reverse torque brought by the rotor. When the propeller is coaxial with the middle axis of the fuselage, the wind area of the single propeller obtains double thrust. The application can improve the energy utilization rate, improve the carrying capacity, improve the flight safety performance and obtain a longer hovering time.

The utility model provides a control circuit of an unmanned aerial vehicle and the unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, and the control circuit of the unmanned aerial vehicle comprises a voltage detection circuit which is used for detecting the connection state of a power signal line of a wired unmanned aerial vehicle and outputting a corresponding power connection signal; the first controlled end of the battery power supply circuit is connected with the output end of the voltage detection circuit, and the battery power supply circuit is used for supplying power to the unmanned aerial vehicle under the condition that the power supply connection signal is not connected; the power input end of the master control circuit is electrically connected with the power interface and the output end of the battery power supply circuit. The unmanned aerial vehicle can still operate stably when the power signal line is disconnected, the crash risk caused by power failure is avoided, and the flight safety is improved.

The invention provides an avionics system architecture based on wireless communication, and relates to the technical field of unmanned aerial vehicles, and the avionics system architecture comprises a central flight control unit used for generating a flight control instruction, a main communication module connected with the central flight control unit, and a plurality of power systems distributed on an aircraft body; by completely cancelling a physical signal cable between the central flight control unit and the power system, fault modes such as cable abrasion, open circuit and poor connector contact caused by vibration of the aircraft body are eliminated, the single-point fault probability is reduced, and the flight safety is improved.

A method for planning an autonomous landing safe trajectory suitable for UAV inspection is proposed. After the UAV takes off, it acquires the current pose of the UAV, the point cloud map information of the surrounding environment, and the spatial orientation of the target point. By establishing the spatial transformation relationship between the camera coordinate system and the body coordinate system, the orientation vector relative to the ground target is calculated, and the target point is generated within the radar-sensible area. Based on the generated target point, an optimization function that minimizes the fourth derivative is constructed based on multiple high-order polynomials to generate a smooth trajectory with continuous position, velocity, and acceleration. The initial trajectory is transformed into a B-spline curve, and local trajectory segments with collision risk are optimized. A segmented penalty mechanism is designed based on the boundary threshold to guide the trajectory away from the boundary area. The time span is adjusted by calculating the trajectory derivative over-limit ratio, and a trajectory similarity cost function is introduced to ensure that the final optimized trajectory maintains the original geometric structure, thereby achieving trajectory control optimization and safe landing of the UAV.

The application provides an automatic reconstruction method and device of a flight parameter sensor, comprising the following steps: step 1, acquiring sensor data of the same flight parameter and confidence of each sensor; step 2, acquiring a reference value of the flight parameter according to the sensor data and the corresponding confidence; step 3, judging validity of the sensor data according to the reference value of the flight parameter; the validity includes invalid, valid and pending; step 4, when the validity of the sensor data is invalid, setting the confidence of the sensor as 0; when the validity of the sensor data is pending, sending a prompt information to the pilot, and setting the confidence of the sensor as 0 when a shielding instruction input by the pilot is received. The sensor automatic reconstruction method provided by the application can effectively identify a faulty sensor, correctly select a normal sensor to provide a flight parameter to the pilot, effectively reduce the operation load of the pilot and improve the flight safety.

The application discloses a kind of barometric altitude dynamic correction method based on airborne data.First, the sliding window parameters are screened using recursive feature elimination method, and then the sliding window is initialized and updated;Clean the sliding window data, first determine whether the sliding window data is null, then correct;For the data fusion multiple methods to detect outliers and correct after completing null judgment and correction;Construct the LSTM model and optimize the sliding window size, select the window size of the best performance indicator, use the LSTM model to correct the barometric altitude dynamically.This method has the characteristics of high precision, strong real-time, etc., improves the deficiency that the existing method can only correct the barometric altitude at a specific location, realizes the dynamic correction of barometric altitude in the whole approach process, improves the obstacle safety under low temperature conditions, at the same time, has the ability to correct the barometric altitude under high temperature conditions, and can be widely used in flight operation using barometric vertical navigation program.

This invention relates to the field of motor technology and discloses a high-power-density permanent magnet motor for unmanned aerial vehicles (UAVs). The motor includes a stator with a winding section and a frequency conversion section. The winding section is arranged in a ring array around the center of the stator, allowing for different coil combinations on a single winding. The winding section includes slots A, B, and C. Slot A is located on the inner wall of the stator, while slots B and C are located on the stator itself. The inner wall of the stator also has inlet holes A, B, and C. Inlet holes A and B communicate with slot A, and inlet holes B and B communicate with slot B. The motor employs a wide-range speed control to adapt to UAV operating conditions, featuring a six-speed adjustment function. The rated speed ranges from 8 r / min (8 Hz) to 48 r / min (48 Hz), and the speed ratio can reach 1:8 during weak field operation. This allows for precise matching of the power requirements of different stages of UAV operation, such as takeoff, cruise, and high-speed flight, achieving full operating condition coverage without motor replacement.

