Carrying unmanned aerial vehicle

Abstract

The invention relates to a carrying unmanned aerial vehicle which comprises an unmanned aerial vehicle body and a carrying mechanism, the carrying mechanism is installed at the bottom of the unmanned aerial vehicle body, the carrying mechanism is used for carrying parts for stringing of a power plant, the carrying mechanism comprises a clamping mechanism and a locking component, and the carrying mechanism clamps the parts for stringing of the power plant through the clamping mechanism. The clamping mechanism and the unmanned aerial vehicle platform are constructed into a tuned mass damping system in non-rigid connection through the elastic connecting piece, swing opposite to the motion phase of the unmanned aerial vehicle is generated through inertia of the insulator, and therefore direct impact of airflow on a vehicle body is passively counteracted, high-frequency jitter of the unmanned aerial vehicle is remarkably reduced, and the stability of the unmanned aerial vehicle is improved. And the flight stability under a complex meteorological condition is improved.

Description

A type of transport drone Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicles (UAVs), specifically a type of transport UAV. Background Technology

[0002] In power engineering construction, the erection of high-voltage transmission lines often requires crossing complex terrains such as mountains, valleys, rivers, or dense forests. As a key component of transmission lines, insulator strings are heavy and fragile, and their high-altitude transportation and precise installation have always been challenges in construction.

[0003] Currently, using drones to transport insulators for overhead power line operations is becoming increasingly common. However, existing drone transport technologies still have the following significant drawbacks: Traditional drones and cargo are often directly connected via rigid hooks or short ropes. When a drone encounters strong airflow, gusts, or needs to maneuver quickly to avoid obstacles (such as trees or tower materials) at high altitudes, the impact force of the airflow is directly transmitted to the drone's fuselage, causing severe shaking or even loss of control. Existing solutions mostly rely on flight control algorithms for attitude correction, which is a "post-event remedy" and cannot passively eliminate the mechanical vibrations caused by airflow from the physical structure. To maintain stability, the flight control system must frequently adjust the motor speed, which not only greatly increases energy consumption and shortens flight time but may also cause the cargo to be damaged by collisions due to severe shaking. Therefore, a new type of drone for transport is proposed. Summary of the Invention

[0004] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the invention.

[0005] Given the following technical problems in the existing technology: existing solutions mostly rely on flight control algorithms for attitude correction, which cannot passively eliminate mechanical vibrations caused by airflow from the physical structure. In order to maintain stability, the flight control system must adjust the motor speed at high frequency, which not only greatly increases energy consumption and shortens the flight time, but may also cause the cargo to be damaged by collision due to violent swinging.

[0006] To address the aforementioned technical problems, this invention provides the following technical solution: a transport drone, comprising a drone and a transport mechanism. The transport mechanism is mounted on the bottom of the drone and is used to transport components for power plant overhead line installation. The transport mechanism includes a clamping mechanism and a locking component. The transport mechanism clamps the power plant overhead line components using the clamping mechanism, and then uses the drone's flight capability to transport the clamping mechanism and the clamped components to the required location. Afterward, the clamping mechanism releases the components for installation. The clamping mechanism is equipped with a locking component, which locks or releases the clamping state of the clamping mechanism to achieve stable clamping or release of the power plant overhead line components. Through integrated clamping and locking design, the entire process from ground grabbing and stable aerial transport to precise high-altitude release is automated, significantly improving the efficiency and safety of power line installation.

[0007] As a preferred technical solution for transporting unmanned aerial vehicles, the transport mechanism also includes intermediate auxiliary components, which include a structural plate and structural side plates. A structural side plate is provided on each side of the structural plate, and the structural plate and structural side plates are perpendicular to each other. A clamping mechanism is connected to the structural side plates. The structural plate and structural side plates are both made of magnetically conductive metal.

[0008] As a preferred technical solution for transporting unmanned aerial vehicles (UAVs), the clamping mechanism includes a clamping component, which comprises an elastic connector, a jaw component, and a clamping arm. The clamping arm is connected to the structural side plate via the elastic connector, and is rotatably connected and movably sleeved with the elastic connector. The clamping arm is formed by connecting two structural beams, with the included angle between the two structural beams between 120 and 150 degrees. Two clamping arms are provided on each structural side plate. The jaw component connects the two clamping arms located on different structural side plates and symmetrically arranged about the structural plate, thus forming two jaw components. The UAV is used to transport components for power plant overhead lines, including insulators. The two jaw components cooperate to clamp the insulators. The jaw components can adapt to the cylindrical shape of the insulators.

