1000kV extra-high voltage unmanned aerial vehicle airborne electricity testing device and method

Abstract

The invention discloses an airborne electricity testing device and method for a 1000kV extra-high voltage unmanned aerial vehicle, and relates to the technical field of electricity testing devices.The airborne electricity testing device comprises a base, an unmanned aerial vehicle body and a wire clamp mechanism, and the wire clamp mechanism comprises a sleeving frame. According to the 1000kV extra-high voltage unmanned aerial vehicle airborne electricity testing device and method disclosed by the invention, after the unmanned aerial vehicle moves the electroscope body and the conductive wire clamp mechanism to the periphery of the high-voltage wire, the electric telescopic rod I is adjusted to drive the positioning pressure head to extrude and position the grounding wire penetrating through the wire penetrating frame; and then an electric telescopic rod II is adjusted to drive each pushing half frame to push the grounding wire in the mounting rack, so that the grounding wire is of an S-shaped structure, and the situation that the grounding wire at the periphery of the electroscope body is in a large-amplitude swinging state due to blowing of wind power, shaking of the grounding wire is cut off from a tension adjusting mechanism, and the grounding wire is prevented from being damaged is avoided. And the influence on the stability of the conductive wire clamp mechanism and the electroscope body is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of electrical testing devices, and in particular to a 1000kV ultra-high voltage unmanned aerial vehicle airborne electrical testing device and method. Background Art

[0002] When conducting 1000kV ultra-high voltage electrical testing, in order to avoid safety accidents caused by human contact, under normal circumstances, an unmanned aerial vehicle is used to carry a wire clamp and lift it to the high-altitude wire, and then cooperate with the ground grounding terminal to complete the electrical testing operation.

[0003] When the existing airborne electrical test device is in use, after the connecting wire clamp is connected to the high-altitude wire, the grounding wire connected to the electrical tester is in a loose state because it is transported from the ground to the high altitude. If the grounding wire at the high-altitude electrical tester encounters strong winds, the swing amplitude is large, which greatly affects the connection stability between the connecting wire clamp and the wire, and then affects the accuracy of the electrical test result, reducing the use value of the airborne electrical test device. Summary of the invention

[0004] The invention discloses an airborne electrical test device for a 1000kV ultra-high voltage unmanned aerial vehicle, aiming to solve the technical problem that, during use of the existing airborne electrical test device, after the connection between the connecting wire clamp and the high-altitude wire is completed, since the grounding wire connected to the electrical tester is transported from the ground to the high altitude and is in a loose state, if the grounding wire at the high-altitude electrical tester encounters strong wind, the swing amplitude is large, thereby greatly affecting the connection stability between the connecting wire clamp and the wire, and then affecting the accuracy of the electrical test result.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A 1000kV UHV UAV airborne electrical testing device comprises a base, a UAV body and a conductor clamp mechanism, wherein the conductor clamp mechanism comprises a socket frame, and one side of the socket frame is fixedly connected to two mounting posts, and one end of the two mounting posts is provided with a same tension adjustment mechanism, wherein the tension adjustment mechanism comprises a mounting frame, and the mounting frame is fixedly connected to one end of the two mounting posts, and the inner side wall of the mounting frame is fixedly connected to three inner blocks, and one side of the three inner blocks is fixedly connected to an electric telescopic rod 2, and the output end of each electric telescopic rod 2 is fixedly connected to a push semi-telescopic rod. The invention relates to a frame, wherein the three pushing half frames are staggered and distributed, a plurality of groups of shock-absorbing spring rods are fixedly connected to the inner arc surface of each pushing half frame, and the end of each group of shock-absorbing spring rods is fixedly connected to an extrusion rod, and a friction groove is provided on the outer wall of the extrusion rod away from the pushing half frame, the inner walls of the mounting frame on both sides near the bottom end are fixedly connected to fixing blocks, and the opposite sides of the two fixing blocks are fixedly connected to the same threading frame, the outer wall of the threading frame is fixedly connected to two electric telescopic rods one, the output ends of the two electric telescopic rods one are fixedly connected to positioning pressure heads, and the bottom of the threading frame is fixedly connected to an extension sleeve.

[0007] By providing a tension adjustment mechanism, after the drone moves the electroscope body and the conductive wire clamp mechanism to the periphery of the high-voltage wire, the electric telescopic rod 1 is adjusted to drive the positioning pressure head to squeeze and position the grounding wire passing through the threading frame, and then the electric telescopic rod 2 is adjusted to drive each pushing half frame to push the grounding wire located inside the mounting frame to make it present an S-shaped structure, thereby adjusting the grounding wire at the end of the electroscope body to make it in a taut state, preventing the grounding wire in the air from being blown by wind and causing the grounding wire located outside the electroscope body to be in a large swing state, and isolating the shaking of the grounding wire from the tension adjustment mechanism to prevent it from affecting the stability of the conductive wire clamp mechanism and the electroscope body, thereby improving the stability of the electroscope body during operation.

[0008] In a preferred solution, a plurality of docking rods are fixedly connected to the side of the sleeve frame facing the mounting frame, and one end of the plurality of docking rods is fixedly connected to the same sliding sleeve, the interior of the sliding sleeve is slidingly connected to the electroscope body, and the outer side wall of the sliding sleeve is fixedly connected to a pulling frame at equal distances, and each pulling frame is fixedly connected to a pulling spring rod, and one end of the pulling spring rod is fixedly connected to the outer side wall of the electroscope body.

