Unmanned aerial vehicle data acquisition system and safety detection method

Abstract

The unmanned aerial vehicle data acquisition system comprises a detection mechanism, a current sensor, a data acquisition and transmission circuit, a data receiving unit and a data analysis and display unit, a speed sensor of the unmanned aerial vehicle is a wind driven generator, a height sensor is a negative pressure transmitter, and the wind driven generator, the negative pressure transmitter, a data acquisition and transmission circuit and a current sensor are installed on the unmanned aerial vehicle. The data receiving unit and the data analysis and display unit are application software of a flight control end of the unmanned aerial vehicle; the detection mechanism comprises a box body, a sealing cover, a flow meter, a valve, a negative pressure pump, an air compressor, a detection circuit and a negative pressure sensor, and the detection mechanism is installed at the detection station. The invention discloses a safety detection method of an unmanned aerial vehicle data acquisition system. The method comprises two modes of flight data detection and static data detection. The flight control terminal can master voltage and current data in flight of the unmanned aerial vehicle, can detect the speed of the unmanned aerial vehicle body and the performance of the height sensor when the unmanned aerial vehicle is static, and can prompt maintenance when the performance is unstable.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle data collection and safety detection, and in particular to an unmanned aerial vehicle data collection system and a safety detection method. Background Art

[0002] A drone (unmanned aircraft) is an unmanned aircraft that is mainly controlled by radio remote control or its own program. It mainly includes military drones and civilian drones. Drones are small in size, low in cost, easy to use, and have low requirements for the environment (including take-off and landing environments), and are very popular among users.

[0003] When existing drones are performing flight missions, they can generally only transmit the drone's flight altitude, weather and other data wirelessly, and are unable to transmit the working voltage and total power consumption data of the drone's multiple lifting motors. In this way, when one or more corresponding motors are working abnormally, the input voltage is too high or too low (for example, the motor coil is open, resulting in a voltage increase, or the motor coil is short-circuited, resulting in a voltage decrease), and the total power consumption or current is too large or too low (for example, the corresponding electrical equipment of the drone body has an open circuit, resulting in a low working current, or the corresponding electrical equipment has a short circuit, resulting in an excessive working current), the remote flight control personnel cannot take immediate action (for example, to make the drone return or land on the spot), resulting in the problem of magnification of the drone's fault, which has an adverse impact on the safe use of the drone. In addition, existing drones do not have matching speed sensor and altitude sensor performance testing equipment, which means that in a static state (when the drone is not in use), staff cannot test the performance of the speed sensor and altitude sensor. In this way, when the speed sensor and altitude sensor are abnormal, incorrect data will be sent back during work, which will have an adverse effect on the remote control of the flight control personnel, and even control the drone flight based on erroneous data, which may cause a flight accident of the drone. Summary of the invention

[0004] In order to overcome the drawbacks of existing drones as described in the background technology due to structural limitations, the present invention provides a drone data acquisition system and safety detection method that, under the joint action of relevant mechanisms, can enable a remote flight control end to grasp the voltage and current data of the drone in flight in real time, and can detect the speed sensor and altitude sensor performance of the drone body in a static state, thereby providing strong technical support for the safe flight of the drone.