[0009] As a preferred technical solution for transporting unmanned aerial vehicles (UAVs), each clamping component includes a swinging metal plate and a clamping block. Clamping arms are located at both ends of the swinging metal plate, and a clamping block is provided in the middle of each swinging metal plate. Large clamping openings are recessed on the opposite surfaces of the two clamping blocks. By connecting the clamping arms on both sides with the swinging metal plate and providing the large recessed clamping openings, uniform distribution of clamping force and self-centering function are achieved, ensuring that the insulator will not be skewed or damaged due to local stress concentration during the clamping process.

[0010] As a preferred technical solution for transporting unmanned aerial vehicles (UAVs), an elastic friction layer is provided on the arc surface of the clamping port of the clamping block, and friction texture is provided on the outer side of the elastic friction layer. Through the textured elastic friction layer, the friction coefficient of the contact interface is significantly improved, effectively preventing the insulator from axially slipping or rotating and falling off under strong wind, turbulence, or sudden stop conditions.

[0011] As a preferred technical solution for transporting unmanned aerial vehicles (UAVs), each clamping block is equipped with a gravity locking component. Two gravity locking components cooperate with each other. Each gravity locking component includes a clamping base frame, a compression plate, and an arc-shaped clamping plate. An arc-shaped movable groove is formed through the clamping block and is inclined. A compression plate is located at the top of the arc-shaped clamping plate, parallel to the upper side of the clamping block. A clamping base frame is located at the bottom of the arc-shaped clamping plate and is inclined. A small clamping opening is located at the end of the clamping base frame away from the arc-shaped clamping plate. Under the action of gravity, the insulator squeezes the compression plate, causing the clamping base frames to move closer together and clamp the insulator. Utilizing the weight of the cargo itself to drive the clamping base frame to tighten achieves a passive self-locking effect of "the heavier the load, the tighter the clamping," solving the problem of clamping force attenuation caused by vibration. When the clamping force of the clamping blocks decreases, the insulator tends to descend, thus applying a stronger compressive force to the compression plate, making the insulator clamped more tightly and securely.

[0012] As a preferred technical solution for transporting unmanned aerial vehicles (UAVs), the elastic connector includes a connecting bolt and thrust bearings. The connecting bolt is fixedly connected to the structural side plate. Each connecting bolt is fitted with two clamping arms and three thrust bearings. The two clamping arms separate the three thrust bearings, which are movably engaged with the connecting bolt. A spring is fitted at both ends of the connecting bolt, and the spring abuts against the corresponding thrust bearing. An axial buffer system is constructed through the combination of springs and thrust bearings.

[0013] As a preferred technical solution for transporting unmanned aerial vehicles, the insulator includes skirts, fittings and pull rods. Several skirts are spaced apart on the pull rods, and each skirt has a fitting at its top.

[0014] As a preferred technical solution for transporting unmanned aerial vehicles (UAVs), the locking component includes a limiting component and a gravity locking component. The gravity locking component is movably sleeved on the limiting component. The limiting component includes a locking arm, a locking frame, a locking groove, and a sliding component. Each clamping arm is equipped with a locking arm, and a sliding component is rotatably connected to the end of the locking arm away from the clamping arm. The locking frame has a locking groove, and a sliding component is slidably connected to each end of the locking groove. The limiting component restricts the opening angle of the clamping mechanism. By limiting the stroke of the sliding component within the locking groove, a rigid constraint is achieved on the maximum opening angle of the clamping arm, preventing structural interference or accidental damage caused by excessive opening of the clamping mechanism in the non-working state.

[0015] As a preferred technical solution for transporting unmanned aerial vehicles (UAVs), the gravity locking mechanism includes locking sleeves, clamping plates, and telescopic components. Two locking sleeves are slidably connected to the locking frame. Each locking sleeve has a clamping plate on its front side, and a telescopic component connects the clamping plates. The outer cylinder and movable end of the telescopic component are each connected to a clamping plate. A constraint groove is formed on the opposite surfaces of each locking sleeve. The upper and lower edges of the constraint groove openings are rounded, and the inner wall of the constraint groove is movably connected to the outer side of the locking arm. Through the linkage of the telescopic components and the cooperation of the double locking sleeves with the rounded constraint grooves, a secondary mechanical locking of the clamping arm position is achieved throughout the transportation process, ensuring that the clamping state remains absolutely irreversible even under extreme airflow disturbances, and release is only permitted when the clamping plates are manually triggered.

