1000kv ultra-high voltage unmanned aerial vehicle airborne electricity testing device and method

Abstract

The application discloses a 1000kV ultra-high voltage unmanned aerial vehicle airborne electricity testing device and method, and relates to the technical field of electricity testing devices, which comprises a base, an unmanned aerial vehicle body and a conductive wire clamp mechanism, wherein the conductive wire clamp mechanism comprises a sleeve joint frame. The 1000kV ultra-high voltage unmanned aerial vehicle airborne electricity testing device and method has the advantages that after the electricity tester body and the conductive wire clamp mechanism are moved to the periphery of a high-voltage wire by the unmanned aerial vehicle, the first electric telescopic rod drives the positioning pressure head to extrude and position the grounding wire passing through the wire passing frame, then the second electric telescopic rod drives each pushing half frame to push the grounding wire located in the mounting frame, so that the grounding wire presents an S-shaped structure, the grounding wire in the air is prevented from swinging greatly due to the blowing of wind, the swinging of the grounding wire is blocked from the tension adjusting mechanism, and the stability of the conductive wire clamp mechanism and the electricity tester body is prevented from being affected.

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 (UAV) onboard electrical testing device and method. Background Art

[0002] When conducting 1000kV ultra-high voltage electrical testing, in order to avoid safety accidents caused by manual contact, under normal circumstances, a drone 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 using the existing airborne electrical test device, after the connecting wire clamp is connected to the high-altitude wire, the grounding wire connected to the electroscope is transported from the ground to the high altitude and is in a loose state. If the grounding wire at the electroscope in the high altitude encounters strong winds, it will swing greatly, which will greatly affect the connection stability between the connecting wire clamp and the wire, thereby affecting the accuracy of the electrical test results and reducing the use value of the airborne electrical test device. Summary of the Invention

[0004] The present invention discloses an airborne electrical test device for a 1000kV ultra-high voltage unmanned aerial vehicle (UAV). The device aims to solve the technical problem that, in the use of existing airborne electrical test devices, after the connection between the wire clamp and the high-altitude conductor is completed, the grounding wire connected to the electroscope is transported from the ground to the high altitude and is in a loose state. If the grounding wire at the electroscope in the high altitude encounters strong winds, the swing amplitude of the grounding wire is large, thereby greatly affecting the connection stability between the wire clamp and the conductor, and further affecting the accuracy of the electrical test results.

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

[0006] A 1000kV UHV UAV airborne electrical test 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, and 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 each 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-actuated push rod. The frame has three pushing half frames in a staggered distribution, and multiple 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 with fixed blocks, and the opposite sides of the two fixed blocks are fixedly connected to the same threading frame, the outer wall of the threading frame is fixedly connected to two electric telescopic rods, the output ends of the two electric telescopic rods are fixedly connected with positioning pressure heads, and the bottom of the threading frame is fixedly connected with an extension pipe 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 wire 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, so that it presents an S-shaped structure, thereby adjusting the grounding wire at the end of the electroscope body to keep it in a taut state, preventing the grounding wire at high altitude from being blown by wind, 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 wall of the sliding sleeve is fixedly connected to the 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 wall of the electroscope body.

[0009] In a preferred solution, mounting grooves are provided on both inner walls of the sleeve frame near the bottom end, 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 facing the inner wall of the sleeve frame, one end of the extrusion spring rod 1 is fixedly connected to one inner wall 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 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, and 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 an extrusion spring rod two at an equal distance, and one end of the extrusion spring rod two 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 near the inner wall of the rear support plate, and the interior of the limiting frame is fixedly connected to a reinforced airbag, and 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, and the interiors of the two pump ring frames are fixedly connected to air pumps, and 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, and an exhaust hole is opened on one side of the reinforced airbag, and 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, the top of the UAV body is fixedly connected to a mounting seat, and the top of the mounting seat is fixedly connected to a top plate, the top of the top plate is fixedly connected to two hydraulic cylinders 2, 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, the top of the mounting seat is sleeved with two docking turntables, the positioning columns are clamped in the positioning holes on the docking turntables, the mounting seat is located on the outside of the two docking turntables and a fixed extension arm is placed, the two docking turntables are connected to the fixed extension arm through bearings, and the fixed extension arm is provided with an impact reduction reinforcement mechanism at the end away from the mounting seat.

[0014] By setting the impact reinforcing mechanism, when the electricity tester is moved to the high-voltage wire by the unmanned aerial vehicle body, the connecting arm between the unmanned aerial vehicle body and the high-voltage wire is long and is impacted by wind to a large extent, the fixed extension arm and the movable extension arm are provided in the application, when the movable extension arm is impacted by wind, the buffer spring rod one and the buffer spring rod two work together to reduce the impact of wind on the movable extension arm, thereby reducing the impact of wind on the unmanned aerial vehicle body, and ensuring that the unmanned aerial vehicle body can stably stay in the high altitude with the electricity tester.