[0009] In a preferred solution, mounting grooves are provided on the inner walls on both sides of the sleeve frame near the bottom, and the interiors of the two mounting grooves are connected to deflection pressure plates through bearings, the tops of the two deflection pressure plates are fixedly connected to metal conductive sheets, and the two deflection pressure plates are fixedly connected to extrusion spring rods 1 at equal distances on one side of the inner wall of the sleeve frame, one end of the extrusion spring rod 1 is fixedly connected to an inner wall of one side of the sleeve frame, and the metal probe of the electroscope body is in contact with one of the metal conductive sheets.

[0010] By providing a conductive wire clamp mechanism, after the drone body moves the sleeve frame above the high-voltage wire, the hydraulic cylinder is adjusted to drive the sleeve frame to move downward. During its downward movement, the deflection pressure plate contacts and squeezes the high-voltage wire, and the high-voltage wire is gradually pressed into the two metal conductive sheets. The high-voltage wire contacts the two metal conductive sheets, and then the air pump is started to blow gas into the reinforced airbag. The reinforced airbag gradually expands and squeezes the deflection pressure plate, so that the interaction force between the metal conductive sheet and the high-voltage wire gradually increases, thereby improving the stability of the connection between the metal conductive sheet and the high-voltage wire. At the same time, the reinforced airbag squeezes the adjustment plate, so that the two blocking round rods contact each other, and the high-voltage wire located between the two metal conductive sheets is blocked by the two blocking round rods, thereby reducing the probability of the high-voltage wire detaching from between the two metal conductive sheets and improving the stability in the electrical testing operation.

[0011] In a preferred solution, the outer side walls of the two deflection pressure plates close to the metal conductive sheet are provided with docking holes, and the bottom inner walls of the two docking holes are connected to adjustment plates through hinges, the tops of the two adjustment plates are fixedly connected to blocking round rods, the opposite sides of the two deflection pressure plates are fixedly connected to rear support plates, and the side of the rear support plate facing the adjustment plate is fixedly connected to two extrusion spring rods at equal distances, and one end of the two extrusion spring rods is fixedly connected to one side of the adjacent adjustment plate.

[0012] In a preferred solution, the sleeve frame is fixedly connected to a limiting frame on the inner wall near the rear support plate, and the interior of the limiting frame is fixedly connected to a reinforced airbag, the reinforced airbag is partially clamped between the rear support plate and the adjustment plate, both sides of the sleeve frame are fixedly connected to pump ring frames, the interiors of the two pump ring frames are fixedly connected to air pumps, the air delivery end of the air pump is fixedly connected to an air delivery pipe, one end of the air delivery pipe is inserted into the interior of the reinforced airbag, an exhaust hole is opened on one side of the reinforced airbag, the interior of the exhaust hole is fixedly connected to an exhaust pipe, and the outer wall of the exhaust pipe is connected to a solenoid valve through a flange.

[0013] In a preferred solution, a mounting seat is fixedly connected to the top of the UAV body, and a top plate is fixedly connected to the top of the mounting seat, two hydraulic cylinders 2 are fixedly connected to the top of the top plate, the output ends of the two hydraulic cylinders 2 are fixedly connected to a lifting plate, the bottom of the lifting plate is fixedly connected to a plurality of positioning columns, two docking turntables are sleeved on the top of the mounting seat, the positioning columns are clamped in the positioning holes on the docking turntables, a fixed extension arm is placed on the outside of the two docking turntables on the mounting seat, the two docking turntables are connected to the fixed extension arm through bearings, and an impact reduction reinforcement mechanism is provided at the end of the fixed extension arm away from the mounting seat.

[0014] By providing an impact reduction reinforcement mechanism, when the electrical testing device is moved to the high-voltage wire through the drone body, since the drone body is at a certain distance from the high-voltage wire, the connecting arm between the two is longer and is subjected to greater wind impact. In the present invention, the connecting arm is divided into a fixed extension arm and a movable extension arm. When the wind impacts the movable extension arm, the buffer spring rod 1 and the buffer spring rod 2 cooperate with each other to reduce the impact of the wind on the movable extension arm, thereby reducing the impact of the wind on the drone body, ensuring that the drone body can drive the electrical testing device to stay stably in the air.

[0015] In a preferred embodiment, the impact reduction reinforcement mechanism includes a semicircular guide rail and a movable extension arm, and one end of the fixed extension arm is fixedly connected to two connecting rods, the semicircular guide rail is fixedly connected to the opposite sides of the two connecting rods, and the fixed extension arm is fixedly connected to an axis frame on one side between the two connecting rods, and the top inner wall and the bottom inner wall of the axis frame are connected to the same connecting shaft through bearings, the movable extension arm is fixedly connected to the outer wall of the connecting shaft, and the outer wall of the connecting shaft is fixedly connected to two groups of buffer spring rods one, one end of the two groups of buffer spring rods one are fixedly connected to an integration rod, and the integration rod is fixedly connected to the outer wall of the fixed extension arm, the inner sliding connection of the semicircular guide rail is connected to a sliding frame, a through hole is opened on the sliding frame, the movable extension arm passes through the through hole, and both sides of the sliding frame are fixedly connected to buffer spring rods two, and one end of the two buffer spring rods two are fixedly connected to the inner wall of the semicircular guide rail.

[0016] In a preferred solution, one end of the movable extension arm is fixedly connected to a lifting rail, and the top of the lifting rail is fixedly connected to a connecting frame, the side of the connecting frame facing downward is fixedly connected to a hydraulic cylinder 1, the output end of the hydraulic cylinder 1 is fixedly connected to a lifting slide rod, the lifting slide rod is slidably connected to the inside of the lifting rail, the top of the lifting slide rod is fixedly connected to a support rod, and the sleeve frame is fixedly connected to the bottom of the support rod.

