Fire extinguishing unmanned aerial vehicle for power facilities

Abstract

The application relates to a fire extinguishing unmanned aerial vehicle for electric power facilities, which comprises a flying vehicle and a throwing mechanism, the bottom of the flying vehicle is provided with a mounting mechanism, the mounting mechanism comprises a loading unit and a throwing unit, the loading unit comprises a locking piece, the locking piece locks fire extinguishing bombs, the flying vehicle can mount and transport the fire extinguishing bombs, the throwing unit comprises a limiting and releasing piece and an unlocking piece, and the limiting and releasing piece is arranged at the top of the loading unit. Through the use of the unlocking piece, the fire extinguishing bombs can be quickly unlocked, the fire extinguishing bombs are given an initial speed, air flow interference is reduced, the fire extinguishing bombs can quickly and accurately reach a fire site, and the fire extinguishing efficiency is improved.

Description

Technical Field

[0001] This invention belongs to the field of multi-functional unmanned aerial vehicles (UAVs), specifically a fire-fighting UAV for power facilities. Background Technology

[0002] With the continuous expansion of the power system, the fire safety of power facilities such as substations and transmission lines has received increasing attention. Once a fire breaks out in a power facility, it is often accompanied by high temperatures, strong electromagnetic fields, and complex terrain. Traditional manual firefighting methods are not only slow to respond but also pose significant risks to personal safety. In recent years, drones, due to their maneuverability and lack of terrain limitations, have been increasingly applied in the field of firefighting.

[0003] Existing firefighting drones primarily operate by carrying fire extinguishing agent tanks for spraying or dropping fire extinguishing bombs. However, these existing technologies have significant shortcomings when applied to firefighting of power facilities: Firstly, most existing drones use gravity-based release of fire extinguishing bombs, resulting in near-zero initial velocity after detachment. During descent, these bombs are highly susceptible to rising hot air currents and crosswinds, causing flight trajectory deviations and making it difficult to accurately hit the fire source. Secondly, existing delivery mechanisms are relatively simple, lacking stable control over the fire extinguishing bomb's flight attitude. The bombs are prone to tumbling during descent, further reducing delivery accuracy and firefighting efficiency. Therefore, this paper proposes a firefighting drone for power facilities. 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: the initial velocity of existing fire-fighting drones is insufficient when dropping fire extinguishing bombs, and the fire extinguishing bombs are easily affected by airflow interference, resulting in low dropping accuracy and low fire extinguishing efficiency.

[0006] To address the aforementioned technical problems, this invention provides the following technical solution: a fire-fighting drone for power facilities, comprising an aircraft and a delivery mechanism. The aircraft has a mounting mechanism at its bottom, which includes a loading unit and a delivery unit. The loading unit includes a locking component that locks the fire extinguishing projectile, enabling the aircraft to load and transport it. The delivery unit includes a limiting launcher and an unlocking component. The limiting launcher is located at the top of the loading unit, and the unlocking component is located inside the loading unit. The unlocking component quickly releases the locking component from the fire extinguishing projectile, and the limiting launcher ejects the projectile, allowing it to leave the mounting mechanism and gain initial velocity, enabling it to quickly reach the fire scene and reducing the impact of external airflow and fire-related airflow. This effectively improves the accuracy of fire extinguishing projectile delivery, reduces fire-fighting delays caused by airflow interference, and is suitable for fire-fighting needs in high-altitude and complex environments of power facilities.

[0007] As a preferred technical solution for fire-fighting drones used in power facilities, the aircraft includes a drone, which includes a fuselage and a support frame. The bottom of the fuselage is provided with two symmetrically distributed support frames, and the top of the fuselage is provided with four structural arms. Each structural arm is provided with a motor with a flight propeller.

[0008] As a preferred technical solution for firefighting drones used in power facilities, the loading unit includes a transport component, which comprises a drone operating housing and drone loading cylinders. The drone operating housing is located at the bottom of the drone body, and several drone loading cylinders are located at the bottom of the drone operating housing. Fire extinguishing bombs are installed inside some of the drone loading cylinders. Multiple drone loading cylinders can load multiple fire extinguishing bombs, meeting the firefighting needs of large-scale or multi-point fires in power facilities. The drone loading cylinders also provide protection for the fire extinguishing bombs.

[0009] As a preferred technical solution for fire-fighting drones used in power facilities, the locking mechanism includes a control column and a hook. The hook is located at the bottom of the control column, and extends into and locks the fire extinguishing bomb. This hook-locking mechanism ensures that the fire extinguishing bomb's detachment during flight is controllable, guaranteeing transportation safety.

