150 results about "Flight instruments" patented technology

An unmanned aerial vehicle that transports harvested crops harvested from a field, includes a flight device to cause the unmanned aerial vehicle to fly, a controller configured or programmed to control operation of the flight device, a communication device to receive package position information indicating a first position where a target package for transport containing the harvested crops is located, and package weight information, and a support device to support the target package. The controller is configured or programmed to determine, based on the package weight information, whether the target package can be transported to a second position different from the first position, and when doing so, control the flight device to cause the unmanned aerial vehicle to fly to the first position, cause the support device to support the target package, and control the flight device to cause the unmanned aerial vehicle to fly to the second position.

The invention discloses a fan blade transportation and installation system and method and a flight device, and belongs to the technical field of intelligent transportation of fan blades. The system comprises a flight transportation module, an intelligent navigation control module, an installation auxiliary module and a scheduling module; the flight transportation module is used for suspending and loading the fan blades, and suspending, flying and transporting the fan blades according to a preset flight route; the intelligent navigation control module is used for monitoring a flight path, collecting flight data and environment data in a flight process, predicting potential obstacles according to the flight data and the environment data, and optimizing a flight strategy; the mounting auxiliary module is used for aligning and fastening the blades and the fan hub; the scheduling module is used for determining a flight plan according to the meteorological data, the performance of the flight transportation module and the priority of the transportation installation task. By combining a plurality of transportation, installation and dispatching modules, efficient and safe transportation and installation of the fan blades are achieved, and the transportation and installation difficulty and cost are reduced.

The invention provides a real-time modeling method and system for cooperative work of land and flight scanning devices, and relates to the technical field of scanning and modeling. The method comprises the following steps: preliminarily scanning a target area by using a land scanning device to generate three-dimensional point cloud data; a flight scanning device is used for conducting supplementary scanning on the complex area, and the coverage blind area of ground scanning is made up; fusing the land scanning data and the flight scanning data to generate a high-precision three-dimensional model; based on real-time data analysis, a flight path is dynamically adjusted to improve scanning efficiency and coverage rate. Through cooperative work of the land and the flight device, the modeling precision and efficiency are effectively improved, and the method is suitable for complex terrains and multi-scene application and has high real-time performance and reliability.

Provided is a flight device and a flight device control method that ensure safety even if a defect occurs in a power connection / disconnection unit. Rotor-side power transmission units 26 of a flight device 10 include first and second rotor-side power transmission units 261 and 262. Power connection / disconnection units 27 transmit power according to conditions and include first and second power connection / disconnection units 271 and 272. The first power connection / disconnection unit 271 is provided between a first engine-side power transmission unit 251 and the first rotor-side power transmission unit 261. The second power connection / disconnection unit 272 is provided between a second engine-side power transmission unit 252 and the second rotor-side power transmission unit 262. The arithmetic control unit 31 changes the flight status when the degree to which the first power connection / disconnection unit 271 transmits the power and the degree to which the second power connection / disconnection unit 272 transmits the power differ by a certain amount or more.

A laser scribing system, comprising: a bearing mechanism (10), wherein a bearing region (111) for bearing a product (200) is formed on the surface of one side in a first direction; shaping devices (20) respectively arranged on two sides of the bearing region in a second direction, wherein at least a part of each shaping device can move relative to the bearing mechanism in the second direction so as to abut against the side surface of the product in the second direction, and the shaping devices arranged corresponding to the bearing region cooperate with each other to adjust the position of the product on the bearing region; and a flying device (30) and a flying driving device that are connected to each other, wherein the flying driving device can drive the flying device to move in a third direction, first laser can be emitted in the first direction by means of the flying device to scribe the product shaped by means of the shaping devices on the bearing mechanism, and the first direction, the second direction and the third direction intersect in pairs. Also provided is a laser scribing method. The scribing system can ensure that the position of a product before laser scribing is accurate, ensures the scribing precision, can control the flying device to fly at an extremely fast speed, has a fast scribing speed, and improves the scribing efficiency.

A system includes a processor that controls an operable flying device, controls an operable imaging means, performs real-time analysis of generated data using artificial intelligence processing means, calculates an optimal rescue route based on the analysis results, controls means for loading and transporting supplies with the flying device, controls means for deploying equipment in regions where communication is disrupted and collecting local condition data, analyzes the collected data to generate emergency response information, and communicates the emergency response information to external rescue organizations.