[0005] The technical solution adopted by the present invention to solve its technical problem is: A data acquisition system for an unmanned aerial vehicle comprises a detection mechanism, a current sensor, a data acquisition and transmission circuit, a data receiving unit, and a data analysis and display unit; the data acquisition and transmission circuit and the current sensor are installed on the unmanned aerial vehicle, the speed sensor of the unmanned aerial vehicle is a wind turbine, the height sensor is a negative pressure transmitter, the control input end of the current sensor and the positive pole of the battery on the unmanned aerial vehicle are electrically connected, the control output end of the current sensor and the negative pole of the battery are electrically connected to the total power input end of the unmanned aerial vehicle, the power input end of the data acquisition and transmission circuit, and the power input end of the negative pressure transmitter; the wind turbine is installed at the lower end of the frame of the unmanned aerial vehicle, and the negative pressure transmitter is installed at the upper end of the fuselage of the unmanned aerial vehicle; the signal output end of the wind turbine, the signal output end of the negative pressure transmitter, the signal output end of the current sensor, the positive power input end of multiple lifting motors of the unmanned aerial vehicle and the multi-channel signal input end of the data acquisition and transmission circuit are electrically connected respectively; the data receiving unit and the data analysis and display unit are application software installed in the control module of the flight control end of the unmanned aerial vehicle; the detection mechanism The structure includes a box body, a sealing cover, a flow meter, a valve, a negative pressure pump, an air compressor, a detection circuit, and a negative pressure sensor. The upper end of the box body is an open structure, and the sealing cover is movably installed on the box body; an air inlet pipe is installed at the front end of the box body, and an exhaust pipe is installed at the rear side of the box body. There are multiple valves, and there are at least two flow meters. One end of the first valve is connected to one end of the air inlet pipe, and the other end of the first valve is connected to the outlet end of the first flow meter. The air inlet end of the first flow meter is connected to the exhaust pipe of the air compressor, and one of the exhaust pipes at the rear end of the box body and the second One end of the valve is connected, another exhaust pipe at the rear end of the box is connected to one end of the third valve, the other end of the third valve is connected to the air inlet end of the second flow meter, a negative pressure tube is installed at the air outlet end of the second flow meter, the other end of the negative pressure tube is connected to the air inlet pipe of the negative pressure pump, and the air inlet pipe of the negative pressure sensor is installed at the side end of the negative pressure tube; the detection circuit has at least two paths, the detection circuit is installed in the component box, the component box is installed outside the front end of the box, and the wiring terminals of the height sensor and the speed sensor are electrically connected to the signal input ends of the two detection circuits.

[0006] Furthermore, the data acquisition and transmission circuit includes electrically connected resistors, a single-chip microcomputer module, and a GPRS module, one end of the seven resistors is respectively connected to the seven signal input ends of the single-chip microcomputer module, the signal output end of the single-chip microcomputer module is connected to the signal input end of the GPRS module, and the power input end of the single-chip microcomputer module is connected to the GPRS module.

[0007] Furthermore, the data receiving unit can receive the real-time working voltage data of multiple lifting motors of the drone and the current data of the total power input end of the drone sent by the data acquisition and sending circuit, and transmit the data to the data analysis and display unit after preliminary processing. The data analysis and display unit can display the various data in real time through the drone flight control display screen after analysis and processing.

[0008] Furthermore, the two detection circuits have the same structure and both include an electrically connected adjustable resistor and resistor, a transistor, a relay, and an alarm. One end of the adjustable resistor is connected to one end of the first resistor and one end of the second resistor, the other end of the second resistor is connected to the base of the transistor, the collector of the transistor is connected to the negative pole of the relay, the positive power input end of the relay and the control power input end are connected, the normally closed contact end of the relay is connected to the positive power input end of the alarm, and the negative power input end of the alarm is connected to the emitter of the transistor and the other end of the first resistor.

[0009] Furthermore, the valve is a manual stop valve or a solenoid valve.

[0010] A safety detection method for a drone data acquisition system includes two methods: flight data detection and static data detection. The flight data detection includes the following process: S1: The wires connected between the speed sensor, the altitude sensor and the data acquisition and transmission circuit of the drone are connected by plugging. When the drone is flying, the speed sensor and the altitude sensor collect the flight speed and altitude data of the drone in real time, and the data are transmitted to the signal input end of the single-chip microcomputer module. The working voltage of multiple lifting motors and the total current data of the drone during flight are transmitted to the signal input end of the single-chip microcomputer module. The single-chip microcomputer module converts the input multiple analog data into digital signals and transmits them to the GPRS module. The GPRS module transmits the multiple data remotely; S2: After receiving the multiple data, the data receiving unit of the flight control end of the drone body preliminarily processes the data, and then transmits the data to the data analysis and display unit. The data analysis and display unit can display the multiple data analysis and processing in real time through the display screen of the drone flight control end. The flight control end personnel can understand the altitude and speed data of the drone in real time, and can take corresponding measures when the drone flight data is abnormal, so as to reduce the failure of the drone. The probability of the failure to expand or even crash; static data detection includes the following processes, A1: the speed sensor, height sensor and the wires connected between the two detection circuits of the drone are connected by plugging, and the drone is placed in the box and the sealing cover is closed; A2: open the first valve and the second valve, and turn on the power switch of the air compressor. The air compressor inputs compressed air into the box, and the compressed air flows in from the front valve and flows out from the rear valve. During the compressed air inflow and outflow process, the wind turbine outputs a voltage signal to the signal input end of the first detection circuit during the flow process. When the voltage output by the wind turbine is too low at the corresponding air flow rate, the alarm alarm prompts that the speed voltage signal output by the wind turbine as a speed sensor is relatively low; A3: open the third valve, and turn on the power switch of the negative pressure pump. The negative pressure pump draws out the air in the box, and a negative pressure is generated in the box. The negative pressure sensor outputs a voltage signal to the signal input end of the second detection circuit. When the voltage output by the negative pressure sensor is too low at the corresponding negative pressure, the alarm alarm prompts that the height voltage signal output by the negative pressure sensor as a height sensor is relatively low.