[0010] As a preferred technical solution for fire-fighting drones used in power facilities, the unlocking component includes a control rod, which is movably inserted into the inner side of the control column, and its bottom end engages with a hook. The combination structure of the control rod and the hook is simple, enabling rapid response to the unlocking action and shortening the preparation time for fire extinguishing bomb deployment.

[0011] As a preferred technical solution for fire-fighting drones used in power facilities, the limiting launch component includes a locking cylinder, an iron rod, an electromagnet, and a piston. The locking cylinder is located on the inner top wall of the drone's operating box. An electromagnet is located at the top of the locking cylinder, and a piston chamber is formed at the bottom of the locking cylinder. A piston is movably connected to the inner side of the piston chamber, and an iron rod is located at the top of the piston. The top of the iron rod engages with the electromagnet, and the bottom of the piston is fixedly connected to an unlocking component. A high-pressure gas supply pipe is connected to the top of the piston chamber. This launching structure, combining the electromagnet and high-pressure gas, can precisely control the launch force of the fire-fighting projectile, further improving the accuracy of deployment and adapting to fires at power facilities at different heights.

[0012] As a preferred technical solution for fire-fighting drones used in power facilities, the fire-extinguishing projectile includes a projectile body, a tail, and an insertion slot. The tail is located at the top of the projectile body, and the insertion slot is located on the inner side of the tail. Both sides of the opening at the top of the insertion slot are rounded. The hook is movably connected to the insertion slot. The rounded corner structure of the insertion slot facilitates the quick insertion of the hook, reduces the difficulty of locking and mounting, and improves the ease of use of the equipment.

[0013] As a preferred technical solution for fire-fighting drones used in power facilities, the fire extinguishing bomb also includes stabilizing fins and a release cover. The release cover is located at the bottom of the bomb body, and four stabilizing fins are evenly distributed on the outer circumference of the tail, with adjacent fins perpendicular to each other. These four perpendicular stabilizing fins enhance the stability of the fire extinguishing bomb during flight, preventing trajectory deviation and ensuring accurate arrival at the fire location. Simultaneously, the release cover can be quickly opened upon arrival, ensuring timely release of the extinguishing agent.

[0014] As a preferred technical solution for fire-fighting drones used in power facilities, the hook assembly includes two movable hooks connected by a spring. Each movable hook includes a guide roller, a control plate, and a locking plate. The two control plates are symmetrically arranged. A movable cavity is formed on the inner side of the bottom of each control column, with two symmetrically arranged connecting ports on each cavity. A control plate is movably connected to each side of the movable cavity, and each control plate has a locking plate that movably inserts into the connecting port. A guide roller is passed through each control plate, and the guide roller is rotatably connected to the control plate. The fire extinguishing bomb... It also includes locking grooves, with two symmetrically formed locking grooves inside the inner side of the groove. The locking plate is movably inserted into the locking grooves. Two symmetrically arranged limiting grooves are formed on opposite surfaces inside the movable cavity. The two ends of the guide rollers extend into one limiting groove respectively, and the guide rollers are slidably connected to the limiting grooves. The bottom end of the control rod is movably abutted against the upper side of the control plate. The locking plate is a right-angled trapezoid. When the locking plate and locking groove are locked, the release cover is made of a fragile material. The inner cavity of the projectile contains the extinguishing agent. The fragile material includes porous foam ceramic, and the porous foam ceramic material includes alumina. The spring-connected double movable hook design allows for flexible switching between locking and unlocking. The right-angled trapezoidal locking plate facilitates quick engagement and disengagement. The cooperation between the guide rollers and the limiting grooves ensures smooth operation of the movable hooks. The release cover made of fragile material can automatically break when the fire extinguishing projectile lands, ensuring rapid release of the extinguishing agent. The porous foam ceramic material combines fragility and stability, preventing accidental damage during transportation.

[0015] As a preferred technical solution for firefighting drones used in power facilities, a hammer is installed at the bottom of the control rod, and a rubber layer is installed at the lower end of the hammer. The rubber layer of the hammer moves in contact with the control plate. The rubber layer of the hammer can buffer the impact force when the control rod contacts the control plate, avoid wear on parts, extend the service life of the equipment, and at the same time increase the contact friction to ensure accurate transmission of the unlocking action and avoid jamming.