[0016] The beneficial effects of the present invention for a transport drone are as follows: by constructing a non-rigidly connected "tuned mass damping system" by using elastic connectors to connect the clamping mechanism and the drone platform, the inertia of the insulator is used to generate an oscillation opposite to the phase of the drone's motion, thereby passively offsetting the direct impact of airflow on the fuselage, significantly reducing the high-frequency jitter of the drone, and improving flight stability under complex weather conditions.

[0017] By constraining the permanent magnet inside the cylinder and the swinging metal plate and fittings to form an electromagnetic damping structure, eddy currents are generated by cutting magnetic field lines when the heavy object swings relative to the magnetic field line. The swing kinetic energy is quickly converted into heat energy and dissipated. This allows the swaying amplitude to be quickly suppressed without consuming electrical energy, preventing the cargo from going out of control due to excessive swinging.

[0018] The gravity clamping structure, consisting of an extrusion plate, an arc-shaped clamping plate, and a clamping base frame, achieves a "tighter the more you pull" self-locking effect by automatically triggering the clamping base frame to tighten using the insulator's own weight. This completely eliminates the risk of goods coming loose due to bumps during transportation and ensures absolute safety during high-altitude transport.

[0019] The mechanical cooperation structure between the locking arm and the constraint groove achieves rigid limiting of the clamping arm angle after the clamping action is completed, preventing the elastic connector from fatigue deformation or accidental opening under long-term load, and providing double mechanical insurance for gravity self-locking.

[0020] By utilizing the clamped fitting itself as part of the closed magnetic circuit, the damping mechanism achieves magnetic circuit disconnection in a static state and magnetic circuit conduction only during oscillation operation. This avoids continuous interference from strong magnetic fields on the UAV compass and GPS navigation sensors, ensuring the accuracy of the flight control system.

[0021] Through the synergistic mechanism of passive vibration absorption and active energy dissipation, the UAV flight control system can achieve more stable motor output without frequent high-power attitude corrections, thereby significantly reducing the overall energy consumption, extending the operating radius and load capacity of a single flight, effectively reducing the time for power line construction, and lowering economic costs. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein: Figure 1 is a schematic diagram of the overall structure of the present invention; Figure 2 is a schematic diagram of the three-dimensional structure of the clamping member of the present invention; Figure 3 is a schematic diagram of the cross-sectional structure of the clamping member of the present invention; Figure 4 is a schematic diagram of the clamping mechanism of the auxiliary member and the insulator of the present invention; Figure 5 is a schematic diagram of the connection relationship between the connecting bolt and the elastic connecting member of the present invention; Figure 6 is a schematic diagram of the cross-sectional structure of the constraint cylinder of the present invention; Figure 7 is a partially enlarged schematic diagram of part A in Figure 2 of the present invention; Figure 8 is a schematic diagram of the cross-sectional structure of the locking sleeve of the present invention; Figure 9 is a schematic diagram of the structure of the elastic friction layer of the present invention.

[0023] Reference numerals: 100, UAV platform; 101, shell; 102, top cover; 103, connecting platform; 200, intermediate auxiliary component; 201, structural plate; 202, structural side plate; 203, constraint cylinder; 2031, structural outer cylinder; 2032, constraint magnetic inner cylinder; 300, clamp component; 301, clamping arm; 302, swinging metal plate; 303, clamping block; 304, clamping base frame; 305, extrusion plate; 306, locking arm; 307, locking frame; 308, locking groove; 309, arc-shaped clamping plate; 310, sliding component; 311, constraint groove; 312, connecting bolt; 313, thrust bearing; 314, locking sleeve; 315, clamping plate; 316, telescopic component; 317, elastic friction layer; 400, insulator; 401, awning; 402, hardware. Detailed Implementation

[0024] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0025] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0026] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0027] Secondly, the present invention is described in detail with reference to the schematic diagrams. When detailing the embodiments of the present invention, for ease of explanation, the cross-sectional views illustrating the device structure may be partially enlarged, not according to the usual scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. In addition, actual fabrication should include three-dimensional spatial dimensions of length, width, and depth.

