Airborne monitoring device and method with induced current monitoring function

Abstract

The invention discloses an airborne monitoring device with an induced current monitoring function, which comprises an unmanned aerial vehicle, an unmanned aerial vehicle field and a remote controller, and is characterized in that the unmanned aerial vehicle carries a current induction ring through a quick release connector; the current induction ring comprises an electric cabinet and an induction coil; a voltage reducing and stabilizing circuit, and a filter, an amplifier and a signal sending module which are connected in sequence are arranged in the electric control box, and the second filter is electrically connected with the induction coil; the quick-release connector comprises a mounting plate fixedly connected with the bottom of the unmanned aerial vehicle, a male connector fixedly connected with the mounting plate and a female connector detachably connected with the male connector, and the female connector is fixedly connected with the current sensing ring. The quick release connector is simple in structure and reasonable in design, the male connector and the female connector are adopted as the quick release connector, and operation difficulty is lowered; the unmanned aerial vehicle and the current induction ring share the power supply, so that the total weight required by the unmanned aerial vehicle and the current induction ring is reduced, the light weight of the current induction ring is realized, and the flight performance and cruising ability of the unmanned aerial vehicle are improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of power transmission line status monitoring, and in particular relates to an airborne monitoring device and method with an induced current monitoring function. Background Art

[0002] For the location of the ground fault of the overhead line, an airborne ground fault inspection scheme is proposed, which can reduce labor intensity and save inspection costs. However, due to the limitations of the technology at that time, the traditional airborne ground fault inspection had too large a volume and weight of the induction current device, and needed to be matched with a six-axis heavy-load unmanned aircraft.

[0003] However, in actual applications, since the flight speed of large-load drones is generally low, when flying at a large angle of attack, the flight speed is too low and it is easily disturbed by wind, which can lead to safety accidents. Because the terrain and environment of line inspection are relatively complex, large-load drones cannot effectively inspect overhead line grounding faults in complex terrain due to their wingspan, take-off environment, and operation interspersed. In complex and changeable natural environments, such as lightning weather, tree growth, unstable geological conditions, etc., the flight and operation of large-load drones will be greatly affected.

[0004] Small drones have the advantages of being easy to carry, flexible, low-cost, easy to operate, widely used, highly concealed, and sustainable. These advantages make small drones play an increasingly important role in various fields. Using a small drone equipped with an induction current loop is an alternative solution.

[0005] Therefore, it is necessary to explore the miniaturization design of the induction current loop, reduce the volume and weight, and select small drones to realize the fault location solution in complex overhead lines, improve the extensiveness of the detection link, and ensure the inspection intensity and the personal safety of the operators. Summary of the invention

[0006] The technical problem to be solved by the present invention is to provide an airborne monitoring device and method with an induced current monitoring function in view of the deficiencies in the above-mentioned prior art. The device and method have a simple structure and a reasonable design. The quick-release connector adopts a male connector and a female connector, which reduces the difficulty of operation. The drone and the current induction ring share a power supply, which reduces the total weight required for the drone and the current induction ring, realizes the lightweight of the current induction ring, and helps to improve the flight performance and endurance of the drone.

[0007] In order to solve the above technical problems, the technical solution adopted by the present invention is: an airborne monitoring device with an induction current monitoring function, characterized in that: it includes a drone, a drone airport for drone communication, and a remote controller, and the drone is equipped with a current induction ring through a quick-release connector;

[0008] The current induction loop includes an electric control box and an induction coil; the electric control box is provided with a step-down voltage stabilizing circuit, and a second filter, an amplifier and a signal sending module connected in sequence, and the second filter is electrically connected to the induction coil;

[0009] The quick-release connector includes a mounting plate fixedly connected to the bottom of the drone, a male connector fixedly connected to the mounting plate, and a female connector detachably connected to the male connector, wherein the female connector is fixedly connected to the current induction ring;

[0010] A wire through hole is provided on the mounting plate, and one end of the wire passes through the wire through hole and is connected to the VCC power supply of the drone; the conductive end of the male connector is fixedly connected to the other end of the wire; one end of the female connector is connected to the conductive end of the male connector, and the other end of the female connector is connected to the step-down voltage stabilization circuit.