[0016] The beneficial effects of this invention's fire-fighting drone for power facilities are as follows: The use of an unlocking mechanism enables rapid unlocking of the fire extinguishing projectile, imparting initial velocity, reducing airflow interference, and ensuring rapid and accurate arrival at the fire scene, thus improving fire-fighting efficiency. The use of a spin mechanism enables high-speed rotation of the fire extinguishing projectile, controlling its flight attitude, preventing tumbling, and improving delivery accuracy and flight stability. The use of a locking mechanism ensures secure mounting and rapid unlocking of the fire extinguishing projectile, guaranteeing stability during transport, achieving precise release at the fire scene, and preventing accidental deployment. The combination of a high-pressure gas structure and a buffer component enables rapid ejection and smooth connection, reducing component impact wear and extending equipment lifespan. The use of an unlocking drive structure enables rapid unlocking of the fire extinguishing projectile, while the centrifugal force generated by the rotation of the control column enhances locking stability and prevents accidental unlocking during transport.

[0017] The use of a special structure for the fire extinguishing bomb release cap enables two release methods: impact-induced breakage and high-temperature failure. This ensures timely release of the extinguishing agent and improves fire extinguishing efficiency. The use of a drone-mounted delivery system allows for the simultaneous mounting and independent deployment of multiple fire extinguishing bombs, adapting to complex fire scenarios, mitigating on-site safety risks, and protecting the personal safety of personnel. The combination of passive wheels and a rotating disc ensures rapid detachment of the fire extinguishing bombs during ejection, preventing the spin mechanism from interfering with the ejection trajectory, balancing spin stability and ejection accuracy, and optimizing fire extinguishing effectiveness. Attached Figure Description

[0018] 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:

[0019] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0020] Figure 2 This is a schematic cross-sectional view of the front of the present invention;

[0021] Figure 3 For the present invention Figure 2 A partially enlarged structural diagram of part A in the middle;

[0022] Figure 4 For the present invention Figure 3 A partially enlarged structural diagram of section B;

[0023] Figure 5 This is a schematic diagram of the structure of the fire extinguishing bomb of the present invention.

[0024] Reference numerals: 100, UAV; 101, fuselage; 102, support frame; 200, transport component; 201, UAV operating box; 202, UAV loading cylinder; 203, locking cylinder; 204, power component; 205, rotating disk; 206, transmission annular groove; 207, elastic ring one; 208, elastic ring two; 210, electromagnet; 211, iron column; 212, piston; 213, control lever; 2 14. Passive wheel; 215. Elastic linkage; 216. Control column; 217. Locking plate; 218. Control plate; 219. Guide roller; 220. Fitting recess; 221. Limiting block; 222. Recovery trough; 223. Limiting groove; 224. Movable cavity; 300. Fire extinguishing bomb; 301. Explosive body; 302. Release cover; 303. Tail; 304. Stabilizing wing; 305. Deep groove; 306. Locking groove. Detailed Implementation

[0025] 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.

[0026] 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.

[0027] 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.

[0028] 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.

[0029] like Figures 1-5 As shown, this invention proposes a fire-fighting drone for power facilities, comprising an aircraft and a delivery mechanism. The aircraft has a mounting mechanism at its bottom, which includes a loading unit and a delivery unit. The loading unit includes a locking component that locks the fire extinguishing projectile, enabling the aircraft to load and transport it. The delivery unit includes a limiting launcher and an unlocking component. The limiting launcher is located at the top of the loading unit, and the unlocking component is located inside the loading unit. The unlocking component quickly releases the locking component from the fire extinguishing projectile, and the limiting launcher ejects the projectile, allowing it to leave the mounting mechanism and gain initial velocity, enabling it to quickly reach the fire scene and reducing the impact of external and fire-related airflow. This effectively improves the accuracy of fire extinguishing projectile delivery, reduces fire-fighting delays caused by airflow interference, and is suitable for fire-fighting needs in high-altitude and complex environments of power facilities.

[0030] The aircraft includes a drone 100, which includes a body 101 and a support frame 102. The bottom of the body 101 is provided with two symmetrically distributed support frames 102, and the top of the body 101 is provided with four structural arms, each of which is equipped with a motor with a flight propeller.

[0031] The loading unit includes a transport component 200, which comprises a drone operation box 201 and drone loading cylinders 202. The drone operation box 201 is located at the bottom of the body 101, and several drone loading cylinders 202 are located at the bottom of the drone operation box 201. Fire extinguishing bombs 300 are installed inside some of the drone loading cylinders 202. Multiple drone loading cylinders can load multiple fire extinguishing bombs, meeting the fire extinguishing needs of large-scale or multi-point fires in power facilities. The drone loading cylinders can also protect the fire extinguishing bombs.

[0032] The locking mechanism includes a control post 216 and a hook. The bottom of the control post 216 is equipped with a hook that extends into and locks the fire extinguishing bomb. The hook-locking mechanism allows the fire extinguishing bomb to be controlled during flight, ensuring transportation safety.