The invention relates to the technical field of aerospace instruments and aircraft atmosphere data systems, and discloses an intelligent sensing and processing method and system for a liquid collection cavity of an atmosphere sensing system. The intelligent sensing and processing system comprises a liquid level monitoring module, a control unit, a drainage execution mechanism, a drainage port and an adjustable heating module, and the liquid level monitoring module is used for outputting monitoring data; the control unit is used for receiving the monitoring data of the liquid level monitoring module, determining the height of the liquid level in the liquid collecting cavity according to the monitoring data, comparing the determined height of the liquid level with a liquid level triggering threshold value, and controlling the drainage executing mechanism and the adjustable heating module according to a comparison result; the adjustable heating module is uniformly wound outside the pressure measuring pipeline, the liquid collecting cavity and the drainage executing mechanism and is used for executing heating operation under the control of the control unit; and the drainage execution mechanism is arranged between the bottom of the liquid collection cavity and the drainage port and is used for switching between opening and closing under the control of the control unit.

The invention belongs to the field of aviation electrical control, and particularly relates to an intelligent integrated display controller. Comprising an intelligent identification module used for identifying pilot gestures and cockpit safety; the voice recognition module is used for recognizing a voice command of a pilot and the safety of the cockpit; the attention improving module is used for identifying the operation timeliness and accuracy of the pilot and reminding the pilot through sound and light effect; the data input and output module comprises an internal bus and an external bus and is used for data transmission; the main processing module is used for comprehensively processing and controlling pictures and data after receiving external bus data of the data input and output module and resolving the resolving results of the intelligent recognition module, the voice recognition module and the attention promotion module; and the graph drawing module is used for drawing graphs.

The invention discloses a flying robot and an unhooking system of the flying robot, the flying robot is connected with an unpowered aircraft through a traction piece and used for pulling the unpowered aircraft to rise through the traction piece, and the unhooking system comprises a controller, a receiver, a steering engine, a support, an opening and closing mechanism and a navigation module; the controller is connected with the receiver, the steering engine and the navigation module, the support is fixed to the flying robot, and the steering engine and the opening and closing mechanism are arranged on the support; the controller receives a preset remote control instruction from the receiver, the controller receives real-time data from the navigation module, the controller is used for generating an unhooking instruction based on the remote control instruction or the real-time data, and the steering engine controls the opening and closing mechanism to be opened based on the unhooking instruction, so that the traction piece is separated from the opening and closing mechanism. The unhooking instruction is generated through the controller based on the remote control instruction or the real-time data, the steering engine controls the opening and closing mechanism to be opened based on the unhooking instruction, rapid separation of the traction piece and the opening and closing mechanism is achieved, and the flight safety of the unpowered aircraft is improved.

The present application relates to the field of unmanned aerial vehicle flight control technology, and particularly relates to a hydrogen fuel cell hybrid power unmanned aerial vehicle cooperative control method and system. The method establishes a flight dynamics and energy dynamics cascade state model, takes the actual total output power of the hybrid power system as an intermediate virtual control quantity, introduces a disturbance observer to estimate the lumped disturbance, and generates an energy distribution control instruction based on backstepping sliding mode control to coordinate and distribute the output of the hydrogen fuel cell and the battery. The present application can realize closed-loop cooperation of flight control and energy management under the condition of slow dynamic response of the fuel cell and limited power climb, and improve the control accuracy, stability and safety of the unmanned aerial vehicle under acceleration, climb, maneuvering and complex disturbance environment.

This invention discloses a tilt-lift short takeoff and landing (STOVL) aircraft and its control method, comprising a fuselage, wing assembly, multi-layered distributed propulsion system, tilt drive assembly, and control unit. The wing is hinged to the fuselage via a pivot in the mid-rear section of the chord, and the tilt drive assembly drives the wing to rotate and adjust the angle of attack. The multi-layered distributed propulsion system includes a first rotor assembly located in the mid-rear section to the wingtip region of the wing and a second rotor assembly located on the lower surface of the wing near the fuselage. During cruise, the first rotor assembly is stopped and feathered, and the propulsion system tilts synchronously with the wing. This invention, through a layered distributed propulsion layout and synchronous wing tilting for synergistic lift enhancement, solves the problems of insufficient control torque at low speeds and high cruise energy consumption, achieving a balance between STOVL performance and cruise economy.

