90 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.

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.

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.

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.

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.

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 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.

The application discloses a fixed-wing flight device landing control method and device, the method comprises the following steps: collecting the geographical information of the runway to construct a data calibration difference table; obtaining the first height difference of the flight device relative to the take-off point determined by each height sensor according to the take-off data and the data calibration difference table; obtaining the second height difference of the flight device relative to the estimated landing point determined by each height sensor based on the height difference between the estimated landing point and the take-off point; selecting the second height difference of a single height sensor as a height source for landing control according to the landing field difference until the flight device lands. The application solves the problem that the existing landing technology is difficult to realize safe and accurate landing control under complex runway conditions, reduces the hardware cost, avoids environmental interference and measurement error caused by additional equipment, and is an economical, efficient and safe solution.

A flying apparatus includes a main body assembly, an arm extending away from the main body assembly in a planar view, and a rotor attached to the arm. The arm is rotatable downward from a predetermined position in which the arm is to be when the flying apparatus flies.

The application provides a non-intrusive experimental evaluation system and method for pilot human-machine trust behavior, and relates to the technical field of human-computer interaction, which comprises the following steps: collecting a plurality of original data points including eye movement trajectory data points, operation instruction data points and flight instrument parameter data points of a pilot to form an objective behavior data set; receiving a plurality of subjective evaluation data points of the pilot based on the objective behavior data set to form a subjective evaluation data set; receiving a plurality of expert evaluation data points of a flight expert according to the subjective evaluation data set and the objective behavior data set to form an expert evaluation data set; and synchronously matching each data point in the objective behavior data set, the subjective evaluation data set and the expert evaluation data set according to a flight task time node to generate a multi-dimensional behavior mapping data set with time corresponding relationship. The application can realize accurate identification, dynamic evaluation and quantitative analysis of pilot human-machine trust behavior.

The utility model provides a flight device and its fire fighting truck, the flight device comprises a mounting structure and an aircraft, the mounting structure comprises a mounting cover, a bottom box and a driving structure, a mounting cavity is formed between the mounting cover and the bottom box, the aircraft and the driving structure are mounted in the mounting cavity, and the driving structure is mounted in the mounting cavity. And the driving structure is connected with the mounting cover so as to drive the mounting cover to move relative to the bottom box, and the mounting cavity is opened or closed through movement of the mounting cover on the bottom box. In the fire rescue process, the aircraft flies out of the mounting cavity, the rescue environment can be surveyed through the aircraft, the road water source condition can be surveyed, a fire point can be found, then the optimal route is analyzed, combat strength deployment and fire scene omnibearing real-time monitoring are carried out, convenience is provided for rescue, and rescue implementation is facilitated.

To prevent a flying device from colliding with an object that needs to be avoided. [Solution] The flying device 2 has a detection unit 272 that detects an avoidance object, which is an object that the flying device 2 is trying to avoid, that is located within an area including the ground surface below the flight route along which the flying device 2 flies, based on an image captured of the area, a calculation unit 273 that calculates a movable area, which is an area into which the avoidance object may move within a specified time, an identification unit 274 that identifies the range in which the flying device 2 will fall to the ground surface within a specified time based on the flight state of the flying device 2, and a change unit 275 that, if the identified fall area includes the movable area of ​​the avoidance object, changes the flight route to a changed route that does not include the movable area identified based on the flight state corresponding to the changed route.

This invention provides a power system voiceprint inspection robot, comprising a flight device and a detection device. The flight device includes a body and multiple flight components. Each flight component includes a wing, propellers, and a first drive block for driving the propellers to rotate. One end of the wing is connected to the body, the first drive block is located at the other end of the wing, and the propellers are located at the output end of the first drive block. The detection device includes a voiceprint detection module, a lifting structure, and a detection component mounted on the lifting structure. The lifting structure drives the detection component to move up and down, and the detection component detects the distance between the flight device and obstacles. The lifting structure is located on the body, and the voiceprint detection module is located at the top of the lifting structure. This invention solves the problem of low efficiency in traditional power system detection methods and has the advantage of a large detection range.

The present invention provides an agricultural aircraft that can maintain stable flight even when the payload weight drops sharply. [Solution] The agricultural flying device 5 comprises an aircraft body 50a, a rotor blade 50c provided on the aircraft body 50a, and a holding device 51 provided on the aircraft body 50a that can be changed between a holding state for holding materials S and a release state for releasing materials S. The rotation speed of the rotor blade 50c decreases when the holding device 51 transitions from the holding state to the release state.

The application provides a self-stabilizing flying device, and relates to the field of aviation technology, which comprises a frame body and a support column, a rotor assembly and a counterweight assembly are arranged on the support column; the rotor assembly is connected above the support column, the counterweight assembly is connected below the support column, and the frame body is movably connected between the rotor assembly and the counterweight assembly through a movable assembly; the movable assembly can make the rotor assembly tilt forward and backward and deflect left and right relative to the frame body to control the flight attitude of the self-stabilizing flying device. The application has the advantages of simple structure, few components, low failure rate, convenient assembly, simple operation, automatic and manual driving, and the like. Meanwhile, the counterweight assembly can right the rotor assembly, the rotating plane of the rotor assembly can be restored to a state of being substantially parallel to the ground, the rotor assembly is not prone to side turning or flying disorder, and the safety is high.

