60 results about "Flight instruments" patented technology

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.

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.

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.

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.

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.

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.

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.

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.

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.

The present invention provides an aircraft capable of effectively cooling the components housed within the cover. [Solution] The flying device 10 comprises an airframe 11 and a cover 12 that covers the airframe 11. The cover 12 has a front cover portion 121 and a rear cover portion 122. By opening the front cover portion 121, a front opening 131 is formed, and by opening the rear cover portion 122, a rear opening 132 is formed. According to the present invention, when the flying device 10 is in flight, the airflow introduced from the front opening 131 and discharged from the rear opening 132 circulates well inside the cover 12. Therefore, the engine 25 and electrical components built into the cover 12 can be cooled well.

The invention discloses a water-land-air triphibian multi-rotor flight device which comprises an upper support, an air bag, a control panel, a control panel support, an antenna, a camera and a lower support. The upper surface of the airbag is fixedly provided with an upper bracket; the lower surface of the airbag is fixedly provided with a lower bracket; the control panel support is installed on the upper surface of the upper support, the control panel is installed in the control panel support, the antenna is installed on the side portion of the control panel support, and the camera is installed at the front end of the control panel support. The water-land-air triphibian seamless switching device is compact in structure and stable in power, water-land-air triphibian seamless switching can be achieved, the problems that existing equipment is poor in multi-scene adaptability, single in function and insufficient in cross-medium operation capacity are solved, and the requirements for integrated operation equipment in the fields of emergency rescue, environment monitoring, geographic exploration, low-altitude logistics and the like are met.

The present disclosure provides a method of monitoring for an unstable approach of an aircraft during flight in one aspect, the method including: determining, using values of a ground speed and a height of the aircraft derived from measurements acquired during the flight, a specific energy of the aircraft during an approach phase of the flight. The method further includes determining a reference specific energy of the aircraft, defining an energy range relative to the reference specific energy, and visually displaying, using a first flight instrument of the aircraft, an indicator of the specific energy relative to the energy range.

The flying device will avoid colliding with objects that it needs to avoid. [Solution] The flying device 2 includes a detection unit 272 that detects an object to be avoided, which is an object that the flying device 2 is intended to avoid, located within an area captured by an image of the area including the ground surface below the flight path it is flying; a calculation unit 273 that calculates a movable area, which is an area in which the object to be avoided may move within a predetermined time; a specification unit 274 that identifies the area to which the flying device 2 may fall onto the ground within a predetermined time based on the flight state of the flying device 2; and a modification unit 275 that, if the movable area of ​​the object to be avoided is included in the identified area to be avoided, changes the flight path to a modified route, which is a modified route in which the movable area is not included in the identified area to be avoided, based on the flight state corresponding to the modified route.

The application provides a method and device for inspection control, an electronic device and a computer readable storage medium. The method comprises: acquiring a first image collected by a flight device at a specified image collection position; identifying whether an inspection object exists in the first image through a preset yolov4-tiny model, wherein the preset yolov4-tiny model uses a DW convolution, a 3*3 convolution kernel and a structured pruning method; if the first image has the inspection object, determining image collection control information of the flight device on the inspection object based on the specified image collection position and a position of the inspection object; and sending an image collection instruction to the flight device based on the image collection control information, so that the flight device collects a second image with the inspection object based on the image collection instruction. The technical solution reduces the labor cost and environmental factor interference in the inspection object identification process, improves the identification efficiency of the inspection object, and helps the smooth progress of power inspection.

The invention provides a flight device and a control method thereof. The apparatus obtains a plurality of magnetic field data measured over a time interval. The apparatus calculates a plurality of orientation orientations based on the plurality of magnetic field data. The apparatus calculates a plurality of displacement orientations based on a plurality of displacement records corresponding to the time interval. The device compares the plurality of orientations and orientations with the plurality of displacement orientations, and determines whether the flight device is subjected to a magnetic interference in the time interval. In response to determining that the flying device is subject to the magnetic disturbance, the device performs an avoidance operation. According to the flight device and the control method thereof, whether the flight device is subjected to magnetic interference or not is judged by comparing different data, and the flight device is prevented from being out of control due to environmental influence.

The utility model discloses a flight device carrying a flame generator, which comprises an aircraft, two hitching arms, a storage battery, a flame generator and a driving component, the bottom end of the aircraft is provided with two connecting frames, and the two connecting frames are oppositely arranged and extend towards the lower part of the aircraft; the two hanging arms are connected to the lower ends of the two connecting frames in a one-to-one opposite mode, first fixing plates are arranged at the lower ends of the two hanging arms so that an installation gap can be defined between the two first fixing plates, the storage battery is arranged in the installation gap, and the two sides of the storage battery are connected with the two first fixing plates correspondingly. The lower ends of the two first fixing plates are both connected with second fixing plates, a rotating shaft is arranged between the two second fixing plates in a penetrating mode, the flame generator is arranged on the rotating shaft, and the driving assembly is arranged between the two second fixing plates and used for driving the rotating shaft to rotate so as to adjust the flame direction of the flame generator. According to the deicing device, deicing operation can be carried out by carrying the flame generator, the operation efficiency is improved, and the use cost is reduced.

Functional module for an autonomous flying device, autonomous flying device, autonomous flight system for a vehicle and vehicle.

The present invention extends an operating time of a flight device and enables appropriately takeoff and landing of the flight device.　A work machine (2) comprises: a vehicle body (11); a travel device (14) that supports the vehicle body (11) so that the vehicle body (11) can travel; a changing mechanism (24) that can change an attitude of the vehicle body (11); a flight device (31) that is connected to the vehicle body (11) via a cable (82), flies using power supplied via the cable (82), and performs work; a landing station (51) that is provided on the upper side of the vehicle body (11) and on which the flight device (31) can land; and an auxiliary device (61) that is provided on the vehicle body (11) and assists work by the flight device (31).

To provide a flight device that can effectively cool the engine during flight. [Solution] The flying device 10 comprises an airframe 19, a rotor 14, an engine 20, a cooling unit 11, and an air guide unit 15. The cooling unit 11 has an engine-side heat exchange unit 111, an external-side heat exchange unit 112, and a medium transport unit 113. The engine-side heat exchange unit 111 is configured to exchange heat with the engine 20. The external-side heat exchange unit 112 is configured to exchange heat with the outside. The medium transport unit 113 is configured to transport a heat transport medium 114 between the engine-side heat exchange unit 111 and the external-side heat exchange unit 112. The air guide unit 15 is disposed between the rotor 14 and the external-side heat exchange unit 112.

The application provides an electric driving system and a flight device, and relates to the technical field of electric driving. The electric driving system comprises an inner stator assembly and an outer rotor assembly; the inner stator assembly comprises an electric control mechanism and a stator shaft mechanism, the outer rotor assembly comprises a rotor mechanism, the electric control mechanism is arranged at one end of the stator shaft mechanism, the stator shaft mechanism is matched and installed with the electric control mechanism, and the rotor mechanism is sleeved on the outer side of the stator shaft mechanism; the electric control mechanism comprises a plurality of inversion units, and the plurality of inversion units are arranged in parallel in sectors at the end position of the stator shaft mechanism. The electric driving system can realize the technical effects of compact structure, high power density and high system reliability.