33results about How to "Stable and reliable flight" patented technology

The invention discloses an unmanned aerial vehicle autonomous navigation positioning method with assistance of visual information. The positioning method aims at providing accurate unmanned aerial vehicle navigation positioning information by making use of a visual sensor and corresponding visual ranging algorithm. In the method, speed and position information of the unmanned aerial vehicle are calculated through a combined visual ranging algorithm, and are used for assisting inertial navigation positioning. When a GNSS (Global Navigation Satellite System) signal is available, inertial navigation system error is corrected through inertial navigation / GNSS combined navigation, and a visual ranging evaluation criterion is established; when the GNSS signal is unavailable, the visual ranging evaluation criterion is used for evaluating the visual ranging result obtained by the combined visual ranging algorithm, error of a inertial navigation system is estimated and compensated with the visual ranging result and the visual ranging evaluation result, and thus, continuous and reliable navigation positioning information is provided for the unmanned aerial vehicle. The method provided by the invention can continuously and steadily provide accurate navigation positioning information for an unmanned aerial vehicle control system for long time.

The invention discloses an unmanned aerial vehicle self-navigation and positioning method based on multi-model distributed filtration and aims to reduce the calculation complexity of the unmanned aerial vehicle self-navigation and positioning method, meet a requirement of an embedded processor on real-time processing, guarantee stable control on an unmanned aerial vehicle and also ensure self-navigation and positioning of the unmanned aerial vehicle under a condition that a satellite navigation positioning system is unavailable within short time or long time. By the virtue of the unmanned aerial vehicle self-navigation and positioning method, measured values of motion of the unmanned aerial vehicle are obtained through different measurement systems and different sensors by constructing different orders of system state equations for estimating multi-mode distributed filtration states; a distributed filtration method is adopted to estimate and compensate an error of a low-cost inertial navigation system, so that continuous and reliable navigation and positioning information can be supplied to the unmanned aerial vehicle. The unmanned aerial vehicle self-navigation and positioning method disclosed by the invention can continuously and stably supply precise navigation and positioning information to an unmanned aerial vehicle control system for a long time.

The invention discloses an unmanned aerial vehicle uplink scheduling method for information flow QoS guarantee based on a TD-LTE technology. The method is cooperatively achieved by an information flow generation module, a classification mapping module, a scheduling module and a channel state detection module at an unmanned aerial vehicle communication terminal under the control of a plurality of signaling. The invention adopts a 4G communication network TD-LTE, and provides an unmanned aerial vehicle information flow classification mapping method and scheduling algorithm, which can provide differential transmission services for various kinds of information sent back to a control management center by an unmanned aerial vehicle during a flying process, and thus provides an effective link guarantee for reliable flying and high-quality information collection of the unmanned aerial vehicle.

The invention discloses a power transmission line inspection-based multi-rotor unmanned aerial vehicle inspection operation simulation training system. The power transmission line inspection-based multi-rotor unmanned aerial vehicle inspection operation simulation training system is established by using the virtual reality technology. The system includes a training host as well as an unmanned aerial vehicle remote controller, a keyboard, a mouse, a display, and a virtual reality helmet which are all connected with the training host in a wireless or wired manner; the training host is the mastercontrol device of the system, and is provided with a virtual unmanned aerial vehicle flight control simulation unit, a virtual unmanned aerial vehicle flight simulation unit, a training evaluation management unit, a defect location and identification unit, a database unit and a background management unit; the unmanned aerial vehicle remote controller, the keyboard and the mouse are all the inputdevices of the system; and the display and virtual reality helmet are the display devices of the system. The simulation training system of the present invention can be used not only to improve the unmanned aerial vehicle inspection operation control skills of operators and but also to prevent unnecessary loss of personnel, grid lines, or unmanned aerial vehicles due to the improper handling of special circumstances.

The invention discloses a double-oar damping rotor unmanned aerial vehicle, including a fuselage and at least four rotors fixedly connected with the fuselage. Each of the at least four rotors includes the following parts: a driving part, which includes a first motor and a second motor relatively fixedly connected with the first motor; a rotation shaft, which comprises a first rotation shaft and a second rotation shaft, wherein the first rotation shaft and the second rotation shaft are respectively connected with the first motor and the second motor, and the first rotation shaft and the second rotation shaft can respectively rotate relative to the axis of the rotation shaft; a propeller hub; blades; and a support. The invention solves the technical problems of unstable flight and loss caused by vulnerability to the impact of foreign matters in the unmanned aerial vehicle of the prior art, and reaches the technical effect of stable and reliable flight of unmanned aerial vehicle and avoidance of the impact of foreign matters.