[0017] In a preferred embodiment, both ends of the top of the base are fixedly connected with lifting rods, and the opposite sides of the two lifting rods are fixedly connected with shaft plates, one side of one shaft plate is fixedly connected with a driving motor 1, the output shaft of the driving motor 1 is fixedly connected with a pay-off roller through a coupling, one end of the pay-off roller is connected to one side of the other shaft plate through a bearing, a grounding wire is wrapped around the outer wall of the pay-off roller, one end of the grounding wire is connected to the tester body, and the other end of the grounding wire is connected to a grounding frame, one side of the shaft plate is fixedly connected with an annular limit rail, the inner sliding connection of the annular limit rail is connected with a follow-up slider, the outer wall of the follow-up slider is fixedly connected with a mounting sleeve, the grounding frame is placed inside the mounting sleeve, and the grounding wire passes through multiple pushing half frames and a single extension sleeve.

[0018] A 1000kV UHV UAV onboard electrical testing method, using the 1000kV UHV UAV onboard electrical testing device as described above, comprises the following steps:

[0019] Step 1: Start the drive motor 1, and drive the motor 1 to lay out the ground wire. At the same time, the drone body drives the electric test device to rise slowly. When the drone body drives the socket frame to move above the high-voltage wire, the staff removes the grounding frame from the installation sleeve and inserts it into the ground to complete the grounding of the ground wire.

[0020] Step 2: After the grounding is completed, the electric telescopic rod 1 is adjusted to drive the positioning pressure head to squeeze and position the grounding wire passing through the wire threading frame, and then the electric telescopic rod 2 is adjusted to drive each push half frame to push the grounding wire inside the mounting frame to make it present an S-shaped structure, thereby adjusting the grounding wire at the end of the electroscope body to make it in a tight state;

[0021] Step 3: After the above operations are completed, adjust the hydraulic cylinder 1 to drive the sleeve frame to move downward. During the downward movement, the deflection pressure plate contacts and squeezes the high-voltage wire, and the high-voltage wire is gradually pressed into the two metal conductive sheets. The high-voltage wire contacts the two metal conductive sheets, and then the air pump is started. The air pump blows gas into the reinforced airbag, and the reinforced airbag gradually expands. The reinforced airbag squeezes the deflection pressure plate and the adjustment plate to complete the reinforcement between the metal conductive sheet and the high-voltage wire. Then the tester body starts to work. After the test is completed, the solenoid valve opens, and the reinforced airbag gradually shrinks. The extrusion spring rod 2 drives the adjustment plate to reset, and the two blocking round rods are separated. At the same time, the reinforced airbag no longer squeezes the deflection pressure plate, and the hydraulic cylinder 1 can smoothly drive the sleeve frame to move out from the high-voltage wire, and the drone body drives the tester device to land.

[0022] From the above, it can be seen that the 1000kV ultra-high voltage UAV airborne electrical testing device provided by the present invention has the function of adjusting the electric telescopic rod one to drive the positioning pressure head to squeeze and position the grounding wire passing through the wire threading frame after the UAV moves the electrical tester body and the conductive wire clamp mechanism to the periphery of the high-voltage wire, and then adjusting the electric telescopic rod two to drive each pushing half frame to push the grounding wire located inside the mounting frame to make it present an S-shaped structure, thereby realizing the adjustment of the grounding wire at the end of the electrical tester body to make it in a taut state, avoiding the grounding wire in the sky due to the blowing of wind, causing the grounding wire located outside the electrical tester body to be in a large swing state, isolating the shaking of the grounding wire from the tension adjustment mechanism, avoiding its influence on the stability of the conductive wire clamp mechanism and the electrical tester body, thereby improving the technical effect of the stability of the electrical tester body during operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1This is a schematic diagram of the overall structure of a 1000kV ultra-high voltage UAV airborne electrical testing device proposed by the present invention.

[0024] Figure 2 This is a front view of the overall structure of a 1000kV ultra-high voltage UAV airborne electrical testing device proposed by the present invention.

[0025] Figure 3 This is a schematic diagram of the combined structure of a conductive wire clamp mechanism and a tension adjustment mechanism of a 1000kV ultra-high voltage UAV airborne electrical testing device proposed by the present invention.

[0026] Figure 4 for Figure 3 Local structure flip diagram of .

[0027] Figure 5 This is a schematic diagram of the tension adjustment mechanism of a 1000kV UHV UAV airborne electrical testing device proposed by the present invention.

[0028] Figure 6 for Figure 5 Schematic diagram of the plan structure.

[0029] Figure 7 This is a schematic diagram of a conductive wire clamp mechanism of a 1000kV UHV UAV airborne electrical testing device proposed by the present invention.

[0030] Figure 8 This is a schematic diagram of the internal structure of a socket frame of a 1000kV ultra-high voltage UAV airborne electrical testing device proposed by the present invention.

[0031] Fig. 9 This is an enlarged view of the combined structure of a deflection pressure plate and a reinforced airbag of a 1000kV ultra-high voltage UAV airborne electrical testing device proposed by the present invention.

[0032] Fig.10 This is a schematic diagram of the combined structure of a fixed extension arm and a movable extension arm of a 1000kV ultra-high voltage UAV airborne electrical testing device proposed by the present invention.

[0033] Fig.11 This is a schematic diagram of the impact reduction and reinforcement mechanism of a 1000kV ultra-high voltage UAV airborne electrical testing device proposed by the present invention.