[0015] In a preferred scheme, the impact reinforcing mechanism comprises a semicircular guide rail and a movable extension arm, one end of the fixed extension arm is fixedly connected with two connecting rods, the semicircular guide rail is fixedly connected with the opposite side of the two connecting rods, one side of the fixed extension arm between the two connecting rods is fixedly connected with an axle bracket, the top inner wall and the bottom inner wall of the axle bracket are connected with the same connecting shaft through bearings, the movable extension arm is fixedly connected with the outer side wall of the connecting shaft, the outer side wall of the connecting shaft is fixedly connected with two groups of buffer spring rods one, one end of each of the two groups of buffer spring rods one is fixedly connected with an integrated rod, the integrated rod is fixedly connected with the outer side wall of the fixed extension arm, the semicircular guide rail is slidably connected with a sliding bracket, the sliding bracket is provided with a through hole, the movable extension arm passes through the through hole, and the two sides of the sliding bracket are fixedly connected with buffer spring rods two, one end of each of the two buffer spring rods two is fixedly connected with the inner side wall of the semicircular guide rail.

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

[0017] In a preferred scheme, the top of the base is fixedly connected with lifting rods at both ends, and the opposite sides of the two lifting rods are fixedly connected with shaft plates, one side of one of the shaft plates is fixedly connected with a drive motor one, the output shaft of the drive motor one is fixedly connected with a pay-off roller through a shaft coupling, one end of the pay-off roller is connected with one side of the other shaft plate through a bearing, the outer side wall of the pay-off roller is wound with a grounding wire, one end of the grounding wire is connected with the electricity tester body, the other end of the grounding wire is connected with a grounding bracket, one side of the shaft plate is fixedly connected with an annular limiting rail, the inside of the annular limiting rail is slidably connected with a follow-up sliding block, the outer side wall of the follow-up sliding block is fixedly connected with a mounting sleeve, the grounding bracket is placed in the inside of the mounting sleeve, and the grounding wire passes through a plurality of pushing half frames and a single extension pipe 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 drive motor 1, drive motor 1 to lay out the ground wire. At the same time, the drone body drives the electrical testing device to slowly rise. 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, adjust the electric telescopic rod 1 to drive the positioning pressure head to squeeze and position the grounding wire passing through the wire frame. Then adjust the electric telescopic rod 2 to drive each pushing half frame to push the grounding wire inside the mounting frame to form an S-shaped structure, thereby adjusting the grounding wire at the end of the electroscope body to keep it in a taut state.

[0021] Step 3: After the above operations are completed, adjust the hydraulic cylinder 1 to drive the socket 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 electrometer body starts to work. After the electrical test is completed, the solenoid valve opens, and the reinforced airbag gradually shrinks. The squeezing spring rod 2 drives the adjustment plate to reset, and the two blocking round rods separate. At the same time, the reinforced airbag no longer squeezes the deflection pressure plate, and the hydraulic cylinder 1 can smoothly drive the socket frame to move out from the high-voltage wire, and the drone body drives the electrical test device to the ground.

[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 electroscope 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, so that it presents an S-shaped structure, thereby realizing the adjustment of the grounding wire at the end of the electroscope body to keep it in a taut state, avoiding the grounding wire in the air from being blown by the wind, causing the grounding wire located outside the electroscope 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 electroscope body, thereby improving the technical effect of the stability of the electroscope 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 The local structure flip diagram of .

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

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

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

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

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

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

[0033] Figure 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] Figure 12 This is a disassembled diagram of the docking turntable and mounting seat structure of a 1000kV ultra-high voltage UAV airborne electrical testing device proposed in the present invention.

[0035] 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 bracket; 707, connecting shaft; 708, buffer spring rod 2; 709, sliding frame; 8, conductive wire clamp mechanism; 80 1. Socket 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 slot; 810. Adjustment plate; 811. Extrusion spring rod 1; 812. Solenoid valve; 813. Exhaust pipe; 814. Docking hole; 815. Extrusion spring rod 2; 816. Rear support plate; 817. Blocking rod; 9. Tension adjustment mechanism; 901. Mounting frame; 902. Extension sleeve; 903. Threading frame; 904. Push half frame; 905. Internal sticking 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; 19. Connecting frame; 20. Hydraulic cylinder 1; 21. Sliding sleeve; 22. Docking rod; 23. Mounting column; 24. Pulling frame; 25. Pulling spring rod; 26. Hydraulic cylinder 2; 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 clearly and completely described 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] The 1000kV ultra-high voltage unmanned aerial vehicle airborne electrical test device disclosed in the present invention is mainly applicable to existing airborne electrical test devices. During use, after the connecting wire clamp is connected to the high-altitude wire, since the grounding wire connected to the electroscope is transported from the ground to the high altitude, it is in a loose state. If the grounding wire at the electroscope in the high altitude 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 results.

