23results about How to "Ensure flight stability" patented technology

The invention relates to the technical field of unmanned aerial vehicles, in particular to a mooring unmanned aerial vehicle safety management system which comprises a multi-source data acquisition module, a data fusion and analysis module, an intelligent risk assessment module, a control instruction generation module and an execution mechanism module. The multi-source data acquisition module acquires flight and mooring cable data of the unmanned aerial vehicle by using various sensors, and transmits the flight and mooring cable data to the data fusion and analysis module through a time division multiple access protocol with low packet loss rate and low delay; the intelligent risk assessment module judges a risk level by combining a risk assessment model based on a support vector machine and a Bayesian network algorithm according to the information, and generates prompt information if the risk level exceeds a preset range; the control instruction generation module generates instructions according to a risk prompt and a preset strategy, ranks the instructions and sends the instructions to the execution mechanism module; a flight control system in the execution mechanism module cooperates with a mooring cable electric take-up and pay-off device and the like, real-time adjustment and control over the flight attitude of the unmanned aerial vehicle and the cable state are achieved, and it is ensured that tasks are safely and stably executed in the complex environment.

The invention discloses a four-flapping-wing aircraft and an attitude control system thereof, and relates to the technical field of micro aircrafts, and the four-flapping-wing aircraft comprises a fixed rack, a guide rod, a slide block mechanism, a pitching frame, a rolling frame, a pulley and a chord driving system. The fixed rack is provided with four cantilevers, a sliding block mechanism is installed on a guide rod, and the pitching frame and the rolling frame control pitching and rolling actions through steering engines respectively. The four pulleys are connected to the pitching frame, and each pulley is hinged to one wing. The string driving system comprises a guide wheel, a string and a crank, one end of the string is connected with the slider mechanism, and the other end bypasses the guide wheel and is connected with the pulley to realize wing flapping. Through the deflectable spars and fine steering engine control, efficient aerodynamic performance, enhanced thrust output and excellent flight flexibility and adaptability are achieved, meanwhile, due to the design of the crank sliding blocks, structural stress is relieved, the service life is prolonged, the aircraft adapts to multiple flight modes, and the environment adaptability and task execution efficiency of the aircraft are improved.

This invention relates to a portable foldable tandem wing aircraft, comprising a frame, a front wing, an arm, a rear wing, a battery pack, a linear motor, a chuck, a mounting base, a first sliding plate, a first spring, a chuck return spring, a second spring, a second sliding plate, arm-wing connectors, a self-locking structure, and a double-ball-joint connecting rod. The mounting base and chuck are located in the middle of the battery pack. The chuck is connected to the output shaft of the linear motor, and the chuck return spring is connected to the mounting base and the chuck. The first sliding plate is slidably mounted on the front end of the battery pack, and the first spring is connected to the first sliding plate. The sliding plate is connected to the fixed base; the second sliding plate is slidably mounted at the rear end of the battery cylinder, and the second spring is connected to the second sliding plate and the battery cylinder; the arm wing connector is located at the front end of the battery cylinder, and the upper and lower ends of the arm wing connector are respectively connected to the arm, the head of the arm is rotatably connected to the arm wing connector, and is rotatably connected to the first sliding plate through a self-locking structure; the left and right sides of the arm wing connector are rotatably connected to the front wing, and the two sides at the rear end of the battery cylinder are rotatably connected to the rear wing; in the folded state, the arm and the rear wing are both locked together with the chuck. This aircraft is not only easy to carry, but also improves the stability during flight.

The invention discloses a fuel cell and lithium battery hybrid unmanned aerial vehicle semi-physical test system and method. The system comprises a hybrid power module used for simulating power output of a fuel cell and a lithium battery; the flight dynamics control module is used for resolving attitude information of the unmanned aerial vehicle; the control instruction sending module is used for sending a motion instruction of the unmanned aerial vehicle to the flight control instruction resolving module; the flight control instruction resolving module is used for resolving a control instruction to obtain motion instruction information; the ground station interface monitoring module is used for recording the flight attitude data of the unmanned aerial vehicle returned by the flight control instruction resolving module; the three-axis flight attitude simulation module receives the motion instruction information and makes attitude response; the real-time simulation module is used for receiving feedback information of the three-axis flight attitude simulation module and simulating the flight state of the unmanned aerial vehicle in a virtual scene; the unmanned aerial vehicle 3D modeling and visual module is used for recording real-time simulation machine data and control information of the flight dynamics control module; according to the invention, accurate and efficient simulation of the unmanned aerial vehicle can be realized.