[0034] Fig.12 This is a structural breakdown diagram of the docking turntable and mounting seat of a 1000kV UHV UAV airborne electrical testing device proposed by the present invention.

[0035] In the figure: 1, base; 2, lifting rod; 3, driving motor 1; 4, shaft plate; 5, drone body; 6, fixed extension arm; 7, impact reduction reinforcement mechanism; 701, movable extension arm; 702, semicircular guide rail; 703, connecting rod; 704, integration rod; 705, buffer spring rod 1; 706, shaft frame; 707, connecting shaft; 708, buffer spring rod 2; 709, sliding frame; 8, conductive wire clamp mechanism; 80 1. Sleeve frame; 802. Deflection pressure plate; 803. Air pump; 804. Pump ring frame; 805. Limiting frame; 806. Metal conductive sheet; 807. Reinforced airbag; 808. Air pipe; 809. Mounting groove; 810. Adjustment plate; 811. Extrusion spring rod 1; 812. Solenoid valve; 813. Exhaust pipe; 814. Docking hole; 815. Extrusion spring rod 2; 816. Back plate; 817. Blocking round rod; 9. Tension adjustment mechanism; 901. Mounting frame; 902. Extension sleeve; 903. Threading frame; 904. Push half frame; 905. Inner block; 906. Friction groove; 907. Extrusion rod; 908. Electric telescopic rod 1; 909. Fixing block; 910. Electric telescopic rod 2; 911. Positioning pressure head; 912. Shock-absorbing spring rod; 10. Lifting rail; 11. Support rod; 12. Electroscope body; 13. Grounding wire ; 14. Grounding frame; 15. Mounting sleeve; 16. Follow-up slider; 17. Annular limit rail; 18. Lifting slide bar; 19. Connecting frame; 20. Hydraulic cylinder one; 21. Sliding sleeve; 22. Docking rod; 23. Mounting column; 24. Pulling frame; 25. Pulling spring rod; 26. Hydraulic cylinder two; 27. Top plate; 28. Mounting seat; 29. ​​Lifting plate; 30. Positioning column; 31. Docking turntable; 32. Pay-off roller. DETAILED DESCRIPTION

[0036] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0037] A 1000kV ultra-high voltage UAV airborne electrical testing device disclosed in the present invention is mainly used in existing airborne electrical testing devices. During use, after the connecting wire clamp is connected to the high-altitude wire, since the grounding wire connected to the electrical tester is transported from the ground to the high altitude, it is in a loose state. If the grounding wire at the high-altitude electrical tester encounters strong winds, the swing amplitude is large, which greatly affects the connection stability between the connecting wire clamp and the wire, thereby affecting the accuracy of the electrical testing result.

[0038] Reference Figure 1-Figure 12A 1000kV UHV UAV airborne electrical testing device comprises a base 1, a UAV body 5 and a conductor clamp mechanism, wherein the conductor clamp mechanism 8 comprises a sleeve frame 801, and one side of the sleeve frame 801 is fixedly connected to two mounting columns 23, and one end of the two mounting columns 23 is provided with a same tension adjustment mechanism 9, the tension adjustment mechanism 9 comprises a mounting frame 901, and the mounting frame 901 is fixedly connected to one end of the two mounting columns 23, the inner side wall of the mounting frame 901 is fixedly connected to three inner blocks 905, and one side of the three inner blocks 905 is fixedly connected to an electric telescopic rod 2 910, and the output end of each electric telescopic rod 2 910 is fixedly connected to a push half frame 904, and the three push half frames 905 are fixedly connected to the inner side wall of the mounting frame 901. The frames 904 are staggered, and a plurality of groups of shock-absorbing spring rods 912 are fixedly connected to the inner arc surface of each pushing half frame 904, and the end of each group of shock-absorbing spring rods 912 is fixedly connected to an extrusion rod 907, and a friction groove 906 is provided on the outer wall of the extrusion rod 907 away from the pushing half frame 904. The inner walls on both sides of the mounting frame 901 near the bottom are fixedly connected to fixed blocks 909, and the opposite sides of the two fixed blocks 909 are fixedly connected to the same threading frame 903, and the outer wall of the threading frame 903 is fixedly connected to two electric telescopic rods 908, and the output ends of the two electric telescopic rods 908 are fixedly connected to positioning pressure heads 911, and the bottom of the threading frame 903 is fixedly connected to an extension sleeve 902.

[0039] In a specific application scenario, after the drone moves the electroscope body 12 and the conductive wire clamp mechanism 8 to the periphery of the high-voltage wire, the electric telescopic rod 1 908 is adjusted to drive the positioning pressure head 911 to squeeze and position the grounding wire 13 passing through the threading frame 903, and then the electric telescopic rod 2 910 is adjusted to drive each pushing half frame 904 to push the grounding wire 13 located inside the mounting frame 901, so that it presents an S-shaped structure, thereby adjusting the grounding wire 13 at the end of the electroscope body 12 to make it in a taut state, thereby preventing the grounding wire 13 in the air from being blown by the wind, causing the grounding wire 13 located outside the electroscope body 12 to be in a large swing state, and isolating the shaking of the grounding wire 13 from the tension adjustment mechanism 9 to prevent it from affecting the stability of the conductive wire clamp mechanism 8 and the electroscope body 12, thereby improving the stability of the electroscope body 12 during operation.

[0040] Specifically, after the tension adjustment mechanism 9 adjusts the grounding wire 13 near the electroscope body 12, the shock-absorbing spring rods 912 located inside each pushing half-frame 904 are in a compressed state, thereby weakening the wind impact on the tension adjustment mechanism 9 through the shock-absorbing spring rods 912 in the compressed state, thereby further improving the stability of the electroscope device.