[0011] The above-mentioned airborne monitoring device with an induced current monitoring function is characterized in that: the male connector includes a first substrate, a second substrate and a male connector body, the first substrate is provided with a receiving cavity for accommodating a conductive column along the length direction of the male connector, and the other end of the wire is electrically connected to the conductive column, and the second substrate is provided with a receiving cavity for accommodating a conductive sheet along the length direction of the male connector, and the conductive column is electrically connected to the conductive sheet; the male connector body is a hollow structure, and a track is provided on the side wall of the male connector body, the starting end of the track is connected to the bottom surface of the side wall of the male connector body, and the end of the track is connected to the limiting hole.

[0012] The above-mentioned airborne monitoring device with an induction current monitoring function is characterized in that: the female connector is a hollow cylindrical structure, and the female connector includes a conductive contact arranged at one end of the female connector body, and the conductive contact extends out of the other end of the female connector through a connecting wire.

[0013] The above-mentioned airborne monitoring device with an induced current monitoring function is characterized in that: through holes are respectively opened on both sides of the side wall of the female connector, guide cylinders are arranged in the through holes, and a support body corresponding to the position of the guide cylinder is arranged on the inner wall of the female connector, and the two sides of the support body are respectively fixedly connected to the two guide cylinders, one end of the spring is fixedly connected to the bottom of the guide cylinder, and the other end of the spring is fixedly connected to the limit piece; the length of the spring is greater than the length of the guide cylinder, and the minimum safe compression length of the spring is less than the length of the guide cylinder; the limit piece can extend out of the limit hole.

[0014] The above-mentioned airborne monitoring device with induced current monitoring function is characterized in that: a signal receiving module, a first filter 28 and a processor connected in sequence are arranged in the drone, and the processor is communicatively connected to the PSDK platform of the drone; the signal sending module is communicatively connected to the signal receiving module.

[0015] The above-mentioned airborne monitoring device with the induction current monitoring function is characterized in that the induction coil includes a closed annular iron core and a coil wound on the outer wall of the closed annular iron core.

[0016] The above-mentioned airborne monitoring device with an induction current monitoring function is characterized in that: the step-down and voltage-stabilizing circuit is used to reduce the 24V DC power of the drone to 5V after a primary step-down, and then to 3.3V after a secondary step-down.

[0017] An airborne monitoring method with an induced current monitoring function of the present invention is characterized by comprising the following steps:

[0018] Step 1: Connect the male connector that is fixedly connected to the current sensing ring and the female connector that is fixedly connected to the drone;

[0019] Step 2: Turn on the drone and the current induction loop is powered;

[0020] Step 3: The drone takes off, and the current induction ring moves along the overhead line of the distribution network to cut and sense, obtain the sensing information, and transmit the sensing information to the electric control box;

[0021] Step 4: The PSDK platform obtains the sensing information and sends it together with the aircraft's track information to the UAV airport. The UAV airport data link sends the sensing information and the aircraft's track information to the ground terminal.

[0022] Step 5: The ground terminal determines the location of the fault point.

[0023] The above-mentioned airborne monitoring method with induced current monitoring function is characterized in that it also includes a signal generator, and the signal generator is used to inject a characteristic AC signal into the fault line.

[0024] The above-mentioned airborne monitoring method with induced current monitoring function is characterized in that the output signal of the signal generator is a 60HZ AC signal.

[0025] Compared with the prior art, the present invention has the following advantages:

[0026] 1. The invention has a simple structure, reasonable design, and is easy to implement and operate.