[0028] As shown in Figures 1-9, this invention proposes a transport drone, including a drone and a transport mechanism. The transport mechanism is installed at the bottom of the drone and is used to transport components for power plant overhead line installation. The transport mechanism includes a clamping mechanism and a locking component. The transport mechanism clamps the power plant overhead line components using the clamping mechanism, and then uses the drone's flight capability to transport the clamping mechanism and the clamped power plant overhead line components to the required location. After that, the clamping mechanism releases the power plant overhead line components for installation. The clamping mechanism is equipped with a locking component, which locks or unlocks the clamping state of the clamping mechanism to achieve stable clamping or release of the power plant overhead line components. Through the integrated clamping and locking design, the entire process of automated operation from ground grabbing, stable aerial transportation to precise high-altitude release is achieved, significantly improving the efficiency and safety of power line installation.

[0029] The transport mechanism also includes an intermediate auxiliary component 200, which includes a structural plate 201 and a structural side plate 202. A structural side plate 202 is provided on each side of the structural plate 201. The structural plate 201 and the structural side plate 202 are perpendicular to each other. A clamping mechanism is connected to the structural side plate 202.

[0030] The clamping mechanism includes a clamping component 300, which comprises an elastic connector, jaw components, and clamping arms 301. The clamping arms 301 are connected to the structural side plate 202 via the elastic connector. The clamping arms 301 are rotatably connected to the elastic connector and movably sleeved. The clamping arms 301 are formed by connecting two structural beams, with an included angle between the two beams between 120 and 150 degrees. Each structural side plate 202 has two clamping arms 301. Jaw components connect the two clamping arms 301 located on different structural side plates 202 and symmetrically arranged about the structural plate 201, thus forming two jaw components. The clamping mechanism carries components used for power plant overhead lines, including insulators 400. The two jaw components cooperate to clamp the insulators 400. Through the double-beam clamping arms at a specific angle, combined with the elastic connector, a flexible, enveloping clamping mechanism, similar to "four fingers encircling," is achieved. This adapts to the columnar shape of the insulator and utilizes elastic deformation to buffer the mechanical impact during takeoff and landing.

[0031] Each clamping jaw component includes a swinging metal plate 302 and a clamping block 303. Clamping arms 301 are located at both ends of the swinging metal plate 302, and a clamping block 303 is provided in the middle of each swinging metal plate 302. Large clamping openings are recessed on the opposite surfaces of the two clamping blocks 303. By connecting the clamping arms on both sides with the swinging metal plate and providing large recessed clamping openings, uniform distribution of clamping force and self-centering function are achieved, ensuring that the insulator will not be skewed or damaged due to local stress concentration during clamping.

[0032] An elastic friction layer 317 is provided on the arc surface of the clamping opening of the clamping block 303, and friction textures are provided on the outer side of the elastic friction layer 317. Through the textured elastic friction layer, the friction coefficient of the contact interface is significantly improved, effectively preventing the insulator from axially slipping or rotating and falling off under strong wind, turbulence, or sudden stop conditions.

[0033] Each clamping block 303 is equipped with a gravity clamping component. Two gravity clamping components cooperate with each other. The gravity clamping component includes a clamping base frame 304, a pressing plate 305, and an arc-shaped clamping plate 309. An arc-shaped movable groove is opened through the clamping block 303. The arc-shaped movable groove is inclined. The pressing plate 305 is provided at the top of the arc-shaped clamping plate 309. The pressing plate 305 is parallel to the upper side of the clamping block 303. The clamping base frame 304 is provided at the bottom of the arc-shaped clamping plate 309. The clamping base frame 304 is inclined. A small clamping opening is opened at the end of the clamping base frame 304 away from the arc-shaped clamping plate 309. Under the action of gravity, the insulator 400 presses the pressing plate 305, so that the clamping base frames 304 move closer to each other and clamp the insulator 400. By utilizing the weight of the goods themselves to drive the clamping base to tighten, a passive self-locking effect of "the heavier the load, the tighter the clamping" is achieved, which solves the problem of clamping force attenuation caused by vibration. When the clamping force of the clamping block 303 decreases, the insulator 400 tends to decrease, thereby applying a stronger squeezing force to the extrusion plate 305, making the insulator 400 clamped tighter and more securely.