[0041] Reference Figure 1-Figure 4In a preferred embodiment, a plurality of docking rods 22 are fixedly connected to the side of the sleeve frame 801 facing the mounting frame 901, and one end of the plurality of docking rods 22 is fixedly connected to the same sliding sleeve 21, the interior of the sliding sleeve 21 is slidingly connected to the electroscope body 12, and the outer wall of the sliding sleeve 21 is fixedly connected to the pulling frame 24 at equal distances, and each pulling frame 24 is fixedly connected to a pulling spring rod 25, and one end of the pulling spring rod 25 is fixedly connected to the outer wall of the electroscope body 12.

[0042] Reference Figure 1 , Figure 3 , Figure 7 , Figure 8 and Fig. 9 In a preferred embodiment, mounting grooves 809 are provided on the inner walls of both sides of the sleeve frame 801 near the bottom, and the interiors of the two mounting grooves 809 are connected to deflection pressure plates 802 through bearings, the tops of the two deflection pressure plates 802 are fixedly connected to metal conductive sheets 806, and the two deflection pressure plates 802 are fixedly connected to the sides of the inner wall of the sleeve frame 801 at equal distances, and one end of the extrusion spring rod 811 is fixedly connected to the inner wall of one side of the sleeve frame 801, and the metal probe of the electroscope body 12 is in contact with one of the metal conductive sheets 806, and the outer side walls of the two deflection pressure plates 802 near the metal conductive sheets 806 are provided with docking holes 814, and the bottom inner walls of the two docking holes 814 are connected to adjustment plates 810 through hinges, and the tops of the two adjustment plates 810 are fixedly connected to blocking round rods 817, and the opposite sides of the two deflection pressure plates 802 are fixedly connected to The rear abutment plate 816 is fixedly connected to the side of the rear abutment plate 816 facing the adjustment plate 810 with an extrusion spring rod 815 at an equal distance, and one end of the extrusion spring rod 815 is fixedly connected to the side of the adjacent adjustment plate 810. The inner side wall of the sleeve frame 801 close to the rear abutment plate 816 is fixedly connected to the limiting frame 805, and the inner part of the limiting frame 805 is fixedly connected to the reinforcing airbag 807, and the reinforcing airbag 807 is partially clamped to the rear abutment plate 816 and the adjustment plate 810. In between, both sides of the sleeve frame 801 are fixedly connected with pump ring frames 804, the insides of the two pump ring frames 804 are fixedly connected with air pumps 803, the air delivery end of the air pump 803 is fixedly connected with an air delivery pipe 808, one end of the air delivery pipe 808 is inserted into the interior of the reinforced air bag 807, an exhaust hole is opened on one side of the reinforced air bag 807, the inside of the exhaust hole is fixedly connected with an exhaust pipe 813, and the outer wall of the exhaust pipe 813 is connected to the solenoid valve 812 through a flange.

[0043] Specifically, after the drone body 5 moves the sleeve frame 801 above the high-voltage wire, the hydraulic cylinder 20 is adjusted to drive the sleeve frame 801 to move downward. During its downward movement, the deflection pressure plate 802 contacts and squeezes the high-voltage wire, and the high-voltage wire is gradually pressed into the two metal conductive sheets 806. The high-voltage wire contacts the two metal conductive sheets 806. Then the air pump 803 is started, and the air pump 803 blows gas into the reinforced airbag 807. The reinforced airbag 807 gradually expands, and the reinforced airbag 807 squeezes the deflection pressure plate 802, so that the interaction force between the metal conductive sheet 806 and the high-voltage wire gradually increases, thereby improving the stability of the connection between the metal conductive sheet 806 and the high-voltage wire. At the same time, the reinforced airbag 807 squeezes the adjustment plate 810, so that the two blocking round rods 817 contact each other, and the high-voltage wire located between the two metal conductive sheets 806 is blocked by the two blocking round rods 817, thereby reducing the probability of the high-voltage wire detaching from between the two metal conductive sheets 806 and improving the stability in the electrical testing operation.

[0044] It should be noted that when the electrical test operation is completed, the solenoid valve 812 is opened, and the reinforcement airbag 807 gradually shrinks, then the extrusion spring rod 815 drives the adjustment plate 810 to reset, and the two blocking round rods 817 are separated. At the same time, the reinforcement airbag 807 no longer squeezes the deflection pressure plate 802, and the hydraulic cylinder 20 can smoothly drive the sleeve frame 801 to be removed from the high-voltage wire, which is convenient for disassembly.

[0045] Reference Figure 1 , Fig.10 , Fig.11 and Fig.12 In a preferred embodiment, a mounting seat 28 is fixedly connected to the top of the drone body 5, and a top plate 27 is fixedly connected to the top of the mounting seat 28. Two hydraulic cylinders 26 are fixedly connected to the top of the top plate 27. The output ends of the two hydraulic cylinders 26 are fixedly connected to a lifting plate 29. The bottom of the lifting plate 29 is fixedly connected to a plurality of positioning columns 30. Two docking turntables 31 are sleeved on the top of the mounting seat 28. The positioning columns 30 are clamped in the positioning holes on the docking turntables 31. A fixed extension arm 6 is placed on the outside of the two docking turntables 31 of the mounting seat 28. The two docking turntables 31 are connected to the fixed extension arm 6 through bearings. The end of the fixed extension arm 6 away from the mounting seat 28 is provided with an impact reduction reinforcement mechanism 7.