[0011] Furthermore, in the process S1, the faster the drone flies and the higher the altitude it flies, the higher the signal voltage at the signal input terminal of the single-chip microcomputer module is, and vice versa, the lower the signal voltage at the signal input terminal of the single-chip microcomputer module is.

[0012] Furthermore, in the process A2, the opening and closing degree of the valve core of the first valve is adjusted in combination with the flow data displayed by the first flow meter, so that the flow rate of the air entering the box body is maintained at the set flow rate.

[0013] Furthermore, in the process A3, the opening and closing degree of the valve core of the third valve is adjusted in combination with the flow data displayed by the second flow meter so that the negative pressure in the box is at the set data, and the third valve is closed after the negative pressure in the box reaches the set value.

[0014] Furthermore, after the static data detection process, the sealing cover is opened, and then the drone is taken out to complete the static data detection process.

[0015] Compared with the prior art, the present invention has the following beneficial effects: when the present invention is used, the speed sensor and the altitude sensor can collect the speed and altitude data of the UAV flight, the voltage data of multiple lifting motors of the UAV, and the total current data of the UAV in real time. The various data are processed by the single-chip module and then transmitted wirelessly through the GPRS module. The remote flight control end can grasp the voltage and current data of the UAV in real time during flight, and can take timely measures (such as making the UAV return or land on the spot) when the UAV flies abnormally, reducing the probability of the UAV failure expanding or even crashing; when the UAV is in a static state, the staff can detect the speed sensor and altitude sensor performance of the UAV body through the detection mechanism, speed sensor detection circuit, altitude sensor detection circuit, etc. When the speed sensor and altitude sensor performance are unstable or damaged, they can be replaced in time, which provides strong technical support for the safe flight of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0017] Figure 1 It is a schematic diagram of the structure of the present invention.

[0018] Figure 2 , 3 It is a circuit diagram of the present invention. DETAILED DESCRIPTION

[0019] Figure 1 , 2As shown in , 3, a drone data acquisition system includes a detection mechanism, a current sensor A2, a data acquisition and transmission circuit 1, a data receiving unit, and a data analysis and display unit; the data acquisition and transmission circuit 1 and the current sensor A2 are installed in the component box of the drone 2, the speed sensor of the drone is a small DC wind turbine M, and the height sensor is a negative pressure transmitter A3; the wind turbine M is fixedly installed at the front lower end of the frame of the drone 2 and the blades of the generator M face the front side end, and the negative pressure transmitter A3 is fixedly installed outside the upper end of the fuselage of the drone 2. The data receiving unit and the data analysis and display unit are application software installed in the control module of the drone flight control end (the wireless remote control and data receiving device of the drone). The detection mechanism includes a box body 31, a sealing cover 32, flow meters A6 and A7, a valve 33, a negative pressure pump M5 (2.5KW), an air compressor M6 (2KW), a detection circuit 34, a power module A1, a negative pressure sensor A8 and power switches S1 and S2. The upper end of the box body 31 is an open structure. There are multiple wire seats around the inner upper end of the box body 31, and there are multiple fixing holes around the sealing cover 32. A plurality of bolts are respectively screwed into the wire holes of the multiple wire seats through the multiple openings of the sealing cover 32 to seal the sealing cover 32 on the box body 31; an air intake pipe 36 that is interconnected with the interior of the box body is welded to the middle part of the front end of the box body, and an exhaust pipe 37 that is interconnected with the interior of the box body is respectively welded to the left and right ends of the upper rear side of the box body. There are three valves and two flow meters. One end of the first valve 33 is connected to the lower end of the air intake pipe 36 through a thread, and the other end of the first valve 33 is connected to the first valve 33 through a thread. The air outlet of a flow meter A6 is connected via a pipe joint, the air inlet of the first flow meter A6 is connected to the exhaust pipe of the air tank of the air compressor M6 via a hose, one of the exhaust pipes 37 at the rear end of the box is connected to one end of the second valve 33 via a threaded connection, the other exhaust pipe 37 at the rear end of the box is connected to one end of the third valve 33 via a threaded connection, the other end of the third valve 33 is connected to the air inlet of the second flow meter A7 via a pipe joint, a negative pressure pipe 38 is threadedly installed at the air outlet of the second flow meter A7, the other end of the negative pressure pipe is connected to the air inlet pipe of the negative pressure pump M5 via a pipe, there is a threaded hole at the side end of the negative pressure pipe, and the air inlet pipe of the negative pressure sensor A8 is threadedly sealed and connected; the detection circuit 34 has two paths, the detection circuit 34, the power module A1 and the power switches S1 and S2 are installed in the component box 35, and the component box 35 is installed outside the left front end of the box 31.