The invention discloses a pesticide spraying device for an unmanned aerial vehicle. The pesticide spraying device comprises a machine body, a conveying pump and liquid drug boxes, wherein a spraying pipe is connected with a liquid outlet of the conveying pump; two liquid drug boxes are arranged; the two liquid drug boxes are respectively fixedly welded in a left foot bracket and a right foot bracket of the machine body; a cross beam is arranged between the left foot bracket and the right foot bracket of the machine body; the conveying pump is mounted on the middle part of the cross beam; a first liquid pumping straight pipe is arranged on a first liquid drug box; a first hose leading to the bottom of the first liquid drug box is connected with the first liquid pumping straight pipe; a second liquid pumping straight pipe is arranged on a second liquid drug box; a second hose leading to the bottom of the second liquid drug box is connected with the second liquid pumping straight pipe; a liquid pumping pipe of the conveying pump is simultaneously connected with the first liquid pumping straight pipe and the second liquid pumping straight pipe through a tee-joint pipe. According to the invention, the volume of the space structure of the unmanned aerial vehicle is reduced and the unmanned flying loss is reduced; the operation of frequently repeatedly loading liquid drug is not required and the time is saved; the unmanned aerial vehicle has better balancing property during a flying process and can stably and reliably fly.

The invention relates to an efficient drone for logistics distribution and with flight stability. The efficient drone comprises a main drone body, several conveying devices and several flight mechanisms, the conveying devices comprise adjusting mechanisms, adjusting plates and conveying mechanisms, the adjusting mechanisms comprise connecting rods, rotary plates, rotary assemblies and translationassemblies, and the translation assemblies comprise first motors, bearings, lead screws and translation blocks; the conveying mechanisms comprise detection assemblies, detection plates, lifting assemblies, lifting plates, air pumps and several fixing assemblies, and the fixing assemblies comprise air cylinders, pistons, vertical plates, bottom plates and fixing units. According to the efficient drone for logistics distribution and with flight stability, loading and unloading of goods are facilitated through the conveying mechanisms, the efficient drone conveniently carries multiple goods for conveying at a time, and the logistics distribution efficiency is improved; besides, by detecting the weight of the goods, the adjusting mechanisms control the positions of adjusting plates, thus the gravity center of the drone is adjusted to be located on the central axis of the main drone body, steady flight of the drone is facilitated, and the practicability of the drone is improved.

The invention provides an attitude control method adaptive to a long-time out-of-control state and belongs to the technical field of carrier rocket control. The method comprises the steps that after starting control, the angular speed is reduced through angular speed control; to ensure that the angular speed of three channels is reduced rapidly, a spray pipe continuous opening working mode is adopted, corresponding spray pipes are opened for the three channels according to the direction of the angular speed until the angular speed is reduced to 0, and when the last angular speed of the three channels is reduced to the level near 0, the three channels are switched to control based on attitude angular deviation at the same time. In the control process of attitude angular deviation, the angular deviation of attitude control under a rocket system is calculated according to a program quaternion and an actual quaternion. By means of the attitude control method adaptive to the long-time out-of-control state, the attitude that an orbit transfer vehicle deviates from a standard trajectory can be suppressed quickly, and it is ensured that an air vehicle flies stably and reliably under full-space attitude orientation.

The invention provides a flight control shock absorption device and an unmanned aerial vehicle, and relates to the technical field of the unmanned aerial vehicle. The flight control shock absorption device is applied to a flight control box. The flight control shock absorption includes a shock absorption plate, a first pillar, a second pillar and a non- Newtonian fluid buffer layer. One end of thefirst pillar is connected with the shock absorption plate, and the other end of the first pillar is connected with the flight control box. One end of the second pillar is connected with flight control box, and the other end of the second pillar is connected with the non- Newtonian fluid buffer layer. The first pillar and the second pillar are correspondingly arranged on both sides of the flight control box. The flight control shock absorption device can play a good role in the shock absorption towards the flight control box, so that the damage to the flight control box during the tumbling process of the unmanned aerial vehicle is avoided, and the operation of the unmanned aerial vehicle is safer and more reliable. The fixing towards the flight control box is achieved, the shock absorptioneffect is achieved, and a stable and reliable working environment for an unmanned aerial vehicle flight control system is provided.