[0046] Reference Fig.10 and Fig.11In a preferred embodiment, the impact reduction reinforcement mechanism 7 includes a semicircular guide rail 702 and a movable extension arm 701, and one end of the fixed extension arm 6 is fixedly connected to two connecting rods 703, the semicircular guide rail 702 is fixedly connected to the opposite sides of the two connecting rods 703, and the fixed extension arm 6 is fixedly connected to a shaft frame 706 on one side between the two connecting rods 703. The top inner wall and the bottom inner wall of the shaft frame 706 are connected to the same connecting shaft 707 through bearings, and the movable extension arm 701 is fixedly connected to the outer wall of the connecting shaft 707. The outer wall of the shaft 707 is fixedly connected with two groups of buffer spring rods 705, one end of each of the two groups of buffer spring rods 705 is fixedly connected with an integration rod 704, the integration rod 704 is fixedly connected to the outer wall of the fixed extension arm 6, the interior of the semicircular guide rail 702 is slidably connected with a sliding frame 709, the sliding frame 709 is provided with a through hole, the movable extension arm 701 passes through the through hole, both sides of the sliding frame 709 are fixedly connected with buffer spring rods 708, one end of each of the two buffer spring rods 708 is fixedly connected to the inner wall of the semicircular guide rail 702.

[0047] Specifically, when the electrical testing device is moved to the high-voltage wire through the drone body 5, since there is a certain distance between the drone body 5 and the high-voltage wire, the connecting arm between the two is longer and is subjected to a greater degree of wind impact. In the present invention, the connecting arm is divided into a fixed extension arm 6 and a movable extension arm 701. When the wind impacts the movable extension arm 701, the buffer spring rod 1 705 and the buffer spring rod 2 708 work in cooperation with each other to reduce the impact of the wind on the movable extension arm 701, thereby reducing the impact of the wind on the drone body 5, ensuring that the drone body 5 can drive the electrical testing device to stay stably in the air.

[0048] Reference Figure 1 and Figure 3 In a preferred embodiment, one end of the movable extension arm 701 is fixedly connected to the lifting rail 10, and the top of the lifting rail 10 is fixedly connected to the connecting frame 19, the side of the connecting frame 19 facing downward is fixedly connected to the hydraulic cylinder 20, the output end of the hydraulic cylinder 20 is fixedly connected to the lifting slide rod 18, the lifting slide rod 18 is slidably connected to the inside of the lifting rail 10, the top of the lifting slide rod 18 is fixedly connected to the support rod 11, and the sleeve frame 801 is fixedly connected to the bottom of the support rod 11.

[0049] Reference Figure 1 and Figure 2In a preferred embodiment, both ends of the top of the base 1 are fixedly connected with lifting rods 2, and the opposite sides of the two lifting rods 2 are fixedly connected with shaft plates 4, one side of one shaft plate 4 is fixedly connected with a driving motor 3, and the output shaft of the driving motor 3 is fixedly connected with a pay-off roller 32 through a coupling, one end of the pay-off roller 32 is connected to one side of the other shaft plate 4 through a bearing, and the outer wall of the pay-off roller 32 is wrapped with a grounding wire 13, one end of the grounding wire 13 is connected to the electroscope body 12, and the other end of the grounding wire 13 is connected to a grounding frame 14, one side of the shaft plate 4 is fixedly connected with an annular limit rail 17, the interior of the annular limit rail 17 is slidably connected with a follow-up slider 16, the outer wall of the follow-up slider 16 is fixedly connected with a mounting sleeve 15, the grounding frame 14 is placed inside the mounting sleeve 15, and the grounding wire 13 passes through multiple pushing half frames 904 and a single extension sleeve 902.

[0050] A kV UHV airborne electrical testing method, using a 1000kV UHV UAV airborne electrical testing device as described above, comprises the following steps:

[0051] Step 1: Start the driving motor 13, and the driving motor 13 releases the grounding wire 13. At the same time, the drone body 5 drives the electric testing device to rise slowly. When the drone body 5 drives the sleeve frame 801 to move above the high-voltage wire, the staff removes the grounding frame 14 from the installation sleeve 15 and inserts it into the ground to complete the grounding of the grounding wire 13;

[0052] Step 2: After the grounding is completed, the electric telescopic rod 1 908 is adjusted to drive the positioning pressure head 911 to squeeze and position the grounding wire 13 passing through the threading frame 903, and then the electric telescopic rod 2 910 is adjusted to drive each pushing half frame 904 to push the grounding wire 13 located inside the mounting frame 901 to make it present an S-shaped structure, thereby adjusting the grounding wire 13 at the end of the electroscope body 12 to make it in a tight state;

[0053] Step 3: After the above operation is completed, adjust the hydraulic cylinder 20 to drive the sleeve frame 801 to move downward. During the downward movement, the deflection pressure plate 802 contacts and squeezes the high-voltage wire, and the high-voltage wire is gradually pressed into the two metal conductive sheets 806. The high-voltage wire contacts the two metal conductive sheets 806, and then the air pump 803 is started. The air pump 803 blows gas into the reinforcement airbag 807, and the reinforcement airbag 807 gradually expands, and the reinforcement airbag 807 squeezes the deflection pressure plate 802 and the adjustment plate 810. , the reinforcement treatment between the metal conductive sheet 806 and the high-voltage wire is completed, and then the tester body 12 starts to work. After the test is completed, the solenoid valve 812 is opened, and the reinforcement airbag 807 is gradually reduced, and the squeezing spring rod 2 815 drives the adjustment plate 810 to reset, and the two blocking round rods 817 are separated. At the same time, the reinforcement airbag 807 no longer squeezes the deflection pressure plate 802, and the hydraulic cylinder 20 can smoothly drive the sleeve frame 801 to move out from the high-voltage wire, and the drone body 5 drives the tester to land.

