36results about How to "Avoid flight accidents" patented technology

The embodiment of the present application provides a method and a device for generating an unmanned aerial vehicle route. The method comprises the following steps of: generating an initial route of anoperation area of the unmanned aerial vehicle; dividing the operation area into a two-dimensional grid; obtaining two-dimensional coordinate information and point position height information of eachintersection in the two-dimensional grid; determining three-dimensional coordinate information of the plurality of target waypoints corresponding to the plurality of waypoints on the initial route according to the two-dimensional coordinate information and the point position height information of each intersection in the two-dimensional grid; and generating a target route of the operation area according to the three-dimensional coordinate information of the plurality of target waypoints. According to the method and the device for generating an unmanned aerial vehicle route, in this embodiment,the elevation information of each waypoint in the operation area can be obtained in real time and accurately by obtaining the spatial characteristics of the ground terrain, and a target route parallel to the undulating terrain can be generated. When the unmanned aerial vehicle flies according to the target route, the flight altitude of the unmanned aerial vehicle can be quickly judged and adjusted to avoid flight accidents such as crash.

A method and system for predicting and alarming the failure of aircraft are disclosed. Said method includes arranging different sensors at various positions where it is possible that the failure occurs, continuously acquiring the data from said sensors, storing the data in hard disk, analyzing and procesisng the data, comparing the result with standard data model, starting alarm system if they are not matched, and transmitting the result to ground command center. Said system is composed of sensors, data acquisition unit, computer, alarm system, and the data receiver and monitor in ground command center.

The invention discloses a navigation method, device and system for a general aviation aircraft. The navigation method for the general aviation aircraft comprises steps as follows: location information of the general aviation aircraft is acquired; three-dimensional realistic scene data corresponding to the position information are read; a three-dimensional landscape low-altitude navigation data package is acquired and comprises basic data, low-altitude barrier data, threatening area data and safety guarantee area data; and a three-dimensional navigation realistic picture is displayed according to the three-dimensional realistic scene data and the three-dimensional landscape low-altitude navigation data package. By means of the method, the device and the system, flying safety of the general aviation aircraft in low altitude and super-low altitude can be effectively improved.

The invention discloses a composite wing unmanned plane automatic pilot and a control method employed by the composite wing unmanned plane automatic pilot. Through the automatic pilot and the control guidance algorithm, a multi-shaft and fixed wing coordination control problem is solved, and full-state full-autonomous course flight of a composite wing unmanned plane is realized.

The invention provides a device for monitoring whether a pilot has a flight illusion or not by combining a functional near infrared reflectance spectroscopic imaging device with a gyroscope, judging the type of the flight illusion and enabling a vestibular electrical stimulation device to send a corresponding stimulation sequence to resist the flight illusion in case of a certain flight illusion. The device comprises the functional near infrared reflectance spectroscopic imaging device for acquiring a blood oxygen concentration signal of the cerebral cortex of the pilot in a flying process, identifying the feature of the blood oxygen signal, and judging whether the flight illusion occurs, the gyroscope for detecting the motion condition of the head of the pilot, the vestibular electrical stimulation device for applying vestibular electrical stimulation and changing an input signal of the semicircular canal of the vestibular organ of a human body to resist the flight illusion, and a control computer for controlling a stimulation mode, a stimulation current mode, stimulation current intensity and stimulation time of the vestibular electrical stimulation device, and displaying relevant parameters in real time. The device provided by the invention can monitor the space cognitive state of a person in the flying process, and can apply the vestibular electrical stimulation in time in case of the flight illusion, so as to resist space disorientation.

The invention relates to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle homeward voyage monitoring method based on an intelligent lamp post anda control center. When a flight electric quantity change curve is analyzed and the flight attitude is adjusted, the residual electric quantity change data and the flight environment monitoring data can be considered at the same time, time delay or adjustment deviation of flight attitude adjustment caused by only considering one of the residual electric quantity change data and the flight environment monitoring data is avoided. It can be understood that the residual electric quantity change data is on the side of the to-be-monitored unmanned aerial vehicle, and the flight environment monitoring data is on the side of the target intelligent lamp post. Real-time flight attitude adjustment can be performed based on the residual electric quantity change data and the flight environment monitoring data, so that real-time and stable monitoring of homeward voyage monitoring of the unmanned aerial vehicle can be realized in combination with the environmental factors and the electric quantity loss, safe homeward voyage of the unmanned aerial vehicle can be ensured and flight accidents can be avoided.