The invention discloses a multifunctional unmanned aerial vehicle (UAV) suitable for electric power patrol inspection, which comprises a UAV main body, an object cavity is arranged in the UAV main body, and a plurality of rotor flying devices are arranged on the sides of the UAV main body. An upper end of that main body of the unmanned aerial vehicle is provided with a waterproof upper shell, anda first waterproof sealing ring is arranged between the waterproof upper shell and the main body of the unmanned aerial vehicle; an electronic component mounting cavity with an opening facing upward is arranged in the middle of the aluminum radiator in the housing cavity. The side surface of the waterproof upper shell is an arc surface, the upper end surface of the waterproof upper shell is a plane, the waterproof upper shell is made of transparent plastic material, the upper end surface of the waterproof upper shell is fixedly provided with an automatic cable grasping manipulator, and the waterproof upper shell is fixedly provided with a thermal infrared imager, a video camera and an ultrasonic flaw detector. The technical scheme has the advantages of reasonable structure design, simple structure, easy assembly and disassembly, good waterproofing performance, long working time, convenient use and normal operation under harsh conditions such as rainy day and night.

The invention relates to a static test device and method for a power element of a high-altitude full-electric UAV, and belongs to the technical field of performance test of small UAV. The test deviceis mainly composed of a simulated high-altitude pressure chamber and a power element performance test platform. The simulated high-altitude pressure chamber simulates atmospheric pressures in different flight high-altitude environments and realizes axial positioning of the power element performance test platform, and the power element performance test platform measures parameters including a thrust of a power system, the input electric energy power, a rotating speed of a blade and the motor temperature comprehensively. The method based on the test device can be used to measure the performanceparameters of the power elements of the UAV in the simulated high-altitude flight environment accurately, static test of the power elements is effectively combined with the test environment, the method and device are adapted to performance test of different parameter function parts, and the technical problem in evaluating performances of the power system in different flight environments in the research process of the high-altitude full-electric VAV is solved.

The invention belongs to the field of unmanned aerial vehicles, and discloses an opposed power generation module which comprises an engine assembly, a driving shaft assembly and power generator assemblies. The engine assembly comprises an air cylinder support, air cylinders, a crankcase and an engine output shaft; the two air cylinder are arranged on two sides of the crankcase front and back; pistons of the two air cylinders are connected with a crankshaft and connecting rod mechanism in the crankcase; the crankshaft and connecting rod mechanism is connected with the engine output shaft; the driving shaft assembly comprises a driving shaft and a driving wheel; two groups of power generator assemblies are arranged; each group of power generator assembly comprises a power generation support,a power generator, a driven shaft, a driven wheel, a belt and a fan; and the two driven shafts are left-and-right symmetrically arranged on two sides of the driving shaft. The opposed power generation module provided by the invention offsets a pull force of the driving shaft, so that a bending force stressed on the driving shaft is reduced, the structure is compact, and the layout is reasonable;and the unmanned aerial vehicle acquires electric energy through the opposed power generation module so as to have a long flight time.

The invention provides an aircraft oil-electricity hybrid energy supply system, an aircraft and a control method thereof. The energy supply system comprises an engine system, an engine controller, a power system and a fuel system; the engine system comprises an engine and a generator; the fuel system is connected with the engine through an oil way; the power output end of the engine is in drivingconnection with the generator; the generator is connected with the engine controller, and the engine controller is in control connection with the power system. Chemical energy generated in the fuel combustion process is converted into mechanical energy of the engine; the engine transmits mechanical energy to the generator to move, the generator converts the mechanical energy into electric energy,and the engine controller distributes the electric energy to the power system after rectifying the electric energy; compared with a pure electric aircraft, the cruising ability of the hybrid system ishigher, the engine does not directly drive the power system to work, and the aircraft is more stable and reliable in the flying process.