The invention relates to the field of concrete carbonization depth measurement, and discloses an unmanned aerial vehicle for detecting the concrete carbonization depth of a high-altitude difficult-to-reach part and a detection method.The unmanned aerial vehicle for detecting the concrete carbonization depth of the high-altitude difficult-to-reach part comprises a flying device used for conveying the device to the concrete surface of a high-altitude difficult-to-reach area; the adsorption device is used for stably adsorbing the flying device on the surface of concrete and counteracting the counter-acting force of the electric percussion drill; the electric percussion drill is used for drilling holes in the concrete surface; the electric actuating device is used for pushing the electric percussion drill to perform drilling operation; and the multifunctional spraying device is used for cleaning the hole and spraying a developing agent after drilling. The device is conveyed to the concrete surface of a high-altitude difficult-to-reach area through the flying device, the flying device is stably adsorbed to the concrete surface through the adsorption device, the electric percussion drill 7 is pushed by the electric actuating device to conduct drilling operation, and a hole is cleaned and a developing agent is sprayed through the multifunctional spraying device after drilling.

A flying vehicle is disclosed with a plurality of projectile systems that each contains a projectile for projecting at another flying device. The flying vehicle can include a control system, a flight system in communication with the control system for enabling the flying vehicle to fly, a first projectile system in communication with the control system and a second projectile system in communication with the control system. The control system determines, based on a characteristic of a target flying vehicle, whether to implement a first mode utilizing the first projectile system or a second mode utilizing the second projectile system to capture the target flying vehicle.

The present invention provides a flying apparatus that can accurately measure a weight of a transported objected in a simple configuration. The flying apparatus 10 includes rotors 11, motors 12, a flight sensor 13, an electric power conversion unit 14, and a computation control unit 15. The flight sensor 13 measures physical quantities acting on a fuselage base portion 16. The computation control unit 15 generates instruction signals based on the physical quantities to cause the fuselage base portion 16 to be at a predetermined position in a predetermined attitude. The electric power conversion unit 14 adjusts amounts of electric power supplied to the motors 121 and the like based on the received instruction signals. Moreover, the computation control unit 15 calculates an estimated weight that is an estimation value of a weight of the transported object, based on magnitudes of the instruction signals.

The invention discloses an unmanned aerial vehicle formation flight control system and method based on a virtual host, an unmanned aerial vehicle formation flight device comprises a virtual host unit, a communication unit and a plurality of slave units, and the virtual host unit simulates the flight state of the whole formation. The slave unit maintains the formation and responds to the flight state of the virtual host, the communication unit communicates between the host unit and the slave unit, and the unmanned aerial vehicle formation flight method comprises the steps of initialization, takeoff, position point matching, formation forming, virtual host flight, state judgment, slave following flight, landing and the like. Step consistency is maintained between the virtual host unit and the slave unit through the communication unit. The host in the unmanned aerial vehicle formation is simulated by a program and is not actually existing, and all actually existing unmanned aerial vehicles are equivalent to slaves, so that the negative effects of formation flight caused by errors and abnormities of the host are reduced, and the accuracy and the stability of the formation flight are improved.

The embodiment of the invention provides a safety monitoring method and system for a VR flight device, and the method comprises the steps: firstly obtaining a real-time operation data set of the VR flight device, and enabling the real-time operation data set to cover environment perception data and equipment state data; performing safety analysis processing on the real-time operation data set to generate a safety state evaluation result, performing dynamic safety strategy matching processing based on the safety state evaluation result to obtain a safety regulation and control instruction, finally adjusting operation parameters of the VR flight device according to the safety regulation and control instruction, and triggering early warning feedback operation. Therefore, the operation safety of the VR flight device can be comprehensively and dynamically monitored, potential risks can be found in time, effective regulation and control are carried out, and stable operation of equipment and user safety experience are guaranteed.