[0020] Figure 1 , 2As shown in , 3, the data acquisition and transmission circuit includes resistors R1, R2, R3, R4, R5, R6, R7 and single-chip module A4, GPRS module A9 connected by circuit board wiring, one end of the seven resistors R1, R2, R3, R4, R5, R6, R7 is respectively connected to the seven signal input terminals 5, 9, 8, 7, 4, 3, 6 of the single-chip module A4, the signal output terminal of the single-chip module A4 is connected to the signal input terminal of the GPRS module A9, and the power input terminals 1 and 2 of the single-chip module A4 and the GPRS module A9 are respectively connected. The data receiving unit can receive the real-time voltage data of multiple lifting motors of the drone and the current data of the total power input terminal of the drone sent by the data acquisition and transmission circuit, and transmit the data to the data analysis and display unit after preliminary processing. The data analysis and display unit can display the various data in real time on the display screen of the drone flight control end after analyzing and processing. The first detection circuit includes an adjustable resistor RP1, resistors R8 and R9, a transistor Q1, a relay J1, and an alarm B connected via circuit board wiring. One end of the adjustable resistor RP1 is connected to one end of the first resistor R8 and one end of the second resistor R9. The other end of the second resistor R9 is connected to the base of the transistor Q1. The collector of the transistor Q1 is connected to the negative electrode of the relay J1. The positive power input end of the relay J1 is connected to the control power input end. The normally closed contact end of the relay J1 is connected to the positive power input end of the alarm B. The negative power input end of the alarm B is connected to the emitter of the transistor Q1 and the other end of the first resistor R8. The second detection circuit includes an adjustable resistor RP2 and resistors R10 and R11, a transistor Q2, a relay J2, and an alarm B1 connected by circuit board wiring. One end of the adjustable resistor RP2 is connected to one end of the first resistor R10 and one end of the second resistor R11. The other end of the second resistor R11 is connected to the base of the transistor Q2. The collector of the transistor Q2 is connected to the negative electrode of the relay J2. The positive power input end of the relay J2 is connected to the control power input end. The normally closed contact end of the relay J2 is connected to the positive power input end of the alarm B1. The negative power input end of the alarm B1 is connected to the emitter of the transistor Q2 and the other end of the first resistor R10. The valve 33 is a manual stop valve or a solenoid valve (a manual valve in this embodiment). The two-core plug and three-core plug wires connected to the signal input ends of the two detection circuits enter the box through the opening at the front end of the box, and the opening is sealed with sealant.

[0021] Figure 1 , 2As shown in Figure 3, the control input terminal 4 pin of the current sensor A2 (the negative pole 2 pin is connected to the negative pole of the battery G1) is connected to the positive pole of the battery G1 on the drone through a wire, and the control output terminal 5 pin of the current sensor and the negative pole of the battery G1 are connected to the 1st and 2nd pins of the total power input terminal A1 of the drone, the 1st and 2nd pins of the power input terminal of the data acquisition and transmission circuit, and the 1st and 2nd pins of the power input terminal of the negative pressure transmitter A3 are connected through wires. The positive pole of the signal output terminal of the wind turbine M (the negative pole is connected to the negative pole of the battery G1), the signal output terminal 3 pin of the negative pressure transmitter A3, the signal output terminal 3 pin of the current sensor A2, the positive power input terminal of the four lifting motors M1, M2, M3, and M4 of the drone, and the other ends of the seven signal input terminals of the data acquisition and transmission circuit resistors R6, R5, R1, R2, R3, R4, and R7 are connected through wires. The power input end of the power module A5, the power input ends of the two power switches S1 and S2 and the two poles of the AC 220V power supply are connected via wires, and the power output ends of the two power switches S1 and S2 and the other pole of the 220V AC power supply are connected via wires to the power input ends of the air compressor M6 and the negative pressure pump M5. The power output ends 3 and 4 of the power module A5 and the power input ends 1 and 2 of the two flow meters A6 and A7, the power input end relay J1 of the first detection circuit controls the power input end and the emitter of the transistor Q1, the power input end relay J2 of the second detection circuit controls the power input end and the emitter of the transistor Q2, and the power input ends 1 and 2 of the negative pressure sensor A8 are connected via wires. The two terminals of the speed sensor M are connected to a two-core socket, the three terminals of the negative pressure sensor A3 are connected to a three-core socket, the other end of the adjustable resistor RP1, the other end of the resistor R6 and the two power input ends of a two-core plug are connected via wires, the positive power input end of the relay J2, the emitter of the transistor Q2, the other end of the adjustable resistor RP2 and the two power input ends of a three-core plug are connected via wires. The other end of the resistor R6 and the negative pole of the battery G1 are connected to the two power input ends of another two-core plug via wires, and the positive pole of the battery G1, the negative pole of the battery G1, the other end of the resistor R5 and the two power input ends of another three-core plug are connected via wires.