The invention relates to an unmanned aerial vehicle, in particular to an indoor unmanned aerial vehicle which comprises a multi-rotor unmanned aerial vehicle body and a flight detection device, wherein the flight detection device is used for detecting flight parameters; a path detection device which is used for detecting flight path parameters; and a control device which is electrically connectedwith the motor of the multi-rotor unmanned aerial vehicle, the flight detection device and the path detection device, and is used for controlling the unmanned aerial vehicle according to the detectedflight parameters and flight path parameters. The indoor unmanned aerial vehicle is suitable for indoor flight so as to realize autonomous positioning, environmental perception and flight path determination of the unmanned aerial vehicle under the condition of no external GPS positioning signal and autonomous flight under the condition of guaranteeing the safety of workers, and the flight is stable and reliable.

The invention discloses an unmanned aerial vehicle line inspection control system based on video image processing, comprising a four-rotor unmanned aerial vehicle platform, a video acquisition module,a PC, a flight control board, a wireless image transmission module, and a wireless data transmission device. A video acquisition module mounted on the four-rotor unmanned aerial vehicle platform acquires a video image. The image is transmitted to the PC through the wireless image transmission module, and is processed by using an upper computer image processing program of the PC end. A line inspection flight control command is obtained, and transmitted to the unmanned aerial vehicle by the wireless data transmission device, is input to a flight control board as a navigation command, and corrects the PD control error of the flight attitude to realize the autonomous line inspection flight control. The unmanned aerial vehicle line inspection control system based on the video image processingcan be used for the electric maintenance line inspection, and realizes the line inspection flight of the ground guide by a digital camera loaded by the unmanned aerial vehicle itself and a wireless image transmission system.

The invention discloses an urban flight route planning system and method for an unmanned aerial vehicle based on Cell-ID. The system comprises a 360-degree narrow-band antenna, an unmanned aerial vehicle and a plurality of communication base stations, wherein the 360-degree narrow-band antenna is installed below the unmanned aerial vehicle, and the data interaction transmission exists between theunmanned aerial vehicle and the plurality of communication base stations. The planning method comprises the following steps: carrying out the preliminary route planning; correcting the route of the unmanned aerial vehicle to obtain a corrected route; carrying out route verification on the corrected route; outputting the flight route, and outputting the verified flight route. The route planned by using the method can guarantee the data communication quality in the flight process, so the unmanned aerial vehicle is not influenced by mirror reflection and a wireless signal multipath effect, the urban flight safety problem of the unmanned aerial vehicle is solved, and the flight of the unmanned aerial vehicle is reliable and stable.

The invention discloses an ornithopter transmission component based on a Y-shaped structure and an implementation method and solves the problems that a slotted transmission component in the prior arthas transmission instability, a main wing beam of a wing is prone to deforming and being damaged, and rotational freedom is redundant. The ornithopter transmission component based on the Y-shaped structure is characterized by comprising a transmission rocker, wherein one end of the transmission rocker is set in a V shape, a first spherical bearing connected with a driving wheel is arranged at theother end of the transmission rocker, second spherical bearings connected with the main wing beam of the wing are arranged on the two sides of the V-shaped end of the transmission rocker, and a structure of the whole transmission component is arranged in a Y shape.

The invention discloses a method and system for establishing an electronic fence of an unmanned aerial vehicle, and electronic equipment, which are used for mining potential associations of working parameters of the unmanned aerial vehicle among different frequencies and among parameter categories based on a spatial convolution mechanism and further considering a multi-frequency path loss effect to determine whether the to-be-calculated distance is within the range of the electronic fence. Therefore, the distance of the virtual electronic fence is set based on the artificial intelligence technology, so that reliable flight of the unmanned aerial vehicle in the fence can be realized, and the personal safety, the power grid safety and the equipment safety are ensured.

The invention discloses an unmanned aerial vehicle controller with an aerial photography function, comprising a controller body, a data transmission unit is arranged at the center of the front end of the controller body, and the controller body is electrically connected to the data transmission unit , the right side of the data transmission unit is provided with a positioning unit, and the controller body is fixedly connected to the positioning unit, and the upper side of the data transmission unit is provided with a data acquisition instrument, by adopting the integration of an aerial display and a camera, Realize the stable aerial photography, and use the command execution button to execute the flight mission command, improve the functionality of the UAV controller, use the steering wheel to control the UAV freely, easy to operate, and reduce labor intensity at the same time. Reduce operating procedures, avoid errors in operation, improve the quality of aerial imaging, and use aerial processors to process images captured by the camera in a timely manner, which is conducive to timely transmission of aerial images to the controller.