The invention relates to the technical field of unmanned aerial vehicles and concrete strength detection, and discloses a high-altitude difficult-to-reach part concrete strength detection unmanned aerial vehicle and a detection method.The high-altitude difficult-to-reach part concrete strength detection unmanned aerial vehicle is characterized in that a flight device is composed of a fuselage, propellers and a battery, and the flight device is used for enabling the unmanned aerial vehicle to reach a high-altitude difficult-to-reach area part; the adsorption device comprises at least three vacuum chucks, the vacuum chucks are connected with the connecting rod in a hinged manner, and the electric actuating device drives the rebound device to detect the strength of concrete, so that the concrete strength detection device has the effects of safety, stability and detection of the strength of the concrete at a high-altitude difficult-to-reach part. Through the strong load-carrying flying capability and the precise hovering control function of the flying device and the stable adsorption and angle adjustment effects of the adsorption device, the concrete strength detection device can reach a high-air-difficult-to-reach part of a concrete structure during use, and the concrete strength detection effect of the high-air-difficult-to-reach area is achieved.

According to an embodiment, a control device controls a user-wearable flight device and includes a processing unit configured to acquire state data related to a state of the flight device and manipulation data related to a manipulation of the flight device, input the acquired state data and the acquired manipulation data to a model trained using deep reinforcement learning, and control the flight device on the basis of an output result of the model to which the state data and the manipulation data are input.

To provide a flight device that can measure a weight of a transported object accurately with a simple configuration.SOLUTION: A flight device 10 is provided with a rotor 11, a motor 12, a flight sensor 13, a power conversion unit 14, and a computational control unit 15. The flight sensor 13 measures a physical quantity acting on an airframe base 16. The computational control unit 15 generates an instruction signal on the basis of the physical quantity so that the airframe base 16 assumes a prescribed position and attitude. The power conversion unit 14 regulates an amount of electric power supplied to the motor 121 and the like on the basis of the inputted instruction signal. Additionally, the computational control unit 15 calculates an estimated weight, that is, an estimated value of a weight of a transported object, on the basis of a magnitude of the instruction signal.SELECTED DRAWING: Figure 3

The present invention relates to a capture claw (10) for capturing an aircraft (300) by means of a physical intervention, wherein the capture claw (10) comprises at least one capture arm (12) which has at one end a coupling section (14) configured to functionally couple the capture arm (12) with a first aircraft (100), in particular a first unmanned aircraft (100); the capture arm (12) has at least one capture tooth (16) at an end opposite the coupling section (14); and the grasping claw (10) is designed with a claw mechanism, wherein the claw mechanism is configured to move the at least one grasping arm (12) from a starting position (30) in which the grasping arm (12) is at least partially in contact with the first flying device (100) to an engagement position (50) in which the at least one fang tooth (16) of the grasping arm (12) engages with a second flying device (300).Furthermore, the invention relates to an unmanned aerial vehicle (100) comprising a capture claw (10).

Provided is a flying apparatus in which components housed under a cover can be cooled effectively.　A flying apparatus 10 comprises an airframe 11 and a cover 12 that covers the airframe 11. The cover 12 has a cover front-face part 121 and a cover rear-face part 122. A front-face opening 131 is formed by providing an opening in the cover front-face part 121, and a rear-face opening 132 is formed by providing an opening in the cover rear-face part 122. According to the present invention, when the flying apparatus 10 flies, flight airstream that is introduced from the front-face opening 131 and is discharged from the rear-face opening 132 is allowed to circulate in good condition inside the cover 12. Hence, an engine 25, electrical equipment, and the like embedded under the cover 12 can be cooled in good condition.

Provided is a flying device capable of effectively operating an engine during flight.　The flying device 10 is a device that floats in the air by means of thrust generated by the rotation of a rotor 14. A flying device 10 includes a machine body 19, an engine 30, a tank 27, and an electric component 28. An internal space 29 of the machine body 19 is partitioned into a first space 291 and a second space 292 by the tank 27. The engine 30 is disposed in the first space 291. The electric component 28 is disposed in the second space 292.