[0054] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A 1000kV UHV UAV airborne electrical testing device, comprising a base (1), a UAV body (5) and a wire clamp mechanism, characterized in that: The conductive wire clamp mechanism (8) comprises a sleeve frame (801), and one side of the sleeve frame (801) is fixedly connected to two mounting columns (23), and one end of the two mounting columns (23) is provided with a same tension adjustment mechanism (9), and the tension adjustment mechanism (9) comprises a mounting frame (901), and the mounting frame (901) is fixedly connected to one end of the two mounting columns (23), and the inner side wall of the mounting frame (901) is fixedly connected to three inner blocks (905), and one side of the three inner blocks (905) is fixedly connected to an electric telescopic rod 2 (910), and the output end of each electric telescopic rod 2 (910) is fixedly connected to a push half frame (904), and the three push half frames (904) are staggered and distributed, and each of the push half frames (90 4), multiple groups of shock-absorbing spring rods (912) are fixedly connected to the inner arc surface, and the end of each group of shock-absorbing spring rods (912) is fixedly connected to an extrusion rod (907), and the outer wall of the extrusion rod (907) away from the pushing half frame (904) is provided with a friction groove (906), the inner walls of both sides of the mounting frame (901) close to the bottom are fixedly connected to fixed blocks (909), and the opposite sides of the two fixed blocks (909) are fixedly connected to the same threading frame (903), the outer wall of the threading frame (903) is fixedly connected to two electric telescopic rods (908), the output ends of the two electric telescopic rods (908) are fixedly connected to positioning pressure heads (911), and the bottom of the threading frame (903) is fixedly connected to an extension sleeve (902).

2. The 1000kV UHV UAV airborne electrical testing device according to claim 1 is characterized in that: A plurality of docking rods (22) are fixedly connected to one side of the sleeve frame (801) facing the mounting frame (901), and one end of each of the docking rods (22) is fixedly connected to the same sliding sleeve (21), the interior of the sliding sleeve (21) is slidingly connected to the electroscope body (12), and the outer wall of the sliding sleeve (21) is fixedly connected to a pulling frame (24) at an equal distance, and each pulling frame (24) is fixedly connected to a pulling spring rod (25), and one end of the pulling spring rod (25) is fixedly connected to the outer wall of the electroscope body (12).

3. The 1000kV UHV UAV airborne electrical testing device according to claim 2 is characterized in that: The inner walls of both sides of the sleeve frame (801) near the bottom are provided with mounting grooves (809), and the interiors of the two mounting grooves (809) are connected to deflection pressure plates (802) via bearings, and the tops of the two deflection pressure plates (802) are fixedly connected to metal conductive sheets (806), and the two deflection pressure plates (802) are fixedly connected to the sides of the inner wall of the sleeve frame (801) at equal distances, and one end of the extrusion spring rod (811) is fixedly connected to the inner wall of one side of the sleeve frame (801), and the metal probe of the electroscope body (12) is in contact with one of the metal conductive sheets (806).

4. The 1000kV UHV UAV airborne electrical testing device according to claim 3 is characterized in that: The outer side walls of the two deflection pressure plates (802) close to the metal conductive sheet (806) are both provided with docking holes (814), and the bottom inner walls of the two docking holes (814) are both connected to the adjustment plate (810) through hinges, and the tops of the two adjustment plates (810) are both fixedly connected to the blocking round rod (817), and the opposite sides of the two deflection pressure plates (802) are both fixedly connected to the rear abutment plate (816), and the side of the rear abutment plate (816) facing the adjustment plate (810) is fixedly connected to the second extrusion spring rod (815) at an equal distance, and one end of the second extrusion spring rod (815) is fixedly connected to one side of the adjacent adjustment plate (810).

5. The 1000kV UHV UAV airborne electrical testing device according to claim 4 is characterized in that: The sleeve frame (801) is fixedly connected to a limiting frame (805) on the inner side wall close to the rear support plate (816), and a reinforcing airbag (807) is fixedly connected inside the limiting frame (805). The reinforcing airbag (807) is partially clamped between the rear support plate (816) and the adjustment plate (810). Pump ring frames (804) are fixedly connected to both sides of the sleeve frame (801). The insides of the two pump ring frames (804) are fixedly connected to air pumps (803). The air delivery end of the air pump (803) is fixedly connected to an air delivery pipe (808). One end of the air delivery pipe (808) is inserted into the inside of the reinforcing airbag (807). An exhaust hole is opened on one side of the reinforcing airbag (807). An exhaust pipe (813) is fixedly connected inside the exhaust hole. The outer wall of the exhaust pipe (813) is connected to a solenoid valve (812) via a flange.

6. The 1000kV UHV UAV airborne electrical testing device according to claim 5 is characterized in that: The top of the drone body (5) is fixedly connected to a mounting seat (28), and the top of the mounting seat (28) is fixedly connected to a top plate (27). The top of the top plate (27) is fixedly connected to two hydraulic cylinders (26). The output ends of the two hydraulic cylinders (26) are fixedly connected to a lifting plate (29). The bottom of the lifting plate (29) is fixedly connected to a plurality of positioning columns (30). The top of the mounting seat (28) is sleeved with two docking turntables (31). The positioning columns (30) are clamped in positioning holes on the docking turntables (31). A fixed extension arm (6) is placed on the outside of the two docking turntables (31) on the mounting seat (28). The two docking turntables (31) are connected to the fixed extension arm (6) through bearings. An impact reduction reinforcement mechanism (7) is provided at one end of the fixed extension arm (6) away from the mounting seat (28).