[0027] 2. The quick-release connector of the present invention adopts a male connector and a female connector, and can be quickly disassembled and installed. It only needs to be pressed, inserted and slid up as required, without using complicated tools or spending a lot of time. It not only reduces the difficulty of operation, but also improves the reliability and stability of the connection.

[0028] 3. In the present invention, the drone and the current induction loop share a power supply, and there is no need to equip each component with a separate power supply. This can reduce the total weight required for the drone and the current induction loop, achieve lightweight current induction loops, and help improve the flight performance and endurance of the drone, enabling it to carry heavier payloads or fly longer distances.

[0029] 4. The main body of the male connector is a hollow structure, and the female connector is a hollow cylindrical structure, which further realizes the lightweight of the current induction ring.

[0030] In summary, the present invention has a simple structure and a reasonable design. The quick-release connector adopts a male connector and a female connector, which reduces the difficulty of operation. The drone and the current induction ring share a power supply, which reduces the total weight required for the drone and the current induction ring, realizes the lightweight of the current induction ring, and helps to improve the flight performance and endurance of the drone.

[0031] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a structural schematic diagram of the present invention.

[0033] Figure 2 This is a schematic diagram of the structure of the UAV equipped with a current induction loop according to the present invention.

[0034] Figure 3 for Figure 2 A-direction view.

[0035] Figure 4 It is a structural schematic diagram of the quick-release connector of the present invention.

[0036] Figure 5 It is a schematic structural diagram of the mounting plate and the male connector of the present invention.

[0037] Figure 6 It is a schematic structural diagram of the female connector of the present invention.

[0038] Figure 7 It is a circuit principle block diagram of the present invention.

[0039] Description of reference numerals:

[0040] 1—remote controller; 2—drone airport; 3—drone;

[0041] 4—current induction ring; 5—female connector; 6—male connector;

[0042] 7—mounting plate; 8—conducting wire; 9—first substrate;

[0043] 10—conductive sheet; 11—second substrate; 12—limiting hole;

[0044] 13—track; 14—male connector body; 16—guide cylinder;

[0045] 17—limiting member; 18—spring; 19—conductive contact;

[0046] 20—support body; 23—step-down voltage stabilization circuit; 24—second filter;

[0047] 25—amplifier; 26—signal sending module; 27—signal receiving module;

[0048] 28—first filter; 29—processor; 30—PSDK platform;

[0049] 41—Electrical control box; 42—Induction coil. DETAILED DESCRIPTION

[0050] The method of the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments of the present invention.

[0051] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0052] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0053] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein, for example. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0054] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0055] Embodiment 1

[0056] like Figures 1 to 7 As shown, an airborne monitoring device with an induction current monitoring function of the present invention includes a drone 3 and a drone airport 2 and a remote controller 1 for communicating with the drone 3. The drone 3 is equipped with a current induction ring 4 via a quick-release connector.

[0057] It should be noted that the staff sends control instructions to the UAV 3 through the remote control 1, the UAV 3 executes the control instructions and flies according to the track, the current induction ring 4 cuts the magnetic flux lines to obtain the induction information, the PSDK platform 30 of the UAV 3 obtains the induction information, and sends the induction information and the aircraft's track information to the UAV airport 2. The UAV airport 2 data link sends the induction information and the aircraft's track information to the ground terminal, and the ground terminal determines the location of the fault point.

[0058] The communication between the drone 3 and the remote controller 1 is achieved through radio waves, including a variety of wireless communication technologies, such as radio frequency signals, Bluetooth, Wi-Fi, etc. Among them, the 2.4GHz and 5.8GHz frequency bands are the most commonly used remote control frequencies. The communication between the drone 3 and the drone airport 2 adopts a communication protocol to ensure the accurate transmission of data and the accurate execution of instructions. These protocols usually include security measures such as data encapsulation, verification, and encryption to ensure that the drone 3 can accurately receive and execute instructions from the drone airport 2. The communication between the drone airport 2 and the ground terminal usually involves functions such as data transmission, command issuance, and status monitoring. The communication is wired or wireless, depending on the application scenario and requirements. In scenarios where long-distance communication or mobile communication is required, wireless communication methods such as 4G / 5G mobile communication networks and Wi-Fi may be used between the drone 3 and the ground terminal.