The invention relates to the field of flight control systems, in particular to an auxiliary monitoring device in a flight control system. The auxiliary monitoring device comprises a core processing module; the core processing module comprises a database unit, a processing unit and a sending unit; rule data violating flight regulations and unsafe flight control data are stored in the database unit,the processing unit acquires a real-time flight airway and attitude information of an aircraft, the real-time flight airway and attitude information of the aircraft and the rule data violating the flight regulations and the unsafe flight control data are compared and analyzed, once the real-time flight airway and attitude information of the aircraft and the rule data violating the flight regulations and the unsafe flight control data are anastomotic, anastomotic information is transmitted to the sending unit; and the sending unit transmits the anastomotic information to a ground blank pipe. The auxiliary monitoring device in the flight control system has the advantages that through the effective combined design of flight status information of the aircraft and active perception informationof the system, the flight is monitored in real time, it is achieved that effective supervision and alarm of driving are provided for flight crews, and the occurrence of flight accidents caused by man-made operation is avoided.

The present invention provides a method for detection of a location device of an unmanned aerial vehicle (1000, A), and an unmanned aerial vehicle (1000, A). The flight state information of a plurality of aircrafts (B, C, D) deteced by an aircraft detection device and position information output by the location device are employed to determine whether the location device on the unmanned aerial vehicle (1000, A) is disturbed or cracked or not, the work state of the location device is detected to avoid flight accidents and ensure the flight safety of the unmanned aerial vehicle (1000, A) and theaircrafts around (B, C, D). The method comprises the steps of: obtaining the position information (S101, S201, S501) output by the location device; obtaining the flight state information (S102, S202, S502) of a plurality of aircrafts (B, C, D) in the unmanned aerial vehicle (1000, A); and detecting the work state (S103, S603) of the loation device according to the position information anda the flight state inforamtion.

The invention discloses a boundary protection method for an unmanned aerial vehicle with a large lift-to-drag ratio. A boundary protection item is added to an attitude driving control loop, and the boundary protection item is the product of an error value of a protected signal and a gain K. The present invention adds boundary protection control on the basis of not changing the original control law structure. When each signal exceeds the boundary, it can quickly adjust the flight attitude to ensure that each signal re-enters the protected range, thereby protecting the UAV. Flight safety.

A flight control method, a flight control device, a control terminal, a flight system, a computer processor, and a memory. The method comprises: displaying prompt information in a photographed image returned by an air vehicle (101, 202, 302, 402, 502); obtaining position information clicked by a user in the image (102, 203, 303, 403, 503); and controlling the flight direction of the air vehicle according to the position information clicked by the user and the prompt information (103, 204, 304, 404, 504). By means of the method, a user can intuitively control the flight direction of an air vehicle according to a specific position of the air vehicle, thereby providing convenience to the user, effectively avoiding occurrence of a flight accident, and improving the safety of the air vehicle.

The invention provides a power frequency electromagnetic field probe and a power line patrol unmanned aerial vehicle navigation device and method, the probe is arranged on an unmanned aerial vehicle for patrol of an alternating current power line, the probe is cuboid, a magnetic field sensor is arranged on a first side surface of the probe, and electric field sensors are arranged on four adjacentside surfaces of the first side surface; a processing module is arranged in the probe; the magnetic field sensor measures the power frequency magnetic field intensity value of the position where the first side face is located in the unmanned aerial vehicle line patrol rotating process; the electric field sensors measure the power frequency electric field intensity values of the positions of the four adjacent side surfaces of the first side surface in the line patrol flight process of the unmanned aerial vehicle; and the processing module sends the power-frequency magnetic field intensity valueand the power-frequency electric field intensity value to a control module of the unmanned aerial vehicle, so that the control module determines the trend of the alternating-current power line and the position of the unmanned aerial vehicle relative to the alternating-current power line. Under the condition that satellite navigation signals are lost, power line patrol navigation of the unmanned aerial vehicle is achieved.

The invention provides a novel monocoque bay oil tank of an unmanned aerial vehicle. The novel monocoque bay oil tank comprises a first tank body and a second tank body; the volume of the first tank body is larger than the volume of the second tank body, a pressurization opening and an oiling opening are formed in the upper part of the first tank body, and an oil conveying opening is formed in theright side of the second tank body; a sealing plate is arranged between the first tank body and the second tank body, an oil guiding pipe is arranged on the position, below the sealing plate, in thesecond tank body, and the second tank body communicates with the first tank body through the oil guiding pipe; and a one-way device is arranged at the oil conveying end of the oil guiding pipe. Fuel oil is consumed in sequence, thus control over the fuel oil mass center is convenient, and the flight property of the unmanned aerial vehicle is improved; the oil guiding pipe is arranged in the secondtank body, thus the fuel oil in the first tank body flows into the second tank body conveniently, meanwhile the one-way device is arranged at the oil conveying end of the oil guiding pipe, and thus backflow of the fuel oil is avoided; and a transverse plate is arranged in the second tank body, the situation that the fuel oil at the oil conveying opening is disrupted due to diving or accelerating,and consequently a flight accident is caused is avoided, a one-way device is also arranged in a third tank body, redundant design is adopted, and thus reliability of an unmanned aerial vehicle oil tank system is improved.