The invention provides a cascaded deformation sensor based on a multi-core spiral fiber bragg grating, which is characterized in that a torsion area is prepared on a multi-core optical fiber to form the multi-core spiral optical fiber, then the fiber bragg grating is prepared in the torsion area, the spiral fiber bragg grating is used as a sensing unit, and a plurality of spiral fiber bragg gratings are cascaded to form a sensor array. The sensor is embedded into an object to be measured, curvature and flexibility conversion is carried out on each group of wavelength difference, and finally, the change of the shape of the object is obtained through inversion by utilizing the difference and fitting. The sensor can be used for online measurement of torsion, bending and other parameters, and has the functions of sensing and positioning a deformed object.

The invention belongs to the technical field of drone battery protection, and discloses a battery thermal insulation heating control system and method in a low temperature environment, a drone and a medium, and a battery thermal insulation heating transport box provides a storage and transportation box for drone batteries; The intelligent battery temperature control system is integrated in the battery thermal insulation heating transport box for temperature management involved in the intelligent battery of the drone; the drone low temperature algorithm system is integrated in the battery thermal insulation heating transport box for realizing The flight strategy adopted by the drone when it detects that the outside is in a low temperature environment. The invention solves the lossless heat preservation and heating of the battery through the battery heat preservation and heating transportation box, uses the battery temperature control system to ensure the real-time monitoring of the battery temperature, and ensures the battery safety state before take-off through the unmanned aerial vehicle low temperature algorithm, and realizes the unmanned aerial vehicle. reliable flight in low temperature environment. The invention can ensure the safety and reliability of unmanned aerial vehicle flight under low temperature environment.

The invention discloses a rotorless remote-controlled aircraft, which belongs to the field of jet aircraft. The rotorless remote control aircraft of the present invention comprises an annular blast cavity, a turbine blow mechanism and a bin body, the bin body is fixed in the middle of the annular blast cavity, an annular cavity is arranged in the annular blast cavity, and an annular cavity is arranged in the annular cavity. There are at least three sets of partitions that equally divide the annular cavity into mutually independent areas, and the middle part of each independent area of ​​the annular cavity is correspondingly provided with a set of evenly arranged on the outer wall of the annular blast cavity for blowing the air to the annular A turbine blowing mechanism that blows air into the cavity. The annular blowing cavity is provided with a circle of air jets that can jet downward to provide lift. The annular cavity is also equipped with a steering mechanism that can drive the diaphragm to rotate to change the direction of the jet. . The aircraft of the present invention has simple and compact structure, strong flight power, stable and reliable flight, simple and convenient control, and strong battery life; at the same time, the aircraft is safer to use and meets the needs of young children.

The present invention discloses a UAV uplink scheduling method based on TD‑LTE technology oriented to QoS guarantee of information flow: an information flow generation module, a classification mapping module, a scheduling module and a channel state detection module at the UAV communication terminal , and the wireless resource configuration module, the channel state detection module and the information flow recovery module at the eNodeB are cooperatively implemented under the control of various signaling. The present invention adopts the 4G communication network TD-LTE, and proposes a UAV information flow classification mapping method and scheduling algorithm, which can provide differentiated transmission services for various types of information sent back to the control management center by the UAV during flight , to provide an effective link guarantee for the reliable flight of UAVs and the acquisition of high-quality collection information.

The invention discloses a power transmission line inspection-based multi-rotor unmanned aerial vehicle inspection operation simulation training system. The power transmission line inspection-based multi-rotor unmanned aerial vehicle inspection operation simulation training system is established by using the virtual reality technology. The system includes a training host as well as an unmanned aerial vehicle remote controller, a keyboard, a mouse, a display, and a virtual reality helmet which are all connected with the training host in a wireless or wired manner; the training host is the mastercontrol device of the system, and is provided with a virtual unmanned aerial vehicle flight control simulation unit, a virtual unmanned aerial vehicle flight simulation unit, a training evaluation management unit, a defect location and identification unit, a database unit and a background management unit; the unmanned aerial vehicle remote controller, the keyboard and the mouse are all the inputdevices of the system; and the display and virtual reality helmet are the display devices of the system. The simulation training system of the present invention can be used not only to improve the unmanned aerial vehicle inspection operation control skills of operators and but also to prevent unnecessary loss of personnel, grid lines, or unmanned aerial vehicles due to the improper handling of special circumstances.