The utility model discloses a telescopic battery support belongs to unmanned aerial vehicle battery technical field, including carbon plate, adjusting support and bandage, carbon plate is used for placing battery group, and the top of carbon plate is opened and is equipped with a plurality of bandage holes, and adjusting support is installed at the top of carbon plate, and adjusting support is used for limiting battery group, and bandage is arranged in the bandage hole, and bandage is used for fixing battery group. The problem of battery group displacement and the flexibility of unmanned aerial vehicle being limited due to the bandage being easy to loosen or even break during flight and the existing fixing mode being difficult to adapt to batteries of different sizes or models in the prior art is solved. The utility model discloses through setting adjusting support, and the synergies with bandage, ensure that battery group does not loosen due to vibration or external force in the flight process, improves flight safety, can adapt to battery group of different sizes, greatly reduces the installation and adjustment time, and enhances the flexibility.

This invention discloses a UAV contouring flight system and method based on multi-sensor fusion and adaptive planning. The system includes a multi-sensor module for simultaneously acquiring 3D point cloud data, image data, and UAV inertial measurement data of the environment; a localization and mapping module for processing the acquired data through a tightly coupled fusion algorithm to output the UAV's real-time pose and a 3D map of the environment; an adaptive path planning module for identifying target objects based on the 3D environmental map and adaptively selecting and executing a matching path generation strategy to generate a contouring flight path that conforms to the target object's surface; and a flight control module for controlling the UAV according to the contouring flight path. This invention solves the problems of low positioning accuracy, inaccurate environmental modeling, and inability to generate high-precision 3D contouring paths for UAVs in environments lacking GPS signals, achieving efficient contouring for regular targets and high-precision contouring flight for complex targets.

The application provides a kind of intelligent icing weather cloud and mist parameter sensor, belongs to intelligent sensor technical field, the sensor includes fixed seat, the top of the fixed seat is equipped with conductive slip ring, the bolt connection between the conductive slip ring and fixed seat, the top of the conductive slip ring is equipped with pipeline structure, the inside of the pipeline structure is equipped with heating unit and sensing unit, the heating unit and sensing unit are all arranged on the inner wall surface of the pipeline structure.The application adopts the above-mentioned intelligent icing weather cloud and mist parameter sensor, solves the technical problems of insufficient measurement accuracy, reliability and data processing capability of existing sensors under complex weather conditions, can accurately measure weather cloud and mist parameters, and improves the accuracy and reliability of measurement by solving data through a neural network model, meets the demand of weather parameter measurement in the field of aerospace, etc.

The utility model belongs to the technical field of aircrafts, and particularly provides a water-proof structure for a wingtip of a fixed wing, which comprises a binding post and an insulating sealing screw sleeve, the binding post is sleeved in the insulating sealing screw sleeve, and the problem that the wingtip of a wing of an unmanned aerial vehicle cannot be water-proof or the water-proof performance of gluing is poor is solved. According to the utility model, moisture is prevented from entering electronic components, circuits and the like inside the wing tip of the unmanned aerial vehicle, and equipment faults caused by short circuit, corrosion and the like are avoided, so that the flight safety of the unmanned aerial vehicle under various weather conditions is guaranteed, the risk of flight accidents is reduced, and the flight safety is enhanced.

The application belongs to the field of unmanned aerial vehicle control, and relates to an unmanned aerial vehicle autonomous obstacle avoidance and countermeasure method and device based on multi-sensor fusion, which comprises the following steps: synchronizing laser radar, millimeter wave radar, binocular vision and ultrasonic sensor in time and space, dynamically evaluating confidence and adopting adaptive weighted fusion to construct a three-dimensional map; identifying and tracking dynamic obstacles, predicting trajectories and calculating collision probability to realize local obstacle avoidance and re-planning; passively monitoring communication frequency bands, extracting radio frequency fingerprints and comparing with a white list to identify suspicious unmanned aerial vehicle identity and direction; forming a directional beam to emit tracking interference or decoy navigation signals; online optimizing fusion weights and path planning parameters on an edge computing unit; and multi-dimensionally evaluating countermeasure effects, automatically adjusting parameters if the effects are below a threshold value and storing cases in a knowledge base for strategy migration. The application improves perception reliability and environmental adaptability, and has high intelligentization and precision of obstacle avoidance and countermeasures, and has the ability of continuous evolution and closed-loop optimization.

The application belongs to the technical field of unmanned aerial vehicle path planning, and discloses an unmanned aerial vehicle path planning method and device, an electronic device and a storage medium, the method comprising: acquiring electromagnetic induction information of an unmanned aerial vehicle in a preset range, inputting the electromagnetic induction information into a preset multi-dimensional electromagnetic radiation cost model, calculating an electromagnetic radiation cost of the unmanned aerial vehicle in the preset range, based on the electromagnetic radiation cost, using a preset cost update rule to plan a flight path for the unmanned aerial vehicle, and obtaining an optimal flight path of the unmanned aerial vehicle in the preset range; through the above method, the flight safety of the unmanned aerial vehicle in a complex electromagnetic environment is improved.