The present invention belongs to the field of air pollution detection technology, and specifically relates to an air pollution source tracing device, including a detection device and an unmanned aerial vehicle, wherein a sampling chamber is provided in the middle of the detection device, the detection device is installed at the upper end of the unmanned aerial vehicle, a sampling channel is provided in the middle of the unmanned aerial vehicle, the sampling chamber is connected to the sampling channel, and landing gears are installed on both sides of the bottom of the unmanned aerial vehicle; the present invention can quickly respond to the monitoring needs of air pollution by carrying the detection equipment on the unmanned aerial vehicle, and realize the rapid tracing of air pollution. This efficient method greatly improves the timeliness and accuracy of pollution monitoring. The landing gear of the present invention adopts a reversible semicircular tube structure, which maintains a horizontal state when the unmanned aerial vehicle is flying, extends the air sampling port, and increases the sampling range; when the unmanned aerial vehicle stops working, it flips into a supporting foot to ensure that the unmanned aerial vehicle lands smoothly. This design not only ensures flight stability, but also takes into account sampling efficiency.

The invention relates to the technical field of unmanned aerial vehicles, and discloses a four-axis eight-rotor heavy-load unmanned aerial vehicle which comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body comprises a carbon fiber upper clamping plate, a carbon fiber middle clamping plate, an aluminum alloy bottom plate, four carbon tube walls and two foot stools, and battery mounting openings are reserved in the carbon fiber upper clamping plate and the carbon fiber middle clamping plate; the four carbon tube walls are connected between the carbon fiber upper clamping plate and the carbon fiber middle clamping plate through aluminum alloy tube clamps, each aluminum alloy tube clamp comprises a tube arm clamping plate, and the tube arm clamping plates are fixedly connected with the carbon tube walls through bolts. The four-axis eight-rotor coaxial layout is adopted, compared with a traditional heavy-load unmanned aerial vehicle needing six or eight independent vehicle arms, the wheelbase of the unmanned aerial vehicle is remarkably shortened, the overall structure is more compact, and the size of the unmanned aerial vehicle is greatly reduced on the premise that powerful power of the eight rotors is guaranteed through the design; and the device is more convenient to transport and deploy in a complex and narrow working environment.

The invention belongs to the technical field of aviation flight control, and particularly discloses an intelligent aircraft turning regulation and control system, which comprises a data acquisition and preprocessing module for collecting flight data and preprocessing the collected flight data; the DQN intelligent optimization module outputs an optimal turning action a based on the aircraft state s to realize an optimal turning strategy; and importing the DQN intelligent optimization module into airborne equipment, adjusting control parameters of the airplane by the DQN intelligent optimization module, and controlling the airplane to complete turning action. According to the method, a real-time optimization model is established by utilizing a Deep Q-Network (DQN) deep reinforcement learning algorithm, the model can adaptively calculate the optimal turning angle, gradient and turning rate according to multivariate information such as current state parameters, environmental factors and air route planning targets of the aircraft, and safer and more efficient autonomous turning operation of the aircraft in a complex environment is realized.

The application discloses a kind of multi-constraint condition's fixed wing cluster unmanned aerial vehicle hover control method, it is related to unmanned aerial vehicle cluster flight control field, including the following steps: S1, long plane obtains hover parameter by hover instruction and analysis;S2, long plane is calculated by speed limit and is obtained long plane constraint speed range by multi-constraint speed limiting, so that long plane can enter hover and maintain hover state;S3, by the curve distance of wingman calculation, for the instruction value of evaluation roll angle;S4, wingman is constrained by the flight distribution situation and hover parameter that other unmanned aerial vehicle emits, if aircraft is close to long plane, first determine the constraint of nearest tangent circle to avoid the problem that aircraft enters circle after and generates same air line dislocation;S5, after wingman enters hover state, the instruction value of speed is calculated by calculating expected motion position, to control wingman hover process;The application can be autonomously coordinated to reduce the control pressure of formation collision avoidance, formation keeping demand.