The invention relates to a flying-saucer-type land-air amphibious bamboo cutting machine, and belongs to the technical field of agricultural machinery. The flying-saucer-type land-air amphibious bamboo cutting machine comprises a rack, the top of the rack is provided with a cab, and a start button connected with a vertical shaft engine is arranged in the cab; the rack is provided with the vertical shaft engine and a dual-clutch transmission which are connected through a shaft, a back drive shaft of the dual-clutch transmission is connected with a back rotary wing drive shaft through a transmission part, the two ends of the back rotary wing drive shaft are connected with a back rotary wing and a back wheel drive shaft through clutches respectively, the back wheel drive shaft drives back walking wheels to walk, a front drive shaft of the dual-clutch transmission is connected with a front transmission shaft through a transmission part, the front transmission shaft is connected with a front rotary wing, a disc saw and a front wheel drive shaft through the matched clutches respectively, and the front wheel drive shaft drives front walking wheels to walk. The flying-saucer-type land-air amphibious bamboo cutting machine is simple in structure, safe and efficient, can walk on the flat land and also can fly across obstacles such as a ravine and a mountain slope through the rotary wings, continuous and automatic bamboo cutting is achieved, and the requirements of bamboo cutting in a hilly and mountains region can be well met.

The invention discloses an unmanned aerial vehicle autonomous navigation positioning method with assistance of visual information. The positioning method aims at providing accurate unmanned aerial vehicle navigation positioning information by making use of a visual sensor and corresponding visual ranging algorithm. In the method, speed and position information of the unmanned aerial vehicle are calculated through a combined visual ranging algorithm, and are used for assisting inertial navigation positioning. When a GNSS (Global Navigation Satellite System) signal is available, inertial navigation system error is corrected through inertial navigation / GNSS combined navigation, and a visual ranging evaluation criterion is established; when the GNSS signal is unavailable, the visual ranging evaluation criterion is used for evaluating the visual ranging result obtained by the combined visual ranging algorithm, error of a inertial navigation system is estimated and compensated with the visual ranging result and the visual ranging evaluation result, and thus, continuous and reliable navigation positioning information is provided for the unmanned aerial vehicle. The method provided by the invention can continuously and steadily provide accurate navigation positioning information for an unmanned aerial vehicle control system for long time.

The invention provides an attitude control method adaptive to a long-time out-of-control state and belongs to the technical field of carrier rocket control. The method comprises the steps that after starting control, the angular speed is reduced through angular speed control; to ensure that the angular speed of three channels is reduced rapidly, a spray pipe continuous opening working mode is adopted, corresponding spray pipes are opened for the three channels according to the direction of the angular speed until the angular speed is reduced to 0, and when the last angular speed of the three channels is reduced to the level near 0, the three channels are switched to control based on attitude angular deviation at the same time. In the control process of attitude angular deviation, the angular deviation of attitude control under a rocket system is calculated according to a program quaternion and an actual quaternion. By means of the attitude control method adaptive to the long-time out-of-control state, the attitude that an orbit transfer vehicle deviates from a standard trajectory can be suppressed quickly, and it is ensured that an air vehicle flies stably and reliably under full-space attitude orientation.

The invention relates to a static test device and method for a power element of a high-altitude full-electric UAV, and belongs to the technical field of performance test of small UAV. The test deviceis mainly composed of a simulated high-altitude pressure chamber and a power element performance test platform. The simulated high-altitude pressure chamber simulates atmospheric pressures in different flight high-altitude environments and realizes axial positioning of the power element performance test platform, and the power element performance test platform measures parameters including a thrust of a power system, the input electric energy power, a rotating speed of a blade and the motor temperature comprehensively. The method based on the test device can be used to measure the performanceparameters of the power elements of the UAV in the simulated high-altitude flight environment accurately, static test of the power elements is effectively combined with the test environment, the method and device are adapted to performance test of different parameter function parts, and the technical problem in evaluating performances of the power system in different flight environments in the research process of the high-altitude full-electric VAV is solved.