[0059] The current induction loop 4 includes an electric control box 41 and an induction coil 42 ; a step-down voltage stabilizing circuit 23 , and a second filter 24 , an amplifier 25 and a signal sending module 26 connected in sequence are arranged in the electric control box 41 ; the second filter 24 is electrically connected to the induction coil 42 .

[0060] In the current sensing loop 4, the main function of the filter is to remove noise and interference signals in the current signal to ensure the accuracy and stability of the signal. Through filtering, the signal-to-noise ratio of the current signal can be improved, making the signal quality higher and easier to detect and measure. The amplifier 25 in the current sensing loop 4 mainly plays the role of signal amplification. Through amplification, the measurement accuracy of the current signal can be improved, making the measurement result more accurate and reliable.

[0061] The quick-release connector includes a mounting plate 7 fixedly connected to the bottom of the drone 3, a male connector 6 fixedly connected to the mounting plate 7, and a female connector 5 detachably connected to the male connector 6, wherein the female connector 5 is fixedly connected to the current sensing ring 4; a wire through hole is provided on the mounting plate 7, and one end of the wire 8 passes through the wire through hole and is connected to the VCC power supply of the drone 3; the conductive end of the male connector 6 is fixedly connected to the other end of the wire 8; one end of the female connector 5 is connected to the conductive end of the male connector 6, and the other end of the female connector 5 is connected to the step-down voltage stabilizing circuit 23.

[0062] The quick-release connector uses a male connector 6 and a female connector 5, and can be quickly disassembled and installed without using complicated tools or spending a lot of time, which can significantly improve work efficiency. Compared with the traditional threaded connection method, the quick-release connector does not require cumbersome thread rotation operations, but only needs to be pressed, inserted and slid up as required. This simplified operation process not only reduces the difficulty of operation, but also improves the reliability and stability of the connection.

[0063] In this embodiment, the current induction loop 4 and the drone share a power supply. When the drone is not powered on, the current induction loop 4 is connected to the same quick-release connector, and the current induction loop 4 and the drone are powered on and started at the same time. Taking the DJI drone M350 as an example, the rated voltage of its RTKVCC pin is 24V. The 24V voltage is drawn out and led to the buck stabilizing circuit 23 through the wire 8, the male connector and the female connector. The buck stabilizing circuit 23 reduces the voltage to 5V once and 3.3V twice. 5V and 3.3V are used to supply power to the electric control box 41 respectively.

[0064] The drone 3 and the current induction loop 4 share a power supply, and there is no need to equip each component with a separate power supply. This can reduce the total weight required for the drone 3 and the current induction loop 4, and achieve lightweight current induction loop 4, which helps to improve the flight performance and endurance of the drone 3, allowing it to carry heavier payloads or fly longer distances.

[0065] In this embodiment, the male connector 6 includes a first substrate 9, a second substrate 11 and a male connector body 14. The first substrate 9 is provided with a receiving cavity for accommodating a conductive column along the length direction of the male connector 6, and the other end of the wire 8 is electrically connected to the conductive column. The second substrate 11 is provided with a receiving cavity for accommodating a conductive sheet 10 along the length direction of the male connector 6, and the conductive column is electrically connected to the conductive sheet 10; the male connector body 14 is a hollow structure, and a track 13 is provided on the side wall of the male connector body 14. The starting end of the track 13 is connected to the bottom surface of the side wall of the male connector body 14, and the end of the track 13 is connected to the limiting hole 12.

[0066] It should be noted that the track 13 is adapted to the limiting member 17 .