[0034] The elastic connector includes a connecting bolt 312 and a thrust bearing 313. The connecting bolt 312 is fixedly connected to the structural side plate 202. Each connecting bolt 312 is fitted with two clamping arms 301 and three thrust bearings 313. The two clamping arms 301 separate the three thrust bearings 313. The thrust bearings 313 are movably fitted with the connecting bolt 312. A spring is fitted at both ends of the connecting bolt 312, and the spring abuts against the corresponding thrust bearing 313. An axial buffer system is constructed through the combination of springs and thrust bearings.

[0035] The insulator 400 includes sheds 401, fittings 402 and pull rods. Several sheds 401 are spaced apart on the pull rods, and each shed 401 has a fitting 402 at its top.

[0036] The locking mechanism includes a limiting component and a gravity locking component. The gravity locking component is movably sleeved on the limiting component. The limiting component includes a locking arm 306, a locking frame 307, a locking groove 308, and a sliding member 310. Each clamping arm 301 is provided with a locking arm 306. The end of the locking arm 306 away from the clamping arm 301 is rotatably connected to the sliding member 310. The locking frame 307 has a locking groove 308, and a sliding member 310 is slidably connected to each end of the locking groove 308. The limiting component restricts the opening angle of the clamping mechanism. By limiting the stroke of the sliding member in the locking groove, a rigid constraint is achieved on the maximum opening angle of the clamping arm, preventing structural interference or accidental damage caused by excessive opening of the clamping mechanism in the non-working state.

[0037] The gravity locking mechanism includes a locking sleeve 314, a clamping plate 315, and a telescopic component 316. Two locking sleeves 314 are slidably connected to the locking frame 307. Each locking sleeve 314 has a clamping plate 315 on its front side. A telescopic component 316 connects between the clamping plates 315. The outer cylinder and movable end of the telescopic component 316 are each connected to a clamping plate 315. A constraint groove 311 is formed on the opposite surfaces of the locking sleeves 314. The upper and lower sides of the opening of the constraint groove 311 are rounded. The inner wall of the constraint groove 311 is movably connected to the outer side of the locking arm 306. Through the linkage of the telescopic component and the cooperation of the double locking sleeves and the rounded constraint groove, a secondary mechanical locking of the clamping arm position is achieved throughout the transportation process, ensuring that the clamping state is absolutely irreversible even under extreme airflow disturbances, and release is only allowed when the clamping plate is manually triggered.

[0038] The locking arm 306 is fixedly connected to the clamping arm 301. The sliding member 310 includes a rolling column, and a limiting plate is provided on one end of the rolling column that passes through the locking groove 308. The diameter of the limiting plate is larger than the width of the locking groove 308. The telescopic member 316 includes a gas spring or an electric cylinder.

[0039] The clamping blocks 303 move closer to each other and clamp the upper part of one of the fittings 402. The umbrella skirt 401 above the clamped fitting 402 is pulled by the insulator 400 as a whole, which squeezes the compression plate 305. The compression plate 305 moves closer along the arc-shaped movable groove, and the arc-shaped clamping plate 309 clamps the lower part of the fitting 402 through the clamping base frame 304.

[0040] The intermediate auxiliary component 200 also includes an electromagnetic damping structure. The electromagnetic damping structure cooperates with the swinging metal plate 302 and the fitting 402. When the jaw component swings around the connecting bolt 312, and when the jaw component moves along the axial direction of the connecting bolt 312, the swinging metal plate 302 and the fitting 402 interact with the magnetic field generated by the electromagnetic damping to generate eddy currents, thereby quickly consuming the kinetic energy of the entire system and stabilizing the structure quickly. The system consists of a carrier mechanism installed at the bottom of the UAV and a carrier mechanism that carries power plant overhead line components. The power plant overhead line components include an insulator 400.

[0041] When drones fly at high altitudes to avoid power grids and trees in mountainous areas, they often encounter strong air currents, making transport difficult. Current methods to reduce interference mainly rely on algorithms to correct the drone's flight status and restrict flight conditions to avoid flying in strong winds. However, this either greatly increases energy consumption, leading to a decrease in transport capacity, and fails to truly eliminate the impact of strong air currents on flight, or it delays the project schedule and postpones construction time.

[0042] Electromagnetic damping structures can passively eliminate swaying caused by strong airflow.