[0022] Figure 1 , 2As shown in , 3, a safety detection method for a drone data acquisition system includes two methods: flight data detection and static data detection. The flight data detection includes the following process, (1): the two-core socket of the drone's speed sensor M and the three-core socket of the altitude sensor are respectively connected to the two-core power plug and the three-core plug of the data acquisition and transmission circuit; after the power output of the battery G1 on the drone enters the negative pressure transmitter A3, the current sensor A2, and the power input end of the data acquisition and transmission circuit, the above sensors and circuits are powered on and work; when the drone is flying, due to the action of the oncoming wind flow, the wind turbine M will send a dynamically changing voltage signal, which will be limited and reduced by the resistor R6 and enter the 3rd pin of the single-chip module A4 (the faster the flight speed, the higher the voltage signal, and vice versa). The negative pressure transmitter A3 will collect the altitude data of the drone's flight airspace in real time. The higher the altitude, the lower the air pressure. The dynamically changing voltage signal output by the 3rd pin of the negative pressure transmitter A3 will enter the single-chip module A through the resistor R5. The higher the signal voltage of the 4th foot of 4, the lower the signal voltage is; when the drone body is flying, its control system is controlled by the remote flight control end. At the same time, the positive power input end power supply at the corresponding motor will enter the 9th, 8th, 7th, and 6th feet of the single-chip module A4 through the resistor R2 or R3, R4, and R7 for voltage reduction and current limiting. When the current sensor A2 is working, the greater the current consumed at the total power input end of the drone, the higher the voltage signal output from its 3rd foot will enter the 5th foot of the single-chip module A4 through the resistor R1 for voltage reduction and current limiting, and vice versa; the above-mentioned multiple flight speed data, flight altitude data, lifting motor working voltage data, and total current data are transmitted to the signal input end of the single-chip module A4, and the single-chip module A4 converts the input multiple analog data into digital signals and transmits them to the GPRS module A9, and the GPRS module A9 transmits the multiple data remotely. (2) The data receiving unit of the UAV flight control end receives various data and processes the data preliminarily, and then transmits the processed data to the data analysis and display unit. The data analysis and display unit analyzes and processes the various data and displays them in real time on the display screen of the UAV flight control end. The flight control end personnel can understand the altitude and speed data of the UAV in real time, and can take corresponding measures when the UAV flight data is abnormal, thereby reducing the probability of the UAV failure expanding or even crashing (such as making the UAV return or land on the spot).