[0067] During specific use, the conductive column is usually nested and fixed in the second substrate 11 by welding, threaded connection or other mechanical means, ensuring a stable connection between the wire 8 and the conductive sheet 10. On the one hand, the conductive column has a large contact area and excellent conductivity to reduce contact resistance. If the conductive column is removed, the contact resistance between the wire 8 and the conductive sheet 10 will increase, resulting in increased power loss. On the other hand, the drone 3 or the current induction loop 4 may be affected by vibration and impact. If the conductive column fails or is damaged, a new conductive column can be easily replaced without replacing or repairing the entire circuit board, reducing maintenance costs and time, and improving the maintainability of electronic equipment.

[0068] In this embodiment, the female connector 5 is a hollow cylindrical structure, and the female connector 5 includes a conductive contact 19 arranged at one end of the female connector body, and the conductive contact 19 extends out of the other end of the female connector 5 through a connecting wire. It should be noted that the male connector body 14 and the female connector body are made of insulating materials.

[0069] The male connector body 14 is a hollow structure, and the female connector 5 is a hollow cylindrical structure, which further realizes the lightness of the current induction ring 4.

[0070] In actual use, when the conductive contact 19 is electrically connected to the conductive sheet 10, the conductive contact 19 is in a cross shape. The cross structure has good mechanical stability and can resist large mechanical stress and vibration, ensuring that the contact is not easily deformed or damaged during long-term use. On the other hand, it is conducive to the uniform distribution of current, avoiding the problem of excessive local current density, helping to reduce the thermal effect and wear of the contact, and improving the service life of the contact.

[0071] In this embodiment, through holes are respectively opened on both sides of the side wall of the female connector 5, and a guide cylinder 16 is arranged in the through hole. A support body 20 corresponding to the position of the guide cylinder 16 is arranged on the inner wall of the female connector 5, and both sides of the support body 20 are respectively fixedly connected to the two guide cylinders 16, one end of the spring 18 is fixedly connected to the bottom of the guide cylinder 16, and the other end of the spring 18 is fixedly connected to the limit member 17; the length of the spring 18 is greater than the length of the guide cylinder 16, and the minimum safe compression length of the spring 18 is less than the length of the guide cylinder 16; the limit member 17 can extend out of the limit hole 12.

[0072] In actual use, first press the limit piece 17. Under the action of the expansion and contraction force of the spring 18, the limit piece 17 retracts into the guide tube 16. Then, press the limit piece 17, extend the female connector 5 into the male connector 6, and slide up along the track 13 until the limit piece 17 is aligned with the limit hole 12. The external force of the fingers and the inner wall of the female connector 5 on the limit piece 17 is lost. At this time, the limit piece 17 extends out of the limit hole 12.

[0073] In a possible embodiment, a protrusion is provided on the circumferential inner wall of the limiting hole, and a recess matching the protrusion is provided on the circumferential outer wall of the limiting member 17 .

[0074] In a possible embodiment, the limiting hole 12 is a circular hole, and the limiting member 17 is in the shape of a truncated cone, wherein the upper base diameter of the truncated cone is larger than the lower base diameter. The diameter of the limiting hole 12 is between the upper base diameter and the lower base diameter of the truncated cone. The lower base diameter of the truncated cone is smaller than the diameter of the track 13.

[0075] In this embodiment, the drone 3 is provided with a signal receiving module 27, a filter 28 and a processor 29 which are connected in sequence. The processor 29 is communicatively connected to the PSDK platform 30 of the drone 3; the signal sending module 26 is communicatively connected to the signal receiving module 27.

[0076] In this embodiment, the induction coil 42 includes a closed annular iron core and a coil wound on the outer wall of the closed annular iron core. The closed annular iron core and the coil wound on the outer wall of the closed annular iron core form a closed circuit, and the current in the overhead line will generate a magnetic field around it. When the current induction loop approaches this magnetic field, an electromotive force will be induced, and then a current will be generated. The magnitude of this induced current is proportional to the magnitude of the current in the overhead line, and is related to parameters such as the number of turns of the coil and the magnetic permeability of the magnetic core. Therefore, a closed loop coil can be used to detect ground faults.