[0043] The unmanned aerial vehicle platform 100 includes a shell 101, a top cover 102, and a connecting platform 103. A structural flat plate 201 and a structural side plate 202 are disposed on the lower and side sides of the connecting platform 103. The top cover 102 is disposed on the top of the shell 101, and a motor with a propeller is disposed on the top cover 102. The connecting platform 103 is disposed on the bottom of the shell 101.

[0044] When both the locking arm 306 and the clamping block 303 are in a horizontal state, the clamping block 303 clamps the fitting 402 through the elastic friction layer 317, and the locking arm 306 is locked in a horizontal state when inserted into the constraint groove 311. If it is necessary to open the clamping arm 301, the locking arm 306 will be restricted by the inner wall of the elastic friction layer 317. Only by manually pinching the two clamping plates 315, compressing the telescopic member 316, and disengaging the locking sleeve 314 from the locking arm 306, can the locked state be released. During flight, if the UAV platform 100 experiences high-frequency shaking or sudden attitude changes due to strong airflow, this embodiment uses the principle of "tuned mass damper" for passive attitude stabilization: Since the insulator 400 is not rigidly connected to the UAV platform 100 through the elastic connector, the motion state of the suspended weight lags behind that of the UAV body due to inertia. When the UAV accelerates to one side, the suspended weight will generate a swinging tendency with the opposite phase, thereby applying a reverse inertial restoring force to the UAV. By using elastic connectors and clamping mechanisms in a non-rigid connection with the drone, when the drone carrying the insulator 400 encounters airflow, the drone, clamping mechanism, and clamped insulator 400 together oscillate relative to each other. The inertia of the clamping mechanism and clamped insulator 400 as a whole counteracts part of the drone's swaying caused by the airflow. Utilizing the "dynamic vibration absorption" effect, part of the vibration energy generated by the airflow impact on the drone body is transferred to the swaying kinetic energy of the suspended weight, effectively reducing the amplitude of the drone body and acting as a low-pass filter to filter high-frequency airflow disturbances. The elastic friction layer 317 is composed of densely arranged U-shaped spring steel plates, which can conduct magnetic fields while clamping the clamping mechanism and clamped insulator 400.

[0045] Meanwhile, to further stabilize the system quickly, this embodiment activates an electromagnetic damping mechanism: as the suspended weight swings or undergoes axial displacement relative to the UAV platform 100, the swinging metal plate 302 and fittings 402 cut magnetic field lines in the strong magnetic field of the constraint cylinder 203, instantly generating powerful eddy currents. These eddy currents generate Joule heating within the conductor, rapidly converting the aforementioned swinging kinetic energy transferred to the weight into heat energy and dissipating it. This dual mechanism of "passive vibration absorption and energy transfer combined with active electromagnetic damping to dissipate energy" allows the system to calm swaying in a very short time, avoiding flight loss of control or a surge in energy consumption caused by direct airflow transmission under traditional rigid connections.

[0046] The electromagnetic damping structure includes a structural plate 201, structural side plates 202, and constraint cylinders 203. Several constraint cylinders 203 are evenly arranged on the structural plate 201. The openings of the constraint cylinders 203 are vertically downwards, facing the jaw components. Each constraint cylinder 203 includes an outer structural cylinder 2031 and a magnetic constraint cylinder 2032. The magnetic constraint cylinder 2032 is located inside the outer structural cylinder 2031, and a permanent magnet is located inside the magnetic constraint cylinder 2032. One of the magnetic poles of the permanent magnet points vertically downwards. The top of the magnetic constraint cylinder 2032 is fixedly connected to the structural plate 201. The magnetic constraint cylinder 2032 is cup-shaped and made of permalloy.

[0047] When the swinging metal plate 302 and the clamping block 303 clamp the fitting 402 of the insulator 400, the metal plate 302 and the clamping block 303 are made of magnetically conductive material, including alloy steel or low carbon steel, forming a complete magnetically conductive circuit composed of metal magnetically conductive material.