[0023] Figure 1 , 2As shown in Figure 3, after the AC 220V power supply enters the power input terminal of the power module A5, the 3rd and 4th pins of the power module A5 output a stable DC 12V power supply which enters the power input terminals of the two flow meters A6 and A7 and the two-way detection circuit and the negative pressure sensor A8. The static data detection includes the following process: (1) Separate the two-core socket of the speed sensor of the drone, the three-core socket of the height sensor and the two-core plug and three-core plug of the data acquisition and transmission circuit, place the drone 2 in the box 31 (the wind turbine is aligned with the side of the air intake pipe 36), and then install the sealing cover 32 on the box with bolts; respectively plug the two-core plug and three-core plug of the two-way detection circuit and the two-core socket of the speed sensor and the three-core socket of the height sensor together. (2) Open the first valve 33 and the second valve 33, and turn on the power switch S6 of the air compressor M6. The air compressor M6 inputs compressed air into the box 31 (the inspector adjusts the opening and closing degree of the valve core of the first valve 33 based on the flow data displayed by the first flow meter A6, so that the air flow rate entering the box remains at the set flow rate). The compressed air flows in from the front valve 33 and flows out from the rear valve 33. During the compressed air inflow and outflow process, the wind turbine M outputs a voltage signal to the other end of the adjustable resistor RP1 at the signal input end of the first detection circuit during the flow process. When the voltage output by the wind turbine at the corresponding air flow rate is appropriate but not too low, the voltage signal output by the wind turbine M is divided by the adjustable resistor RP1 and the resistor R8. The resistor R9 reduces the voltage and limits the current. The base voltage of the transistor Q1 is relatively high (higher than 0.7V). The transistor Q1 will turn on the collector to output a low level and enter the relay J 1 negative power input terminal, relay J1 will be energized to attract the control power input terminal and the normally closed contact terminal to open, alarm B will not be energized to work, indicating that the speed sensor is working normally; when the voltage output by the wind turbine is too low at the corresponding air flow rate, the voltage signal output by the wind turbine M is divided by the adjustable resistor RP1 and the resistor R8, and the resistor R9 reduces the voltage and limits the current to enter the base voltage of the transistor Q1, which is relatively low (lower than 0.7V), and the transistor Q1 will cut off the collector and no longer output a low level to enter the negative power input terminal of the relay J1. Relay J1 will lose power and no longer attract the control power input terminal and the normally closed contact terminal to close, and alarm B will be energized to work, indicating that the speed sensor is working abnormally (in the initial state, when the air compressor starts to work and the alarm works, the staff does not evaluate its performance. When the air flow rate entering the box is stable and the alarm is energized again after a period of time, it means that the speed sensor M is working abnormally).(3) Open the third valve 33 (the first and second valves 33 are closed), and turn on the power switch S1 of the negative pressure pump M5. The negative pressure pump M5 draws out the air in the box 1, and negative pressure is generated in the box 31. The negative pressure transmitter A3 outputs a voltage signal to the other end of the adjustable resistor RP2 at the signal input end of the second detection circuit (the detection personnel adjust the opening and closing degree of the valve core of the third valve 33 in combination with the negative pressure data displayed by the second flow meter A7 and the negative pressure sensor A8, so that the negative pressure degree of the air in the box remains at the set value). When the box is under the corresponding negative pressure and the voltage output by the negative pressure transmitter A3 is appropriate but not too low, the voltage signal output by the negative pressure transmitter A3 is divided by the adjustable resistor RP2 and the resistor R10. The resistor R11 reduces the voltage and limits the current. The base voltage of the transistor Q2 is relatively high (higher than 0.7V). The transistor Q2 will conduct and the collector outputs a low level and enters the negative power input end of the relay J2. The relay When the voltage output by the negative pressure transmitter A3 is inappropriate and too low, the voltage signal output by the negative pressure transmitter A3 is divided by the adjustable resistor RP2 and the resistor R10, and the base voltage of the transistor Q2 is relatively low (lower than 0.7V) after the resistor R11 reduces the voltage and limits the current. The collector of the transistor Q2 is cut off and no longer outputs a low level to enter the negative power input terminal of the relay J2. The relay J2 loses power and no longer closes the control power input terminal and the normally closed contact terminal. The alarm B1 is powered on and works, indicating that the height sensor is working abnormally (in the initial state, when the negative pressure pump just starts to work and the alarm is working, the staff does not evaluate its performance. When the negative pressure in the box is stable and the alarm is powered on again after a period of time, it means that the height sensor M is working abnormally).