The invention provides a water tank icing prediction method for a flight device, a computer device and a computer readable storage medium, and the method comprises the steps: intercepting a cross section of a water tank in the flight device from a three-dimensional geometric model of the flight device, stretching the cross section according to the volume of the water tank, and forming a preset three-dimensional water tank model, stretching according to a preset three-dimensional water tank model to generate a preset computational domain; generating a preset grid according to a preset computational domain; configuring an airflow model, a water phase change model and a thin-wall heat conduction model for the preset computational domain, and setting boundary conditions for the preset computational domain to form an icing prediction model; simulating the icing prediction model according to the numerical value of the preset working condition matrix to obtain icing prediction data; and judging the icing prediction data according to a preset grading system, generating a safety boundary curve graph, and outputting flight time suggestion information. The water tank structure is simplified, a large time step length is allowed to be adopted in the simulation process, and therefore the calculation efficiency is improved.

To provide an aircraft capable of absorbing the difference in load between the main rotor and the sub rotor. 【Solution means】The fuselage 11 of the aircraft 10 is configured to accommodate the engine 12 and the generator 13. The engine 12 generates power for rotationally driving the main rotor 15 and the sub rotor 16. The generator 13 is driven by the engine 12 to generate electric power for rotationally driving the motor 14. The motor 14 is rotationally driven by the electric power supplied from the generator 13. The main rotor 15 mechanically rotates by the rotational driving force of the engine 12 to generate a thrust for floating the fuselage 11. The sub rotor 16 rotates by the motor 14 to adjust the attitude of the fuselage 11 in the air. The power conversion unit 18 is configured to change the output of the generator 13 or the thrust of the main rotor 15.

The invention provides a flight device lifting object inclination measurement method based on double IMUs, a medium, a terminal, a system and a controller, and the method, the medium, the terminal, the system and the controller break through the technical bottleneck that traditional single sensor measurement is liable to be interfered and is obvious in delay through a cooperative measurement and precise calculation scheme based on the double IMUs. The three-dimensional space inclination state of a suspended object relative to an unmanned aerial vehicle body can be directly captured, high-precision quantification of core inclination parameters such as a roll angle, a pitch angle and a yaw angle is achieved, and real-time output of a measurement result is guaranteed by means of an efficient data processing algorithm. And the accurate matching of the data updating frequency and the unmanned aerial vehicle operation dynamic response demand is ensured. According to the technology, high-reliability feedback is provided for active anti-swing control, object swing is effectively restrained, and resonance is avoided; meanwhile, key indexes are provided for safety early warning, when inclination exceeds a threshold value, early warning can be rapidly triggered, emergency operation can be assisted, hidden dangers such as object falling and collision are remarkably reduced, and the stability, safety and efficiency of unmanned aerial vehicle hoisting operation are synchronously improved.

The present application provides a fall damage reduction system, a flying device, and a vehicle-mounted device. The flying device includes a flight communication section (24), a device fall determination section (25, S101), and a flight notification section (25, S104, S105). The flight communication section performs wireless communication in accordance with a communication standard for inter-vehicle communication. The device fall determination section determines whether the flying device is likely to fall. In a case where the flying device is determined by the device fall determination section to be likely to fall, the flight notification section transmits fall information including information indicating a presumed fall position via the flight communication section. The vehicle-mounted device includes a vehicle communication section (34) and a processing section (37, S207, S208, S210, S211, S212, S214, S215, S218, S219). The vehicle communication section performs wireless communication in accordance with a communication standard for inter-vehicle communication. In a case where the fall information is received via the vehicle communication section, the processing section executes fall avoidance processing that is processing for avoiding the fall position.

The utility model discloses a variable sweepback wing flight device which comprises a fuselage, wings and a vertical fin, a fixing plate is installed on the fuselage to install a steering engine, the steering engine is used for driving two clamping and locking gears fixedly installed on the wings, and sweepback movement of the wings is controlled in real time; meanwhile, clamping and locking control over the two clamping and locking gears is achieved through a shape memory spring which is fixedly installed on the machine body and can be electrically controlled, and clamping and locking pieces are arranged at the two ends of the shape memory spring; through the structural design of a motor, a conveyor belt, a battery and a belt pulley arranged in the fuselage, the gravity center of the whole flight device is adjusted in real time, and automatic balance control over the variable sweepback wings is achieved. According to the variable sweepback wing flight device, the sweepback movement of the sweepback wings can be accurately and steplessly controlled in real time in the flight process, the task execution capacity of different flight speeds can be considered, the weight can be reduced, and the size of a fuselage can be reduced.