The utility model belongs to the technical field of intelligent network connection automobiles, and relates to an automobile tripod capable of automatically flying and placing and a system thereof, comprising a flying device, a tripod, a power supply, a control device and a visual perception module, the power supply and the control device are arranged in the flight device, the tripod is arranged at the top of the flight device, and the visual perception module is arranged outside the flight device; the power source supplies power to the automobile tripod capable of being automatically placed in a flying mode. The control device is electrically connected with the flying device, the tripod and the visual perception module. The tripod is provided with a lifting device and is connected with the flying device through the lifting device; according to the invention, a driver and passengers do not need to manually place the tripod when getting off, so that the risk that the driver and passengers are collided when getting off and placing the tripod in an expressway environment is avoided, and the life safety of the driver and passengers is guaranteed.

Provided is a flying apparatus and a method for controlling the same which are capable of preventing the flying apparatus from flying in a state where the weight of a transported body is excessive. A flying apparatus 10 comprises: an airframe base unit 16; a rotor 11; a motor 12; a calculation control unit 15; and a weight detecting unit 17. The rotor 11 rotates to generate thrust for causing the airframe base unit 16 to float. The motor 12 rotationally drives the rotor 11. The weight detecting unit 17 detects a weight value of a transported body 18. If the weight value detected by the weight detecting unit 17 exceeds a threshold weight value, the calculation control unit 15 does not permit takeoff.

The present invention is related to a remotely-controlled flying device intended to approach and contact a high-voltage overhead power line for operation thereon, said flying device comprising : - a mechanical structure (1) bearing a plurality of propellers (8) and an aircraft body (4) containing at least a power hub, a flight controller and radio communication means, and - an electrical shield (2, 7) encapsulating said mechanical structure (1), wherein the remotely-controlled flying device also comprises a surge protector or the like (3) designed to locally capture and guide toward the electrical shield (2) possible electric discharges in the phase of power line approaching and / or contacting and to render the electrical shield (2) equipotential with the power line.

A flight device according to the present invention comprises a body section 1 that has a plurality of vertices 4, 5 positioned on the same circumscribed circle or circumscribed ellipse in a plan view and a plurality of side parts 2, 3 connected across adjacent vertices 4, 5, and the body section 1 being formed in a polygonal shape in plan view. The flight device also comprises arm parts 11, 21 that have frames 12, 13, 22, 23 extended outward from the vertices 4, 5 on one side and the vertices 4, 5 on the other side of the side parts 2, 3. A rotor attached to the arm parts 11, 21 is also provided.

Provided is a flying apparatus capable of effectively cooling an engine during flight.　A flying apparatus 10 comprises an airframe 19, a rotor 14, an engine 20, a cooling portion 11, and an airflow guide portion 15. The cooling portion 11 comprises an engine-side heat exchanging portion 111, an outer-side heat exchanging portion 112, and a medium transporting portion 113. The engine-side heat exchanging portion 111 is configured to exchange heat with the engine 20. The outer-side heat exchanging portion 112 is configured to exchange heat with the outside. The medium transporting portion 113 is configured to transport a heat transport medium 114 between the engine-side heat exchanging portion 111 and the outer-side heat exchanging portion 112. The wind guide portion 15 is disposed between the rotor 14 and the outer-side heat exchanging portion 112.

The application relates to the technical field of G01C11 / 00, in particular to a surveying information data collection method and a storage medium. The surveying information data collection method comprises the following steps: S1. using a flight device to carry a position module and a camera module, acquiring ground surveying image information by shooting through the camera module; and S2. editing and storing region range position information through a setting module, transmitting the region range position information to the flight device through an information transmission module, and starting the camera module to shoot images in the region range. Through the surveying information data collection method and system, the position data information of specific surveying can be fed back to the flight device, and surveying images of specific position regions can be acquired.

The utility model discloses a bionic butterfly flight device, which belongs to the technical field of aircrafts and comprises a transmission main shaft, swing wings are respectively arranged on two sides of the transmission main shaft, and a first swing mechanism and a second swing mechanism are respectively arranged at two ends of the transmission main shaft. The two ends of the first swing mechanism in the second direction are connected with one ends of the two swing wings, and the first swing mechanism can drive the two swing wings to swing in the second direction and the third direction; the two ends of the second swing mechanism in the second direction are connected with the other ends of the two swing wings correspondingly, and the second swing mechanism can drive the two swing wings to swing in the plane where the first direction and the second direction are located. According to the bionic butterfly flight device, the center of the device is adjusted through the two swing mechanisms, gliding of the flight device is facilitated, kinetic energy output of the flight device is reduced, direction changing of the direction device is achieved through the second swing mechanism, the overall structure is simple, operation is convenient, and flight and steering operation of the flight device in the air are achieved.

This application provides a flight device, comprising: a fuselage; and an energy storage component disposed outside the fuselage, the energy storage component including a connecting mechanism and a battery, the connecting mechanism being mounted on the fuselage; the connecting mechanism having a locked state and an unlocked state, the connecting mechanism being configured to switch between the locked state and the unlocked state, in the locked state the connecting mechanism being connected to the battery, and in the unlocked state the connecting mechanism being disengaged from the battery, thereby detaching the battery from the fuselage. With this configuration, in emergency situations such as battery spontaneous combustion, the connecting mechanism can switch to the unlocked state. Since both the connecting mechanism and the battery are located outside the fuselage, the interior of the fuselage can be effectively isolated from fire sources, while the battery can be quickly jettisoned.