[0024] Figure 1 , 2 As shown in , 3, through the above, during the use of the present invention, the speed and altitude data of the UAV flight, the voltage data of multiple sets of lifting motors of the UAV, and the total current data of the UAV can be collected in real time. The remote flight control end can grasp the voltage and voltage data of the UAV in real time. When the UAV flies abnormally, measures can be taken in time (such as making the UAV return or land on the spot), reducing the probability of the UAV failure expanding or even crashing; in the static state, the staff can detect the speed sensor and altitude sensor performance of the UAV body, and when the speed sensor and altitude sensor performance are unstable or damaged, they can be replaced in time, which provides strong technical support for the safe flight of the UAV. Figure 2 , 3The resistance values ​​of resistors R1, R2, R3, R4, R5, R6 and R7 are 4.7K; the model of single chip microcomputer module A4 is STM32C0; the model of GPRS module A9 is KB3031-NF; the power module A5 is a finished product of AC 220V DC 12V switching power module; the wind turbine M is a 5V small wind turbine; the current sensor A2 is a finished product of DC current sensor model ZL01, which has two power input terminals, one signal output terminal, one control power input terminal and one signal output terminal; the negative pressure transmitter A3 is a negative pressure vacuum detector model PCM300, which has two power input terminals, one signal output terminal and one control power input terminal. Output end; negative pressure sensor A8 is a finished negative pressure sensor of model HIGHJOIN with digital tube display; flowmeters A6 and A7 are electromagnetic vortex flowmeters of model TK1100F with digital tube display; the resistance values ​​of resistors R8, R9, R10 and R11 are 10K, 47K, 10K and 47K respectively; the resistance value of adjustable resistors RP1 and RP2 is 470K (adjusted to 24K and 25K respectively); the model of relays J1 and J2 is DC12V; the model of transistors Q1 and Q2 is 9013 (NPN); alarms B and B1 are flash alarms (the luminous surface is located at the front outer end of the component box), and the luminous colors of the two are inconsistent.

[0025] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It is obvious to those skilled in the art that the present invention is limited to the details of the above exemplary embodiments, and that the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes that fall within the meaning and scope of the equivalent elements of the claims are included in the present invention.

[0026] In addition, it should be understood that although the present specification is described according to the implementation mode, the implementation mode does not only include an independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in the embodiments can also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A drone data acquisition system, characterized in that: It includes a detection mechanism, a current sensor, a data acquisition and transmission circuit, a data receiving unit, and a data analysis and display unit; the data acquisition and transmission circuit and the current sensor are installed on a drone, the speed sensor of the drone is a wind turbine, the height sensor is a negative pressure transmitter, the control input end of the current sensor and the positive pole of the battery on the drone are electrically connected, the control output end of the current sensor and the negative pole of the battery are electrically connected to the total power input end of the drone, the power input end of the data acquisition and transmission circuit, and the power input end of the negative pressure transmitter; the wind turbine is installed at the lower end of the drone frame, and the negative pressure transmitter is installed at the upper end of the drone fuselage; the signal output end of the wind turbine, the signal output end of the negative pressure transmitter, the signal output end of the current sensor, the positive power input end of multiple lifting motors of the drone and the multi-channel signal input end of the data acquisition and transmission circuit are electrically connected respectively; the data receiving unit and the data analysis and display unit are application software installed in the control module of the drone flight control end; the detection mechanism includes a box, A sealing cover, a flow meter, a valve, a negative pressure pump, an air compressor, a detection circuit, and a negative pressure sensor. The upper end of the box is an open structure, and the sealing cover is movably installed on the box; an air inlet pipe is installed at the front end of the box, and an exhaust pipe is installed at the rear side of the box. There are multiple valves and at least two flow meters. One end of the first valve is connected to one end of the air inlet pipe, and the other end of the first valve is connected to the outlet end of the first flow meter. The air inlet end of the first flow meter is connected to the exhaust pipe of the air compressor. One of the exhaust pipes at the rear end of the box is connected to one end of the second valve, and the other exhaust pipe at the rear end of the box is connected to one end of the third valve. The other end of the third valve is connected to the air inlet end of the second flow meter. A negative pressure pipe is installed at the outlet end of the second flow meter, and the other end of the negative pressure pipe is connected to the air inlet pipe of the negative pressure pump. The air inlet pipe of the negative pressure sensor is installed at the side end of the negative pressure pipe; the detection circuit has at least two paths, and the detection circuit is installed in the component box, and the component box is installed outside the front end of the box. The wiring terminals of the height sensor and the speed sensor are electrically connected to the signal input terminals of the two detection circuits.

2. The unmanned aerial vehicle data acquisition system according to claim 1, characterized in that: The data acquisition and transmission circuit includes electrically connected resistors, a single-chip microcomputer module, and a GPRS module. One end of seven resistors is respectively connected to seven signal input ends of the single-chip microcomputer module, the signal output end of the single-chip microcomputer module is connected to the signal input end of the GPRS module, and the single-chip microcomputer module is connected to the power input end of the GPRS module.