[0077] In this embodiment, the step-down and voltage stabilizing circuit 23 is used to reduce the 24V DC power of the drone 3 to 5V after a primary step-down, and then to 3.3V after a secondary step-down.

[0078] Embodiment 2

[0079] An airborne monitoring method with an induced current monitoring function according to this embodiment includes the following steps:

[0080] Step 1: Connect the male connector 5 fixedly connected to the current sensing loop 4 and the female connector 6 fixedly connected to the drone 3.

[0081] The female connector 5 is fixedly connected to the current sensing loop 4; a wire through hole is provided on the mounting plate 7, and one end of the wire 8 passes through the wire through hole and is connected to the VCC power supply of the drone 3; the conductive end of the male connector 6 is fixedly connected to the other end of the wire 8; one end of the female connector 5 is connected to the conductive end of the male connector 6, and the other end of the female connector 5 is connected to the step-down voltage stabilization circuit 23.

[0082] The male connector 6 includes a first substrate 9, a second substrate 11 and a male connector body 14. The first substrate 9 is provided with a receiving cavity for accommodating a conductive column along the length direction of the male connector 6, and the other end of the wire 8 is electrically connected to the conductive column. The second substrate 11 is provided with a receiving cavity for accommodating a conductive sheet 10 along the length direction of the male connector 6, and the conductive column is electrically connected to the conductive sheet 10. The male connector body 14 is a hollow structure, and a track 13 is provided on the side wall of the male connector body 14. The starting end of the track 13 is connected to the bottom surface of the side wall of the male connector body 14, and the end of the track 13 is connected to the limiting hole 12.

[0083] The female connector 5 is a hollow cylindrical structure. The female connector 5 includes a conductive contact 19 arranged at one end of the female connector body. The conductive contact 19 extends out of the other end of the female connector 5 through a connecting wire.

[0084] Through holes are respectively opened on both sides of the side wall of the female connector 5, and guide cylinders 16 are arranged in the through holes. A support body 20 corresponding to the position of the guide cylinder 16 is arranged on the inner wall of the female connector 5, and both sides of the support body 20 are fixedly connected to the two guide cylinders 16 respectively. One end of the spring 18 is fixedly connected to the bottom of the guide cylinder 16, and the other end of the spring 18 is fixedly connected to the limit member 17; the length of the spring 18 is greater than the length of the guide cylinder 16, and the minimum safe compression length of the spring 18 is less than the length of the guide cylinder 16; the limit member 17 can extend out of the limit hole 12.

[0085] Step 2: The drone 3 is turned on, and the current induction loop 4 is powered.

[0086] In this embodiment, the current induction loop 4 and the drone share a power supply. When the drone is not powered on, the current induction loop 4 is connected to the same quick-release connector, and the current induction loop 4 and the drone are powered on and started at the same time. Taking the DJI drone M350 as an example, the rated voltage of its RTKVCC pin is 24V. The 24V voltage is drawn out and led to the buck stabilizing circuit 23 through the wire 8, the male connector and the female connector. The buck stabilizing circuit 23 reduces the voltage to 5V once and 3.3V twice. 5V and 3.3V are used to supply power to the electric control box 41 respectively.

[0087] The drone and the current induction loop share a power supply, and there is no need to equip each component with a separate power supply. This can reduce the total weight required for the drone 3 and the current induction loop 4 and achieve lightweight current induction loop 4. This helps to improve the flight performance and endurance of the drone, allowing it to carry heavier payloads or fly longer distances.