A method for monitoring the coherence of an atmospheric pressure value to be used for configuring flight instruments of an aircraft includes: interrogating a database to obtain an altitude value of a selected airport; obtaining a static pressure value, a static temperature value, and a geometric altitude value, corresponding to a current situation of the aircraft; deducing therefrom an estimate of a static pressure value at the selected airport; evaluating a coherence level between the estimate and the atmospheric pressure value to be used for configuring the flight instruments of the aircraft; and generating a warning if the coherence level is below a predefined threshold.

Disclosed herewith is a cleaning system for cleaning an above ground channel. The cleaning system includes a cleaning unit having a cleaning head coupled to a cleaning body, a flying device coupled with the cleaning unit, and a remote controller configured to control the flying device and the cleaning unit. The flying device lifts the cleaning unit above the ground and positions the cleaning unit above the channel. The cleaning head includes an air blower or a rotary head. A cleaning method includes coupling a cleaning unit to a flying device, establishing a communication link between a remote controller and the cleaning unit, controlling the flying device to position the cleaning unit in a gutter channel; and controlling the cleaning unit to implement a cleaning operation in the gutter channel. The cleaning operation includes rotating a mechanical head or blowing air in the gutter channel.

This invention discloses a device for detecting and clearing ice and snow debris from power lines, comprising five parts: a crawling mechanism, an obstacle-crossing and clearing mechanism, an eddy current heating device, an autonomous power-collecting device, and a drone docking and flight device. The autonomous power-collecting device includes an electromagnetic power-collecting device and a pantograph contact power-collecting device. The crawling device and the eddy current heating device are located inside an openable structure, while the outside of the openable structure is connected to the electromagnetic power-collecting device and the obstacle-crossing and clearing mechanism. Drone docking and flight devices are located on both sides of the crawling device, with the pantograph contact power-collecting device placed on top of the drone docking and flight devices. A main control unit is located between the crawling device and the electromagnetic power-collecting device. This invention solves the problem that traditional mechanical clearing methods easily damage power lines and accelerate wear. Simultaneously, this invention also addresses the safety hazards faced by existing clearing equipment and personnel, as well as the problem of short single-operation time due to battery performance limitations.

1. Name of the product in this design: Core Strength Trainer (Simulated Wingsuit Flight Device). 2. Purpose of this design: Core muscle strength trainer (simulated wingsuit flight device). 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

The invention relates to the technical field of aircrafts, in particular to a flying device with a mooring ducted fan and an aerodyne. The split galloping vehicle has three operation modes: a land mode, a reconnaissance mode and a flight mode. When the split aerodyne runs in the land mode, the main running scene of the split aerodyne is land, the flying device does not participate in movement of the aerodyne body, and the flying device is fixed to the top of the aerodyne and does not affect the land running performance of the aerodyne; in the reconnaissance mode, the flight device lifts off and suspends to serve as a mooring type aerial reconnaissance platform, the automobile body is on the ground, and the flight device supplies energy through the automobile body; in the flight mode, the flight device is vertically lifted, and the automobile body is dragged to the air through the mooring rope to drive the automobile body to fly. The split aerodyne has all-region traffic capacity, and has the characteristics of convenience, stability and simplicity in operation when encountering steep slopes, broken bridges and collapsed terrains and climbing over hillsides and spaces within a short time.

The invention discloses a landing buffer mechanism and a flight device, and relates to the field of aircrafts. The landing buffer mechanism comprises at least one group of buffer components which are arranged below the wings. The buffer assembly comprises a shell, a plurality of buffer rods, a linkage unit and an elastic piece. The multiple buffer rods are assembled on the shell in a sliding mode, and at least part of rod bodies extend to the outer side of the shell. Each linkage unit is arranged between every two adjacent buffer rods and used for enabling the two buffer rods to move face to face or back to back when the buffer rods slide relatively. The elastic piece sleeves the outer wall of the linkage unit and is used for driving the buffer rod to reset. When the landing surface is flat, the plurality of buffer rods slide synchronously, and the elastic piece provides buffering; when a landing surface is uneven, the buffer rods slide independently according to terrain differences, relative movement is generated through the linkage units to be matched with topographic relief in a self-adaptive mode, damping force generated by the elastic pieces and the relative movement cooperatively provides a buffer effect, posture changes of an aircraft body are effectively restrained, and landing stability and safety are improved.