A fuel oil monitoring system comprises a probe module and a signal processing module, the probe module is used for collecting fuel oil data, and the signal processing module is used for monitoring the fuel oil state in real time according to the collected fuel oil data and outputting an alarm signal; according to the utility model, the problems of reliability and detection efficiency of the traditional mechanical part are effectively solved, and the monitoring precision of the fuel level sensor is obviously enhanced; by monitoring the fuel stock of the fuel tank in real time and sending an alarm immediately when the fuel level drops to a safety lower limit value, the system ensures flight safety, gives sufficient time to a pilot to take action, and prevents potential crisis.

The utility model discloses a hand -throwing unmanned plane suitable for standardization batch production relates to unmanned plane technical field. The utility model discloses three -section foldable fuselage, three -section airfoil and three piece tail fin, through three -section modular fuselage and airfoil design, combine folding hinge positioning, lock catch rigid locking and quick -release dowel down -type locking mechanism, realize the quick disassembly of whole machine in 5 minutes, wherein airfoil carbon tube A inserts the automatic pilot electrical connector of conduction, and tail fin carbon tube B inserts synchronous meshing servo arm, and completely exempts manual wiring step, cooperate task cabin standardization interface, and support function module hot plug replacement. The design replaces traditional cementing technology with full bolt connection, reduces production cost, improves the battlefield deployment efficiency, and through double -insurance locking mechanism and carbon pipe enhanced torsional structure, ensures flight stability, satisfies the standardization batch production demand of military individual soldier carrying and emergency investigation.

The invention discloses an unmanned aerial vehicle state detection platform based on multiple sensors, and relates to the technical field of unmanned aerial vehicle detection, the unmanned aerial vehicle state detection platform comprises a detection platform, the upper surface of the detection platform is horizontally and fixedly provided with an input conveying belt, a clamping moving assembly, a main detection assembly, two transfer conveying assemblies, an auxiliary detection assembly and an output conveying belt, one side of the input conveying belt is provided with a transfer conveying assembly, the other side of the input conveying belt is provided with a main detection assembly, and the other side of the main detection assembly is provided with another transfer conveying assembly; the clamping moving assembly is arranged above the transfer conveying assembly on one side of the input conveying belt and the main detection assembly, and is fixedly assembled on one side surface of the detection platform; the auxiliary detection assembly is parallel to the input conveying belt and is placed between the two transfer conveying assemblies; the unmanned aerial vehicle fixing ring is horizontally placed on the upper surface of the input conveying belt; autonomous detection can be carried out through automatic operation, so that the unmanned aerial vehicle is effectively evaluated, and potential risks of the unmanned aerial vehicle are prevented.

This utility model discloses an irregularly shaped foldable three-axis drone frame and drone device, comprising: an assembly frame structure; a front rotor assembly structure, comprising two sets, the two sets of front rotor assembly structures being respectively and positionably interchangeably mounted on the front two sides of the assembly frame structure, and the rotation directions of the driving rotation ends of the two sets of front rotor assembly structures being opposite to each other; and a rear rotor assembly structure, comprising a single set, extending to the rear of the assembly frame structure, the rear rotor assembly structure having two sets of coaxially arranged driving rotation ends, the two sets of driving rotation ends being opposite to each other. This solves the technical problem in the prior art where drone frames struggle to simultaneously achieve portability and field of view advantages.

This utility model discloses a drop arrow for killing wild boars using a drone, relating to the field of drone accessory technology. The utility model includes an arrow shaft with an arrowhead on one side and fletching on the other side. A fixing component is provided on one side of the arrow shaft, including a mounting post installed on the side of the arrowhead. This utility model significantly improves the flexibility and adaptability of the drop arrow through modular design. The detachable connection structure between the arrow shaft and the arrowhead allows for quick replacement of the arrowhead or adjustment of the counterweight, thereby precisely adjusting the striking force for wild boars of different sizes. The counterweight is fitted onto the surface of the arrow shaft, and the weight can be increased or decreased according to actual needs, avoiding the drawback of traditional one-piece drop arrows that require complete replacement. The design of the fixing sleeve and the fletching ensures flight stability, while the interlocking structure of the square groove and the square post further prevents fletching deviation, ensuring the drop arrow maintains a precise trajectory after deployment and effectively improving the hunting success rate.