[0088] It is necessary to select a suitable drone. The drone needs to be small and foldable, with a lightweight design, easy to carry during operation, and convenient for one person to operate. During operation, ensure that the drone 3 has stable flight, easy control, and sufficient load capacity. Conduct an environmental assessment of the area where the overhead lines are located to understand the impact of factors such as terrain, climate, and electromagnetic interference on drone flight and current measurement. According to the assessment results, a flight plan is formulated to determine parameters such as flight altitude, speed, and route to ensure that the drone 3 can complete the task safely and effectively. According to the flight plan, the remote controller 1 controls the drone 3 to take off and conduct inspections along the predetermined route. During the inspection process, the drone 3 should maintain a stable flight state and avoid severe vibration and shaking to ensure the measurement accuracy of the current induction loop 4.

[0089] In a possible embodiment, drone 3 selects the DJI Mavic 3E / 3T model, the bare machine weight with propellers is 915 grams to 920 grams, its cruising time is up to 45 minutes, it supports 100-watt high-energy fast charging, and can also achieve 88-watt fast charging directly through the drone body. It has a PSDK unified interface to facilitate the access of third-party hardware devices.

[0090] During the flight, pay close attention to the flight status of the drone and changes in the surrounding environment to ensure flight safety. In case of emergencies, take emergency measures immediately, such as lowering the flight altitude, changing the route or making an emergency landing.

[0091] Step 3: The drone 3 takes off, and the current induction ring 4 moves along the overhead line of the distribution network to perform cutting induction, obtain induction information, and transmit the induction information to the electric control box 41 .

[0092] In overhead line fault detection, when a ground fault occurs in the line, the fault current will flow through the grounding resistor and the earth to form a closed loop, which will generate an additional magnetic field around the overhead line. The current induction loop 4 can detect the change of this magnetic field, thereby determining whether there is a ground fault in the line.

[0093] When the drone 3 flies close to the overhead line, the current in the overhead line will generate a magnetic field around it. When the current induction loop 4 approaches this magnetic field, it will induce an electromotive force, and then generate a current. The magnitude of this induced current is proportional to the magnitude of the current in the overhead line, and is related to known parameters such as the number of turns of the coil of the current induction loop 4 and the magnetic permeability of the magnetic core.

[0094] Step 4: PSDK platform 30 obtains sensing information, and sends the sensing information and the aircraft's track information to UAV airport 2. The UAV airport 2 data link sends the sensing information and the aircraft's track information to the ground terminal;

[0095] Step 5: The ground terminal determines the location of the fault point.

[0096] The ground terminal processes and analyzes the received sensing information and the aircraft's track information in real time. By setting the current threshold, it can be determined whether there is a ground fault in the overhead line. If abnormal data is found, the track information corresponding to the abnormal data is searched to lock the suspected fault point, mark it immediately, and arrange for further inspection or maintenance.

[0097] In this embodiment, a signal generator is also included, and the signal generator is used to inject a characteristic AC signal into the fault line. The output signal of the signal generator is a 60HZ AC signal.

[0098] The above description is only an embodiment of the present invention and does not limit the present invention in any way. Any simple modification, change and equivalent structural change made to the above embodiment based on the technical essence of the present invention still falls within the protection scope of the technical solution of the present invention.

Claims

1. An airborne monitoring device with an induced current monitoring function, characterized in that: It comprises a drone (3), a drone field (2) and a remote controller (1) for communicating with the drone (3), wherein the drone (3) is equipped with a current induction loop (4) via a quick-release connector; The current induction loop (4) comprises an electric control box (41) and an induction coil (42); a step-down voltage stabilization circuit (23), and a second filter (24), an amplifier (25) and a signal transmission module (26) connected in sequence are arranged in the electric control box (41); the second filter (24) is electrically connected to the induction coil (42); The quick-release connector comprises a mounting plate (7) fixedly connected to the bottom of the drone (3), a male connector (6) fixedly connected to the mounting plate (7), and a female connector (5) detachably connected to the male connector (6), wherein the female connector (5) is fixedly connected to the current induction ring (4); A wire through hole is provided on the mounting plate (7), and one end of the wire (8) passes through the wire through hole and is connected to the VCC power supply of the drone (3); the conductive end of the male connector (6) is fixedly connected to the other end of the wire (8); one end of the female connector (5) is connected to the conductive end of the male connector (6), and the other end of the female connector (5) is connected to the step-down voltage stabilization circuit (23).