[0048] The swinging metal plate 302 tends to be horizontal and both the metal fitting 402 and the metal fitting 402 are located directly below the permanent magnet inside the constraint cylinder 203. The magnetic field generated by one of the magnetic poles of the permanent magnet passes through the constraint cylinder 203 to the structural plate 201, the structural side plate 202, the connecting bolt 312, the clamping arm 301, the swinging metal plate 302, the clamping block 303, the arc-shaped clamping plate 309, the clamping base frame 304, and the metal fitting 402, returning to the other magnetic pole of the permanent magnet, thus forming a magnetic circuit and achieving connection. By utilizing the low magnetic resistance characteristics of the magnetically conductive metal, the magnetic field is effectively guided and forms a closed circuit through the magnetically conductive metal components, allowing the magnetic field to smoothly reach the swinging metal plate 302 and the metal fitting 402 that clamps the insulator 400 via the clamping block 303.

[0049] Unlike the shielding effect of the confined magnetic inner cylinder 2032 that weakens the magnetic field, the magnetic circuit forms effective electromagnetic damping after it is turned on.

[0050] In the non-working state, the magnetic field is strictly constrained by the confined magnetic inner cylinder 2032, and no metal forms a magnetic circuit, eliminating interference with the internal equipment of the drone; in the working state, the magnetic circuit is instantly connected through the intervention of the insulator fittings, generating a stable damping force; the automatic connection is achieved by utilizing the magnetic conductivity of the fittings themselves, without the need for additional operation.

[0051] The specific implementation method is as follows: The telescopic component 316 adopts a gas spring. By pinching the two clamping plates 315 together, the constraint groove 311 inside the locking sleeve 314 is disengaged from the locking arm 306, thereby releasing the locked state of the clamping component 300. At this time, the clamping arm 301 swings under the action of gravity and is in an open state. The operator places the insulator 400 to be transported under the carrying mechanism, controls the two clamping arms 301 to move closer together, and makes the two clamping plates 315 clamp the insulator 400. During this period, the two locking arms 306 move closer with the movement of the clamping arms 301. During this period, the locking arms 306 gradually insert into the constraint groove 311, and the locking sleeve 314... When the telescopic component 316 is compressed under pressure, and the locking arm 306 becomes horizontal, the telescopic component 316 returns to its original length and pushes the locking sleeve 314 into the locking arm 306. At this time, the two clamping blocks 303 also become horizontal and clamp the insulator 400. The umbrella skirt 401 above the clamped hardware 402 is pulled down by the overall weight of the insulator 400, pressing the compression plate 305 downward. The compression plate 305 moves closer along the arc-shaped movable groove, driving the arc-shaped clamping plate 309 to move, thereby causing the clamping base frame 304 to move closer to each other and firmly clamp the lower part of the hardware 402, achieving gravity self-locking. The locking arm 306 is inserted into the structure under the action of structural reset. The clamping slot 311 is restricted to a horizontal state, and the clamping component 300 enters a locked state to ensure that the clamping mechanism's angle is fixed during transportation. At this time, the swinging metal plate 302 and the hardware 402 are located directly below the permanent magnet inside the constraint cylinder 203, and the magnetic circuit is connected to form a strong magnetic field, and the electromagnetic damping structure enters the working state. The UAV platform 100 takes off, lifting the insulator 400 and flying to the designated erection height. During flight, if strong airflow causes the UAV to sway, the clamping component 300 and the suspended insulator 400 will swing relative to the UAV platform 100 or move axially through the elastic connector. At this time, the swinging metal plate 302 and the hardware 402 Cutting magnetic field lines generates eddy currents, which are rapidly consumed by electromagnetic damping to passively dissipate swaying and maintain stable transport. Upon reaching the target position, the UAV platform 100 hovers and slowly descends until the pull rod or lower hardware at the bottom of the insulator 400 contacts the mounting point or release mechanism. Through external commands or mechanical triggering, the force state of the gravity clamp and the action of the auxiliary release mechanism are released, the clamping base 304 and the pressing plate 305 are reset, and the hardware 402 is released. The operator squeezes the clamping plate 315 again to release the limit of the locking arm 306, opens the clamping arm 301, and the UAV platform 100 rises and disengages, completing the release and erection preparation of the insulator 400.

[0052] It should be understood that numerous specific implementation decisions can be made during the development of any practical implementation, such as in any engineering or design project. Such development efforts may be complex and time-consuming, but for those skilled in the art who benefit from this disclosure, the development effort will be a routine work of design, manufacturing, and production without requiring much experimentation.