The utility model provides a remote control positioning device for an unmanned aerial vehicle, which belongs to the technical field of remote control of the unmanned aerial vehicle, aims to solve the problems of abnormal flight attitude, inaccurate positioning and the like caused by the fact that a key is easily reset due to unskilled operation or negligence of control of an operator, and comprises a remote control device main body, and a display screen is arranged on the rear side of the top end surface of the remote control device main body; the two protection supporting plates are hinged to the left side and the right side of the outer end of the display screen respectively; two ends of the protective support plate are hinged with the remote control device main body through connecting support shafts; the two driving supports are slidably arranged on the outer sides of the left and right end faces of the remote control device body respectively. The opening and closing control mechanism is arranged between the driving bracket and the protective support plate; the reset key is arranged on the front side of the top end face of the remote control device body. The mistaken touch prevention mechanism is arranged on the outer side of the reset key; and the phenomenon that an operator easily presses a reset key due to unskilled control or misoperation is greatly avoided, and smooth task execution of the unmanned aerial vehicle and flight safety of the unmanned aerial vehicle are guaranteed.

The invention provides an unmanned aerial vehicle routing inspection path automatic planning method for a power transmission line, and belongs to the technical field of unmanned aerial vehicle routing inspection. The problems that when an unmanned aerial vehicle conducts power transmission line inspection at present, picture shooting is not clear, and precise hovering cannot be achieved are solved. Comprising the following steps: acquiring position information of unmanned aerial vehicle inspection mark points of a power transmission line, and calculating coordinates; according to the PID parameters, dynamic models of the height and the attitude of the unmanned aerial vehicle are constructed; designing a path planning tracking controller based on a PID algorithm; according to the central position of the unmanned aerial vehicle and the distance between the unmanned aerial vehicle and the obstacle, the safety distance of unmanned aerial vehicle inspection flight in any direction is obtained, and inspection path planning is completed; calculating the current height and attitude of the unmanned aerial vehicle, and measuring and calculating the position and angle deviation between the current unmanned aerial vehicle and the corresponding task point; setting a deviation threshold value, measuring relative position deviation and angle deviation after the unmanned aerial vehicle arrives at the task point, and adjusting the height and posture of the unmanned aerial vehicle according to the deviation threshold value; the method is applied to power transmission line inspection.

The application relates to the technical field of building measurement construction, in particular to an equipment and a measurement method for automatically measuring prefabricated components based on a space scanning technology, which comprises a unmanned aerial vehicle, a measurement scanning equipment, a balance connecting mechanism and an auxiliary assembly; the unmanned aerial vehicle and the measurement scanning equipment are fixedly connected through the balance connecting mechanism, and the balance connecting mechanism guarantees the balance stability of the measurement scanning equipment during measurement work; through the cooperation of the unmanned aerial vehicle, the measurement scanning equipment and the balance connecting mechanism, the vibration generated in the balance state of the unmanned aerial vehicle in the air scanning work has a positive influence on the accuracy of the scanning work; the unmanned aerial vehicle and the measurement scanning equipment have a buffer stability protection function, and the stability of the connection between the two can be guaranteed in the continuous flight process; the equipment has corresponding work flexibility and improves the scanning work quality.

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 discloses an adjustable unmanned aerial vehicle load hanger belongs to unmanned aerial vehicle load mounting technical field, including fixed plate, adjusting mechanism, slide rail subassembly, load support and drive mechanism, and the fixed plate top surface is installed with the paired drive mechanism, and the both ends of fixed plate bottom surface are installed with the paired slide rail subassembly, and the adjusting mechanism is set up in pairs, and is installed in the fixed plate bottom surface, and one drive mechanism is connected with the one end transmission of each adjusting mechanism, and the other end of adjusting mechanism is connected on a slide rail subassembly, and the load support is set up in pairs, and both ends are installed on two adjusting mechanisms, and the paired load support is arranged in parallel between adjusting mechanism. The existing unmanned aerial vehicle hanger because specially for specific load custom, lead to when the load replacement needs to be re-customized, increase cost, reduce efficiency's problem is solved, has reduced the cost and time required for load replacement, and ensures the flight stability when mounting different loads.

The application relates to the technical field of unmanned aerial vehicles, and provides an unmanned aerial vehicle control method and device and electronic equipment. The method comprises the following steps: acquiring visual perception information and flight state parameters of an unmanned aerial vehicle; obtaining flight action parameters of the unmanned aerial vehicle at each decision moment by a trained reinforcement learning model according to the visual perception information and the flight state parameters; performing flight control evaluation on a target object according to the visual perception information to obtain flight control credibility of the target object; performing second-order smoothing constraint on the flight action parameters in the case that the flight control credibility meets preset credibility; and determining a flight control instruction for controlling the unmanned aerial vehicle according to the flight action parameters after the second-order smoothing constraint. The application can improve the control accuracy of the unmanned aerial vehicle in a complex environment scene and improve the flight stability of the unmanned aerial vehicle.