This application discloses a collaborative planning method for UAV swarm ground attack missions, comprising: S1 randomly distributing the UAV swarm over a designated area and assessing the relative states of the UAVs and ground targets; S2 assigning targets to the swarm of m UAVs and n ground targets based on a mission benefit calculation method; S3 planning the flight path of each UAV to the target using the Dubins path planning method based on the situation assessment results and the target assignment scheme; and S4 replanning threatened paths, considering obstacle threats. This invention addresses the problems of assessing the situation, assigning corresponding tasks, and planning the shortest path when multiple UAVs are performing ground attack missions.

This invention relates to the field of fuel cell technology and discloses a fuel cell heat dissipation system and control method for active balancing heat dissipation in unmanned aerial vehicles (UAVs). The fuel cell heat dissipation system includes a UAV heat dissipation assembly and an active balancing control subsystem. The UAV heat dissipation assembly includes a liquid cooling circuit and rotors disposed at the tips of multiple heat dissipation arms. The liquid cooling circuit includes coolant channels disposed inside the multiple heat dissipation arms. The coolant channels include in-arm liquid inflow pipes and in-arm liquid return pipes. Multiple in-arm liquid inflow pipes are arranged close to the inner side of the heat dissipation arms, and the multiple inflow pipes converge at the tips of the heat dissipation arms and connect to the in-arm liquid return pipes. The inflow pipes have an S-shaped variable diameter pipe structure, and their arrangement density gradually decreases from the root to the tip of the heat dissipation arm. The active balancing control subsystem includes a sensor group, an actuator group, and a controller. This invention can improve the reliability and flight safety of the UAV thermal management system.

The utility model relates to the technical field of airplanes, in particular to an airplane capable of landing on a snowfield. The snowboard comprises a machine body, a damping mechanism and two snowboards, the bottom of the machine body is connected with the tops of the two snowboards through a damping mechanism, the damping mechanism is used for damping when the machine body lands, and the two snowboards are flush with each other and are arranged at an interval; the snowboard comprises a first inclined section, a transverse section and a second inclined section which are sequentially connected from front to back, the joint of the first inclined section and the transverse section and the joint of the second inclined section and the transverse section are of an arc-shaped structure, the first inclined section inclines upwards towards the front end of the machine body, and the second inclined section inclines upwards towards the rear end of the machine body. The width of the snowboard is sequentially increased from front to back. By arranging the snowboard, the pressure during landing of the airplane can be effectively dispersed, the sinking problem caused by the loose and soft accumulated snow is avoided, and therefore the airplane can land on the snowfield.

This application relates to a method, apparatus, computer device, and storage medium for determining collision probability. The method includes: determining the number of collision detection operations based on model parameters in a discretized three-dimensional model of the propeller; performing collision detection operations based on the number of detections and recording the number of collision events; and determining the collision probability of an object colliding with the propeller based on the number of collision events and the number of detections. This quantitatively assesses the probability of an object colliding with the propeller, thereby determining the probability of the object passing through the propeller. Using this probability provides data support for the analysis of the rejection characteristics of aircraft propellers and the design of aircraft propellers, enabling researchers to design aircraft more accurately. This is of great significance for improving the overall resistance of aircraft to foreign object impacts and engine ingestion capabilities, and enhancing aircraft flight safety.

This invention provides an adaptive inspection and early warning method for cable trenches using unmanned aerial vehicles (UAVs), belonging to the technical field of UAV inspection and early warning for cable trenches. To address the shortcomings of current UAVs in cable trench inspection processes, such as insufficient spatial adaptive planning, dynamic frequency allocation, and multi-source early warning linkage, a 3D laser scanner is used to scan along the cable trench axis to acquire dense point cloud data of the trench's internal structure. After denoising, registration, and stitching of the acquired data, internal structural parameters are extracted, including width, height, bend radius, branch locations, fire door locations, and ventilation opening locations. Obstacle areas and communication signal attenuation areas are then marked to construct a 3D spatial constraint model of the cable trench, generating a weighted 3D flyable area map. Historical fault records, equipment operating parameters, and environmental monitoring data for each inspection area are collected. This invention is used for UAV inspection of cable trenches.

The invention relates to the technical field of aircrafts, and provides an image processing method and device, computer equipment and a storage medium. The method comprises the steps that a to-be-processed image from an aircraft is received, the to-be-processed image is obtained by shunting an original image collected by the aircraft, and the other image obtained by shunting the original image is used for environment perception of the aircraft; and performing image enhancement processing on the to-be-processed image to obtain an enhanced image. According to the invention, the control precision and flight safety of the aircraft can be improved, and the real-time performance and accuracy of the environment perception of the aircraft can be improved.