[0053] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A carrier drone, characterized in that: The system includes a drone and a transport mechanism. The transport mechanism is installed on the bottom of the drone and is used to transport components for power plant wiring. The transport mechanism includes a clamping mechanism and a locking component. The transport mechanism clamps the power plant wiring components through the clamping mechanism. After the drone uses its flight capability to transport the clamping mechanism and the clamped power plant wiring components to the required location, the clamping mechanism releases the power plant wiring components for erection. The clamping mechanism is equipped with a locking component, which locks or releases the clamping state of the clamping mechanism to achieve the purpose of stably clamping or releasing the power plant wiring components.

2. The unmanned aerial vehicle (UAV) according to claim 1, characterized in that: The transport mechanism also includes intermediate auxiliary components, which include a structural plate and structural side plates. A structural side plate is provided on each side of the structural plate, and the structural plate and structural side plates are perpendicular to each other. A clamping mechanism is connected to the structural side plates.

3. The unmanned aerial vehicle (UAV) according to claim 2, characterized in that: The clamping mechanism includes a clamping component, which includes an elastic connector, a jaw component, and a clamping arm. The clamping arm is connected to the structural side plate via the elastic connector. The clamping arm is rotatably connected to the elastic connector and is movably sleeved. The clamping arm is formed by connecting two structural beams with an included angle between the two structural beams between 120 and 150 degrees. Two clamping arms are provided on each structural side plate. The two clamping arms located on different structural side plates and symmetrically arranged about the structural plate are connected by a jaw component, thus forming two jaw components. The components used for transporting power plant overhead lines include insulators. The two jaw components cooperate to clamp the insulators.

4. A carrier drone according to claim 3, characterized in that: Each jaw component includes a swinging metal plate and a clamping block. The clamping arms are located at both ends of the swinging metal plate, and a clamping block is provided in the middle of each swinging metal plate. Large clamping openings are recessed on the opposite surfaces of the two clamping blocks.

5. A carrier drone according to claim 4, characterized in that: An elastic friction layer is provided on the arc surface of the clamping opening of the clamping block, and friction texture is provided on the outer side of the elastic friction layer.

6. A carrier drone according to claim 3, characterized in that: Each clamping block is equipped with a gravity clamping component. Two gravity clamping components cooperate with each other. The gravity clamping component includes a clamping base frame, a pressing plate, and an arc-shaped clamping plate. An arc-shaped movable groove is opened through the clamping block. The arc-shaped movable groove is inclined. A pressing plate is set at the top of the arc-shaped clamping plate. The pressing plate is parallel to the upper side of the clamping block. A clamping base frame is set at the bottom of the arc-shaped clamping plate. The clamping base frame is inclined. A small clamping opening is opened at the end of the clamping base frame away from the arc-shaped clamping plate. Under the action of gravity, the insulator presses the pressing plate, so that the clamping base frames come closer to each other and clamp the insulator.

7. A carrier drone according to claim 3, characterized in that: The elastic connector includes a connecting bolt and a thrust bearing. The connecting bolt is fixedly connected to the structural side plate. Each connecting bolt is fitted with two clamping arms and three thrust bearings. The two clamping arms separate the three thrust bearings. The thrust bearings are movably connected to the connecting bolt. A spring is fitted at both ends of the connecting bolt, and the spring abuts against the corresponding thrust bearing.

8. A carrier drone according to claim 3, characterized in that: An insulator includes sheds, fittings, and a pull rod. Several sheds are spaced apart on the pull rod, and a fitting is provided at the top of each shed.

9. A carrier drone according to claim 1, characterized in that: The locking component includes a limiting component and a gravity locking component. The gravity locking component is movably sleeved on the limiting component. The limiting component includes a locking arm, a locking frame, a locking groove, and a sliding component. Each clamping arm is provided with a locking arm. The end of the locking arm away from the clamping arm is rotatably connected to a sliding component. The locking frame has a locking groove. A sliding component is slidably connected to each end of the locking groove. The limiting component restricts the opening angle of the clamping mechanism.

10. A carrier drone according to claim 9, characterized in that: The gravity locking component includes a locking sleeve, a clamping plate, and a telescopic component. Two locking sleeves are slidably connected on the locking frame. A clamping plate is provided on the front of each locking sleeve. A telescopic component is connected between the clamping plates. A clamping plate is connected to the outer cylinder and the movable end of the telescopic component. A constraint groove is provided on the opposite side of each locking sleeve. The upper and lower sides of the opening of the constraint groove are rounded. The inner wall of the constraint groove is movably connected to the outer side of the locking arm.

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