7. The 1000kV UHV UAV airborne electrical testing device according to claim 6 is characterized in that: The impact reduction reinforcement mechanism (7) comprises a semicircular guide rail (702) and a movable extension arm (701), and one end of the fixed extension arm (6) is fixedly connected to two connecting rods (703), the semicircular guide rail (702) is fixedly connected to the opposite sides of the two connecting rods (703), a side of the fixed extension arm (6) located between the two connecting rods (703) is fixedly connected to an axle frame (706), the top inner wall and the bottom inner wall of the axle frame (706) are connected to the same connecting shaft (707) via bearings, the movable extension arm (701) is fixedly connected to the outer side wall of the connecting shaft (707), and the connecting shaft (707) is fixedly connected to the outer side wall of the connecting shaft (707). ) are fixedly connected to the outer wall of the semicircular guide rail (702), one end of each of the two groups of buffer spring rods (705) is fixedly connected to an integration rod (704), the integration rod (704) is fixedly connected to the outer wall of the fixed extension arm (6), the interior of the semicircular guide rail (702) is slidably connected to a sliding frame (709), a through hole is opened on the sliding frame (709), and the movable extension arm (701) passes through the through hole, and both sides of the sliding frame (709) are fixedly connected to buffer spring rods (708), one end of each of the two buffer spring rods (708) is fixedly connected to the inner wall of the semicircular guide rail (702).

8. The 1000kV UHV UAV airborne electrical testing device according to claim 7 is characterized in that: One end of the movable extension arm (701) is fixedly connected to a lifting rail (10), and the top of the lifting rail (10) is fixedly connected to a connecting frame (19), a side of the connecting frame (19) facing downward is fixedly connected to a hydraulic cylinder (20), an output end of the hydraulic cylinder (20) is fixedly connected to a lifting slide bar (18), the lifting slide bar (18) is slidably connected to the inside of the lifting rail (10), the top of the lifting slide bar (18) is fixedly connected to a support rod (11), and the sleeve frame (801) is fixedly connected to the bottom of the support rod (11).

9. The 1000kV UHV UAV airborne electrical testing device according to claim 8 is characterized in that: Both ends of the top of the base (1) are fixedly connected to lifting rods (2), and opposite sides of the two lifting rods (2) are fixedly connected to shaft plates (4), one side of one shaft plate (4) is fixedly connected to a driving motor (3), the output shaft of the driving motor (3) is fixedly connected to a pay-off roller (32) via a coupling, one end of the pay-off roller (32) is connected to one side of the other shaft plate (4) via a bearing, the outer side wall of the pay-off roller (32) is wound with a grounding wire (13), one end of the grounding wire (13) is connected to the outer side wall of the pay-off roller (32), and one end of the grounding wire (13) is connected to the outer side wall of the pay-off roller (32). The device is connected to the electroscope body (12), the other end of the grounding wire (13) is connected to the grounding frame (14), one side of the shaft plate (4) is fixedly connected to an annular limit rail (17), the interior of the annular limit rail (17) is slidably connected to a follow-up slider (16), the outer side wall of the follow-up slider (16) is fixedly connected to a mounting sleeve (15), the grounding frame (14) is placed inside the mounting sleeve (15), and the grounding wire (13) passes through a plurality of push half frames (904) and a single extension sleeve (902).

10. A 1000kV UHV UAV onboard electrical testing method, using the 1000kV UHV UAV onboard electrical testing device as claimed in claim 9, characterized in that: The following steps are involved: Step 1: Start the driving motor 1 (3), the driving motor 1 (3) performs wire laying processing on the grounding wire (13), and at the same time, the drone body (5) drives the electric testing device to slowly rise, and when the drone body (5) drives the sleeve frame (801) to move above the high-voltage wire, the staff removes the grounding frame (14) from the installation sleeve (15) and inserts it into the ground, completing the grounding processing of the grounding wire (13); Step 2: After the grounding is completed, the electric telescopic rod 1 (908) is adjusted to drive the positioning pressure head (911) to squeeze and position the grounding wire (13) passing through the threading frame (903), and then the electric telescopic rod 2 (910) is adjusted to drive each pushing half frame (904) to push the grounding wire (13) located inside the mounting frame (901) to form an S-shaped structure, thereby adjusting the grounding wire (13) at the end of the electroscope body (12) to put it in a tight state; Step 3: After the above operation is completed, the hydraulic cylinder 1 (20) is adjusted to drive the sleeve frame (801) to move downward. During the downward movement, the deflection pressure plate (802) contacts and squeezes the high-voltage wire, and the high-voltage wire is gradually pressed into the two metal conductive sheets (806). The high-voltage wire contacts the two metal conductive sheets (806). Then, the air pump (803) is started, and the air pump (803) blows gas into the reinforcement airbag (807). The reinforcement airbag (807) gradually expands, and the reinforcement airbag (807) squeezes the deflection pressure plate (802) and the adjustment plate (810). , the reinforcement treatment between the metal conductive sheet (806) and the high-voltage wire is completed, and then the tester body (12) starts to work. After the test is completed, the solenoid valve (812) is opened, and the reinforcement airbag (807) is gradually reduced, and the second squeezing spring rod (815) drives the adjustment plate (810) to reset, and the two blocking round rods (817) are separated. At the same time, the reinforcement airbag (807) no longer squeezes the deflection pressure plate (802), and the hydraulic cylinder (20) can smoothly drive the sleeve frame (801) to move out from the high-voltage wire, and the drone body (5) drives the tester to land.

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