3. The unmanned aerial vehicle data acquisition system according to claim 1, characterized in that: The data receiving unit can receive the real-time working voltage data of multiple lifting motors of the UAV and the current data of the total power input end of the UAV sent by the data acquisition and sending circuit, and transmit the data to the data analysis and display unit after preliminary processing. The data analysis and display unit can display the various data in real time through the UAV flight control display screen after analysis and processing.

4. The unmanned aerial vehicle data acquisition system according to claim 1, characterized in that: The two detection circuits have the same structure, both including electrically connected adjustable resistors and resistors, transistors, relays, and alarms. One end of the adjustable resistor is connected to one end of the first resistor and one end of the second resistor, the other end of the second resistor is connected to the base of the transistor, the collector of the transistor is connected to the negative pole of the relay, the positive power input end of the relay and the control power input end are connected, the normally closed contact end of the relay is connected to the positive power input end of the alarm, and the negative power input end of the alarm is connected to the emitter of the transistor and the other end of the first resistor.

5. The unmanned aerial vehicle data acquisition system according to claim 1, characterized in that: The valve is a kind of manual stop valve and solenoid valve.

6. A safety detection method for an unmanned aerial vehicle data acquisition system according to any one of claims 1 to 6, characterized in that: The flight data detection includes two methods: flight data detection and static data detection. The flight data detection includes the following process: S1: The wires connecting the speed sensor, altitude sensor and data acquisition and transmission circuit of the UAV are connected by plugging. When the UAV is flying, the speed sensor and altitude sensor collect the flight speed and altitude data of the UAV in real time, and the data is transmitted to the signal input end of the single-chip microcomputer module. The working voltage of multiple lifting motors of the UAV during flight and the total current data of the UAV are transmitted to the signal input end of the single-chip microcomputer module. The single-chip microcomputer module converts the input multiple analog data into digital signals and transmits them to the GPRS module. The GPRS module transmits the multiple data remotely; S2: The data receiving unit of the flight control end of the UAV body preliminarily processes the data after receiving the multiple data, and then transmits the data to the data analysis and display unit. The data analysis and display unit analyzes and processes the multiple data and displays them on the display screen of the UAV flight control end. Real-time display, flight control personnel can understand the altitude and speed data of the drone in real time, and can take corresponding measures when the drone flight data is abnormal, reducing the probability of the drone failure expanding or even crashing; static data detection includes the following processes, A1: The speed sensor, altitude sensor and wires connecting the two detection circuits of the drone are connected by plugging, and the drone is placed in the box and the sealing cover is closed; A2: Open the first valve and the second valve, and turn on the power switch of the air compressor. The air compressor inputs compressed air into the box. The compressed air flows in from the front valve and flows out from the rear valve. During the compressed air inflow and outflow process, the wind turbine outputs a voltage signal to the signal input end of the first detection circuit during the flow process. When the voltage output by the wind turbine is too low at the corresponding air flow rate, the alarm alarm prompts that the wind turbine as a speed sensor is working abnormally and the output speed voltage signal is relatively low; A3: Open the third valve and turn on the power switch of the negative pressure pump. The negative pressure pump draws out the air in the box, generating negative pressure in the box. The negative pressure sensor outputs a voltage signal to the signal input end of the second detection circuit. When the voltage output by the negative pressure sensor is too low under the corresponding negative pressure, the alarm prompts that the negative pressure sensor is working abnormally as a height sensor and the output height voltage signal is relatively low.

7. A safety detection method for an unmanned aerial vehicle data acquisition system according to any one of claim 6, characterized in that: In process S1, the faster the drone flies and the higher the altitude it flies, the higher the signal voltage at the signal input terminal of the single-chip microcomputer module is, and vice versa, the lower the signal voltage at the signal input terminal of the single-chip microcomputer module is.

8. A safety detection method for an unmanned aerial vehicle data acquisition system according to any one of claim 6, characterized in that: In process A2, the opening and closing degree of the valve core of the first valve is adjusted in combination with the flow data displayed by the first flow meter so that the flow rate of air entering the box body is maintained at the set flow rate.

9. A safety detection method for an unmanned aerial vehicle data acquisition system according to any one of claim 6, characterized in that: In process A3, the opening and closing degree of the valve core of the third valve is adjusted in combination with the flow data displayed by the second flow meter so that the negative pressure in the box is at the set data. When the negative pressure in the box reaches the set value, the third valve is closed.

10. A safety detection method for an unmanned aerial vehicle data acquisition system according to any one of claim 6, characterized in that: After the static data detection process, open the sealing cover and then take out the drone to complete the static data detection process.

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