The invention discloses a flight matching method for a piston engine and an unmanned helicopter. The method comprises the following operation steps: judging the current flight state of the unmanned helicopter; if the current unmanned helicopter is in the hovering state, the corresponding relation between the accelerator OIL and the total distance is finally obtained through the relation between the required power NXU and the total distance under different flight weights T; If the current unmanned helicopter is in the forward flight state, the corresponding relation between the accelerator OILand the total distance in the forward flight state is finally obtained through the relation between the required power NXU and the total distance at different forward flight speeds V0. According to the flight control method, force balance and power balance are guaranteed, and therefore flight accidents caused by improper coordination of the piston type unmanned helicopter and the engine are avoided.

The embodiment of the invention provides a combined test method and device for a motor and a propeller of an unmanned aerial vehicle, a computer readable medium and electronic equipment. The unmanned aerial vehicle motor and propeller combined test method comprises the following steps: controlling an unmanned aerial vehicle motor to rotate at a set motor rotating speed, driving propellers to rotate, and acquiring the rotating speed corresponding to each propeller, the flight speed of the unmanned aerial vehicle in the same flight environment and the power consumption of a battery under the condition that the unmanned aerial vehicle runs at the set motor rotating speed; based on the rotation speed, the flight speed and the power consumption, flight performance parameters of the motor corresponding to the propellers are determined; according to the method, the target propeller most matched with the motor is selected from the propellers based on the flight performance parameters, and the target propeller matched with the motor and the unmanned aerial vehicle is selected from the propellers, so that flight accidents can be avoided, and the performance of the motor can be exerted to the maximum extent; and the flight efficiency and safety of the unmanned aerial vehicle in the flight process are improved.

The invention relates to a minimum speed protection control system for unmanned aerial vehicles, comprising: a control computer as a control center and an airspeed sensor electrically connected to it, the computer is equipped with two minimum speed fault handling modules that are started by timing interruption, and the two The modules include: a minimum speed over-boundary control module and a minimum speed fault handling control module, wherein the minimum speed over-boundary control module is used to monitor the aircraft speed obtained by the airspeed sensor system in real time, and control the speed of the aircraft within the allowable range; the minimum speed The fault handling control module is triggered by a clock timing interrupt, and its minimum fault handler controls the parachute recovery of the aircraft. According to the current flight speed obtained by the airspeed sensor, when the speed is lower than the minimum speed limit, the invention can adjust the throttle opening of the engine to resume normal flight, and can control the parachute recovery of the aircraft when the minimum speed cannot be controlled, which solves the problem Some UAVs do not have the minimum flight speed control and are prone to stall and cause flight accidents.

The present invention provides a power frequency electromagnetic field probe, a navigation device and method for a power line inspection UAV. The probe is set on the UAV used for line inspection of AC power lines. There are magnetic field sensors, and the four adjacent sides of the first side are equipped with electric field sensors; the inside of the probe is equipped with a processing module; the magnetic field sensor measures the power frequency magnetic field strength at the position of the first side during the rotation of the UAV. value; the electric field sensor measures the power frequency electric field strength value at the position of the four adjacent sides of the first side during the UAV line inspection flight; the processing module sends the power frequency magnetic field strength value and the power frequency electric field strength value to the wireless The man-machine control module enables the control module to determine the direction of the AC power line and the position of the UAV relative to the AC power line. In the absence of satellite navigation signals, the power line patrol navigation of UAVs is realized.

The invention discloses a boundary protection method for an unmanned aerial vehicle with a large lift-drag ratio, and the method comprises the step: adding a boundary protection item which is the product of an error value of a protected signal and a gain K into an attitude driving control loop; according to the method, boundary protection control is added on the basis of not changing the originalcontrol law structure, and when each signal exceeds the boundary, each signal can be ensured to enter the protected range again by quickly adjusting the flight attitude, so that the flight safety of the unmanned aerial vehicle is protected.