[0038] Reference Figures 1-12A 1000kV UHV UAV airborne electrical testing device includes a base 1, a UAV body 5, and a conductor clamp mechanism. The conductive wire clamp mechanism 8 includes a socket frame 801, and one side of the socket frame 801 is fixedly connected to two mounting posts 23, and one end of the two mounting posts 23 is provided with a same tension adjustment mechanism 9. The tension adjustment mechanism 9 includes a mounting frame 901, and the mounting frame 901 is fixedly connected to one end of the two mounting posts 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. The output end of each electric telescopic rod 2 910 is fixedly connected to a push half frame 904. 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 multiple 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. The extrusion rod 907 is provided with a friction groove 906 on the outer wall 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. 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. 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 wire 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 all 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, 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 slidably 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 Figure 9 In a preferred embodiment, mounting grooves 809 are provided on both sides of the inner wall of the sleeve frame 801 near the bottom end, and the interiors of the two mounting grooves 809 are connected to the deflection pressure plates 802 through bearings, and the tops of the two deflection pressure plates 802 are fixedly connected to the 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. An extrusion spring rod 811 is fixedly connected, 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 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 the adjustment plates 810 through hinges, and the tops of the two adjustment plates 810 are fixedly connected to the blocking round rod 817, and the opposite sides of the two deflection pressure plates 802 are fixedly connected. The rear support plate 816 is fixedly connected to the side of the rear support plate 816 facing the adjustment plate 810 with an extrusion spring rod 815 at an equal distance. 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 support plate 816 is fixedly connected to the limiting frame 805, and the interior of the limiting frame 805 is fixedly connected to the reinforcement airbag 807. The reinforcement airbag 807 is partially clamped to the rear support plate 816 and the adjustment plate 810. In between, both sides of the sleeve frame 801 are fixedly connected with pump ring frames 804, and the insides of the two pump ring frames 804 are fixedly connected with air pumps 803. The gas delivery end of the air pump 803 is fixedly connected with a gas delivery pipe 808. One end of the gas delivery pipe 808 is inserted into the interior of the reinforced airbag 807. An exhaust hole is opened on one side of the reinforced airbag 807. The inside of the exhaust hole is fixedly connected with an exhaust pipe 813. 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 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 interior of 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 during the electrical testing operation.

[0044] It should be noted that when the electrical test operation is completed, the solenoid valve 812 is opened, the reinforcement airbag 807 gradually shrinks, and the extrusion 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 1 20 can smoothly drive the socket frame 801 to be removed from the high-voltage wire, which is easy to disassemble.

[0045] Reference Figure 1 、 Figure 10 、 Figure 11 and Figure 12 In a preferred embodiment, 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 snapped into 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 a shock reducing reinforcement mechanism 7.

[0046] Reference Figure 10 and Figure 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 side of the fixed extension arm 6 located between the two connecting rods 703 is fixedly connected to a shaft frame 706, and 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, connecting The outer wall of the shaft 707 is fixedly connected with two groups of buffer spring rods 705, and one end 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 has a through hole, and 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, and one end 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 subject 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 cooperate 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 downward side of the connecting frame 19 is fixedly connected to the hydraulic cylinder 20, and 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 to a lifting rod 2, and the opposite sides of the two lifting rods 2 are fixedly connected to an axis plate 4, one side of one axis plate 4 is fixedly connected to a driving motor 3, and the output shaft of the driving motor 3 is fixedly connected to a pay-off roller 32 through a coupling, one end of the pay-off roller 32 is connected to one side of the other axis plate 4 through a bearing, and a grounding wire 13 is wrapped around the outer wall of the pay-off roller 32, 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, and an annular limit rail 17 is fixedly connected to the inner sliding connection of the annular limit rail 17, and the outer wall of the follow-up slider 16 is fixedly connected to the mounting sleeve 15, and 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 tube sleeve 902.

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

[0051] Step 1: Start the drive motor 13, which is used to lay out the ground wire 13. At the same time, the drone body 5 drives the electrical testing device to slowly rise. When the drone body 5 drives the socket frame 801 to move above the high-voltage wire, the staff removes the grounding frame 14 from the mounting sleeve 15 and inserts it into the ground to complete the grounding of the ground wire 13.