2. An airborne monitoring device with an induction current monitoring function according to claim 1, characterized in that: The male connector (6) comprises a first substrate (9), a second substrate (11) and a male connector body (14); the first substrate (9) is provided with a receiving cavity for receiving a conductive column along the length direction of the male connector (6); the other end of the wire (8) is electrically connected to the conductive column; the second substrate (11) is provided with a receiving cavity for receiving a conductive sheet (10) along the length direction of the male connector (6); the conductive sheet is electrically connected to the conductive sheet (10); the male connector body (14) is a hollow structure; a track (13) is provided on the side wall of the male connector body (14); the start end of the track (13) is connected to the bottom surface of the side wall of the male connector body (14); the end of the track (13) is connected to the limiting hole (12).

3. An airborne monitoring device with an induction current monitoring function according to claim 1, characterized in that: The female connector (5) is in the form of a hollow cylindrical structure. The female connector (5) comprises a conductive contact (19) arranged at one end of the female connector body. The conductive contact (19) extends out of the other end of the female connector (5) through a connecting wire.

4. An airborne monitoring device with an induction current monitoring function according to claim 2, characterized in that: Through holes are respectively provided on both sides of the side wall of the female connector (5), and a guide cylinder (16) is arranged in the through hole. A support body (20) corresponding to the position of the guide cylinder (16) is provided on the inner wall of the female connector (5), and both sides of the support body (20) are respectively fixedly connected to the two guide cylinders (16). One end of the spring (18) is fixedly connected to the bottom of the guide cylinder (16), and the other end of the spring (18) is fixedly connected to the limit member (17); the length of the spring (18) is greater than the length of the guide cylinder (16), and the minimum safe compression length of the spring (18) is less than the length of the guide cylinder (16); and the limit member (17) can extend out of the limit hole (12).

5. The airborne monitoring device with an induction current monitoring function according to claim 1, characterized in that: The drone (3) is provided with a signal receiving module (27), a first filter (28) and a processor (29) which are connected in sequence; the processor (29) is communicatively connected to a PSDK platform (30) of the drone (3); and the signal sending module (26) is communicatively connected to the signal receiving module (27).

6. An airborne monitoring device with an induction current monitoring function according to claim 1, characterized in that: The induction coil (42) comprises a closed annular iron core and a coil wound around the outer wall of the closed annular iron core.

7. An airborne monitoring device with an induction current monitoring function according to claim 1, characterized in that: The step-down and voltage-stabilizing circuit (23) is used to reduce the 24V direct current of the drone (3) to 5V after a primary step-down, and then to 3.3V after a secondary step-down.

8. An airborne monitoring method with an induced current monitoring function, characterized in that: Step 1: Connecting a male connector (5) fixedly connected to the current sensing loop (4) and a female connector (6) fixedly connected to the drone (3); Step 2: The drone (3) is turned on, and the current induction loop (4) is powered; Step 3: The drone (3) takes off, and the current induction loop (4) moves along the overhead line of the distribution network to cut and sense, obtains sensing information, and transmits the sensing information to the electric control box (41); Step 4: The PSDK platform (30) obtains the sensing information and sends the sensing information and the aircraft's track information to the UAV airport (2). The UAV airport (2) data link sends the sensing information and the aircraft's track information to the ground terminal; Step 5: The ground terminal determines the location of the fault point.

9. An airborne monitoring method with an induction current monitoring function according to claim 8, characterized in that: The device also includes a signal generator, which is used for injecting a characteristic AC signal into the fault line.

10. An airborne monitoring method with an induction current monitoring function according to claim 9, characterized in that: The output signal of the signal generator is a 60HZ AC signal.

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