A method for controlling an unmanned aerial vehicle (100), a flight controller (10), and an unmanned aerial vehicle (100). The method for controlling the unmanned aerial vehicle (100) comprises the following steps: acquiring the current flight direction of the unmanned aerial vehicle (100) in real time (S12); acquiring the current detection direction of a detection sensor (20) in real time (S13);calculating an angle difference between the current flight direction and the current detection direction (S14); and controlling and adjusting the current detection direction according to the angle difference such that the adjusted detection direction of the detection sensor (20) is consistent with the current flight direction (S15). The detection sensor (20) can rotate in various directions, and the adjusted detection direction of the detection sensor (20) is always consistent with the current flight direction; and the detection range of the detection sensor (20) always covers the range of a route in the current flight direction of the unmanned aerial vehicle (100), so as to effectively detect an obstacle in the flight direction of the unmanned aerial vehicle (100), thereby avoiding a flight accident caused by collision with the obstacle.

Embodiments of the present invention provide a vibration testing method, device and aircraft, which relate to the technical field of vibration testing. The vibration test method includes: obtaining an adjustment signal; adjusting the control signal of the motor according to the adjustment signal, so that the rotational speed of the motor changes, thereby making the aircraft in a target vibration state; Vibration signals of ; Among them, different structural parts represent structural parts with the same purpose and different composition and structure. The vibration testing method, device and aircraft provided by the invention can measure vibration signals generated by the aircraft during actual flight.

The invention relates to an auxiliary positioning method of a drone. The auxiliary positioning method is characterized by including 1), mounting an infrared sensing receiver on a drone; 2), connectingat least four infrared sensing locaters with the infrared sensing receiver mounted on the drone respectively; 3), before flying of the drone, inserting the four infrared sensing locaters into the ground in rectangular arrangement; 4), turning on a GPS device of the drone, and starting up the infrared sensing receiver; 5), on a drone operating system, entering the positions of the four infrared sensing locaters into a GPS system; 6), flying the drone for trail, and by the system, comparing differences between the position of the drone in a matrix, formed by the infrared sensing locaters, and aGPS located position to calibrate a flying coordinate system.

The invention relates to an unmanned aerial vehicle flight control system and an unmanned aerial vehicle, and is applied to the technical field of unmanned aerial vehicles. The unmanned aerial vehicleflight control system comprises a flight control mainboard and a plurality of flight control sub-boards, wherein each flight control sub-board is connected with the flight control mainboard and is used for receiving a starting signal sent by the flight control mainboard, activating a flight control mode after receiving the starting signal, and sending a control signal to the flight control mainboard; and the flight control mainboard is used for generating the starting signals through an enabling module on the flight control mainboard, sending the starting signals to the flight control sub-boards, receiving the control signals sent by the flight control sub-boards, judging whether the control signals are correct or not, and selecting the flight control sub-boards corresponding to the correct control signals to control the flight of the unmanned aerial vehicle.

The invention provides a synchronous rotating mechanism for left and right wings of a transport helicopter, through which the rotating angles of two wings are synchronous, thereby ensuring the flight stability of the transport helicopter and effectively avoiding flight accidents. The synchronous rotating mechanism is characterized by comprising a worm gear and a worm, wherein the worm is connected with a power drive device, the worm gear is respectively connected with drive shafts at the two ends of the worm gear, the drive shafts are respectively connected with a driving gear, the driving gears are respectively connected with a driven gear, and the driven gears are respectively connected with a wing propeller assembly.

The invention provides a novel monocoque bay oil tank of an unmanned aerial vehicle. The novel monocoque bay oil tank comprises a first tank body and a second tank body; the volume of the first tank body is larger than the volume of the second tank body, a pressurization opening and an oiling opening are formed in the upper part of the first tank body, and an oil conveying opening is formed in theright side of the second tank body; a sealing plate is arranged between the first tank body and the second tank body, an oil guiding pipe is arranged on the position, below the sealing plate, in thesecond tank body, and the second tank body communicates with the first tank body through the oil guiding pipe; and a one-way device is arranged at the oil conveying end of the oil guiding pipe. Fuel oil is consumed in sequence, thus control over the fuel oil mass center is convenient, and the flight property of the unmanned aerial vehicle is improved; the oil guiding pipe is arranged in the secondtank body, thus the fuel oil in the first tank body flows into the second tank body conveniently, meanwhile the one-way device is arranged at the oil conveying end of the oil guiding pipe, and thus backflow of the fuel oil is avoided; and a transverse plate is arranged in the second tank body, the situation that the fuel oil at the oil conveying opening is disrupted due to diving or accelerating,and consequently a flight accident is caused is avoided, a one-way device is also arranged in a third tank body, redundant design is adopted, and thus reliability of an unmanned aerial vehicle oil tank system is improved.