[0052] Step 2: After grounding is completed, the first electric telescopic rod 908 is adjusted to drive the positioning pressure head 911 to squeeze and position the grounding wire 13 passing through the wire threading frame 903. Then, the second electric telescopic rod 910 is adjusted to drive each pushing half frame 904 to push the grounding wire 13 inside the mounting frame 901, so that it forms an S-shaped structure, thereby adjusting the grounding wire 13 at the end of the electroscope body 12 to keep it in a taut 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 electroscope body 12 starts to work. After the test is completed, the solenoid valve 812 is opened, and the reinforcement airbag 807 gradually shrinks, then 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 electroscope device to the ground.

[0054] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A 1000kV UHV UAV onboard electrical testing device, comprising a base (1), a UAV body (5) and a conductive wire clamp mechanism (8), characterized in that: The conductive wire clamp mechanism (8) includes a sleeve frame (801), and one side of the sleeve frame (801) is fixedly connected to two mounting posts (23), and one end of the two mounting posts (23) is provided with a same tension adjustment mechanism (9), the tension adjustment mechanism (9) includes a mounting frame (901), and the mounting frame (901) is fixedly connected to one end of the two mounting posts (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), the three push half frames (904) are staggered, and each push half frame (90 4) are fixedly connected to the inner arc surface thereof, and the end of each group of shock-absorbing spring rods (912) is fixedly connected to an extrusion rod (907), and the extrusion rod (907) is provided with a friction groove (906) on the outer wall away from the pushing half frame (904). 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 pipe sleeve (902).

2. The 1000kV UHV UAV airborne electrical testing device according to claim 1 is characterized in that: The sleeve frame (801) is fixedly connected to a plurality of docking rods (22) on one side facing the mounting frame (901), and one end of each of the plurality of docking rods (22) is fixedly connected to a 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 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).

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) through 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 support plate (816), and the side of the rear support 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 near the rear support plate (816), and the interior of the limiting frame (805) is fixedly connected to a reinforcement airbag (807), and the reinforcement airbag (807) is partially clamped between the rear support plate (816) and the adjustment plate (810). Both sides of the sleeve frame (801) are fixedly connected to pump ring frames (804), and the interiors 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), and one end of the air delivery pipe (808) is inserted into the interior of the reinforcement airbag (807). An exhaust hole is opened on one side of the reinforcement airbag (807), and the interior of the exhaust hole is fixedly connected to an exhaust pipe (813), and the outer wall of the exhaust pipe (813) is connected to a solenoid valve (812) through a flange.

6. The 1000kV UHV UAV airborne electrical testing device according to claim 5, characterized in that: The top of the UAV 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 the positioning holes on the docking turntables (31), the mounting seat (28) is located outside the two docking turntables (31) and a fixed extension arm (6) is placed, the two docking turntables (31) are connected to the fixed extension arm (6) through bearings, and the end of the fixed extension arm (6) away from the mounting seat (28) is provided with a shock-reducing reinforcement mechanism (7).

7. The 1000kV UHV UAV airborne electrical testing device according to claim 6, characterized in that: 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 located 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 a bearing, and the movable extension arm (701) is fixedly connected to the outer wall of the connecting shaft (707). The connecting shaft (707) ) is fixedly connected to the outer wall of the semicircular guide rail (702) with two groups of buffer spring rods (705), 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), 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, characterized in that: 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 (18), the lifting slide (18) is slidably connected to the inside of the lifting rail (10), the top of the lifting slide (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).

9. The 1000kV UHV UAV airborne electrical testing device according to claim 8, 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) 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, the outer side wall of the pay-off roller (32) is wound with a grounding wire (13), 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 the annular limit rail (17), the inner portion of the annular limit rail (17) is slidably connected to the follower slider (16), the outer side wall of the follower slider (16) is fixedly connected to the mounting sleeve (15), the grounding frame (14) is placed inside the mounting sleeve (15), and the grounding wire (13) passes through multiple push half frames (904) and a single extension tube sleeve (902).

10. A 1000kV UHV UAV onboard electrical testing method, using the 1000kV UHV UAV onboard electrical testing device according to claim 9, characterized in that: The following steps are involved: Step 1: Start the driving motor 1 (3), and the driving motor 1 (3) performs a wire laying process on the grounding wire (13). At the same time, the drone body (5) drives the electric test device to slowly rise. When the drone body (5) drives the socket 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 process 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 achieving the adjustment of 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, adjust the hydraulic cylinder 1 (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). Then start the air pump (803). The air pump (803) blows gas into the interior of 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 electroscope 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 spring rod (815) is squeezed to drive 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 electroscope device to the ground.

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