The invention discloses a quadrotor unmanned aerial vehicle near-earth operation task multi-mode control method and system and a storage medium, relates to the technical field of unmanned aerial vehicle control, and aims to solve the problem that an existing unmanned aerial vehicle control method is difficult to adapt to reliable flight control under ground disturbances at different heights by adopting a single-mode controller design. And the problem that anti-interference flight control of partial states can only be realized under the existing ground disturbance is solved. According to the invention, high-energy-efficiency control is carried out by utilizing extra lift force generated by ground turbulent flow, and a multi-mode height-dependent variable parameter controller is designed by distinguishing different modes at different heights, so that high-performance and high-energy-efficiency flight control at different heights near the ground can be realized. The flight length in the operation process is reduced, the lift force requirement of the rotor wings is lowered, and the purpose of cost-saving, efficiency-improving and high-energy-efficiency flight control is achieved. The flight stability of the unmanned aerial vehicle under near-earth disturbance is guaranteed, meanwhile, the energy loss of the unmanned aerial vehicle is reduced, the purposes of saving cost and improving efficiency are achieved, and high engineering application value is achieved.

The invention relates to the technical field of aircrafts, and provides an environment sensing method and device and an aircraft. The method comprises the following steps: acquiring a current environment image of an aircraft, and performing feature extraction on the current environment image to obtain image features of the current environment image; obtaining the prior distribution of the obstacle, wherein the prior distribution of the obstacle is generated in advance according to the three-dimensional occupied grid sample set; performing aggregation processing on the image features according to prior distribution of obstacles to obtain aggregation features; based on the aggregated feature, a three-dimensional occupancy grid corresponding to the aircraft is predicted, the three-dimensional occupancy grid being used to indicate an obstacle present in a flight environment of the aircraft. The sensing precision and real-time performance of the aircraft in a complex flight environment can be remarkably improved, and the flight stability and safety of the aircraft are effectively guaranteed.

The invention provides an unmanned aerial vehicle based on 5G communication and 3D technology and an operation method thereof.The unmanned aerial vehicle is characterized in that a top plate is fixedly installed at the upper end of an overall frame structure of the unmanned aerial vehicle, multiple sets of supporting frameworks are symmetrically fixed to the periphery of the top plate, and supporting legs making contact with the ground are symmetrically installed at the lower end of the overall frame structure; a plurality of support arms are symmetrically connected to the middle end of the integral frame structure, and positive paddles and negative paddles are mounted at the tail ends of the symmetrically arranged support arms; a chip of the unmanned aerial vehicle adopts a Raspberry Pi development chip, a built-in CMOS chip and a 5G millimeter wave reverse array extremely simple framework, and the unmanned aerial vehicle is built in a flight control mainboard and is connected with a first speed reduction stepping motor and a second speed reduction stepping motor through Dupont lines. And the WIFI chip in the connection interface connected with the VR glasses controls the unmanned aerial vehicle. The 5G communication technology and the 3D technology are combined, the flight stability of the unmanned aerial vehicle is improved, the flight safety is improved, and the unmanned aerial vehicle can well adapt to the complex and severe environment.

This invention belongs to the field of flight vehicle design technology, specifically relating to a performance testing system and method for large-size flight units. The system includes a test bench, a drive motor, a sensor module, a rotor module, a data acquisition card, a motor controller, a cooling system, a power distribution device, and a host computer. The positions of the rotor module and drive motor are adjusted via an adjustable platform. The cooling system and power distribution device achieve heat dissipation and power supply for the drive motor. The host computer performs linearity tests, square wave step tests, frequency sweep tests, and thermal balance tests, thereby obtaining the performance parameters and safe operating boundaries of the large-size flight unit under different positions, voltages, and heat dissipation conditions. This invention considers the high voltage and high heat dissipation requirements of large-size flight units, and designs auxiliary systems such as a cooling system and a bidirectional power distribution device, making it more suitable for actual application scenarios of large-size flight units, with smaller testing errors and strong applicability.