[0033] The unlocking mechanism includes a control rod 213, which is movably inserted into the inner side of the control column 216. The bottom end of the control rod 213 engages with a hook. The simple structure of the control rod and hook allows for rapid response of the unlocking action, shortening the preparation time for the fire extinguishing grenade deployment.

[0034] The limiting launch component includes a locking cylinder 203, an iron rod 211, an electromagnet 210, and a piston 212. The locking cylinder 203 is located on the inner top wall of the UAV operating box 201. The electromagnet 210 is located on the top of the locking cylinder 203, and a piston chamber is opened at the bottom of the locking cylinder 203. The piston 212 is movably connected to the inner side of the piston chamber. The iron rod 211 is located on the top of the piston 212, and the top of the iron rod 211 cooperates with the electromagnet 210. The bottom of the piston 212 is fixedly connected to an unlocking component, and a high-pressure gas supply pipe is connected to the top of the piston chamber. The launching structure, which combines the electromagnet and high-pressure gas, can precisely control the launching force of the fire extinguishing projectile, further improving the accuracy of the deployment and adapting to fires involving power facilities at different heights.

[0035] The fire extinguishing bomb 300 includes a bomb body 301, a tail section 303, and a penetration groove 305. The tail section 303 is located at the top of the bomb body 301, and the penetration groove 305 is located on the inner side of the tail section 303. Both sides of the opening at the top of the penetration groove 305 are rounded. The hook is movably connected to the penetration groove 305. The rounded corner structure of the penetration groove facilitates the quick insertion of the hook, reduces the difficulty of locking and attaching, and improves the ease of use of the equipment.

[0036] As a preferred technical solution for fire-fighting drones used in power facilities, the fire extinguishing bomb 300 also includes stabilizing fins 304 and a release cover 302. The release cover 302 is located at the bottom of the bomb body 301, and four stabilizing fins 304 are evenly arranged on the outer circumference of the tail 303, with adjacent stabilizing fins 304 perpendicular to each other. The four mutually perpendicular stabilizing fins can improve the stability of the fire extinguishing bomb during flight, avoid flight trajectory deviation, and ensure that the fire extinguishing bomb accurately reaches the fire location. At the same time, the release cover can be quickly opened after the fire extinguishing bomb arrives, ensuring timely release of the extinguishing agent.

[0037] The hook assembly includes two movable hooks connected by a spring. Each movable hook includes a guide roller 219, a control plate 218, and a locking plate 217. The two control plates 218 are symmetrically arranged. A movable cavity 224 is formed on the inner side of the bottom of the control column 216. Two symmetrical connecting ports are formed on the movable cavity 224. A control plate 218 is movably connected to each side of the movable cavity 224. Each control plate 218 has a locking plate 217, which is movably inserted into the connecting port. A guide roller 219 is passed through the control plate 218, and the guide roller 219 is rotatably connected to the control plate 218. The fire extinguishing bomb 300 also includes a locking groove 306, extending into the groove 306. Two locking grooves 306 are symmetrically opened on the inner side of 05. The locking plate 217 is movably inserted into the locking groove 306. Two limiting grooves 223 are symmetrically arranged on the opposite inner surface of the movable cavity 224. The two ends of the guide roller 219 extend into one limiting groove 223 respectively. The guide roller 219 is slidably connected to the limiting groove 223. The bottom end of the control rod 213 is movably abutted against the upper side of the control plate 218. The locking plate 217 is a right trapezoid. When the locking plate 217 is locked with the locking groove 306, the release cover 302 is made of a fragile material. The inner cavity of the projectile 301 contains the extinguishing agent. The fragile material includes porous foam ceramic. The material of the porous foam ceramic includes alumina. The spring-connected double-hook design allows for flexible switching between locking and unlocking. The right-angled trapezoidal locking plate facilitates quick engagement and disengagement. The cooperation between the guide roller and the limiting groove ensures smooth operation of the hooks. The release cap, made of fragile material, automatically breaks upon landing, ensuring rapid release of the extinguishing agent. The porous foam ceramic material combines fragility and stability, preventing accidental damage during transportation.

[0038] A hammer is provided at the bottom of the control lever 213, and a rubber layer is provided at the lower end of the hammer. The rubber layer of the hammer is in contact with the control plate 218. The rubber layer of the hammer can buffer the impact force when the control lever contacts the control plate, avoid wear of parts, extend the service life of the equipment, and at the same time increase the contact friction to ensure accurate transmission of the unlocking action and avoid jamming.

[0039] The carrier component 200 also includes a spin mechanism, which can rotate the fire extinguishing bomb to improve its flight stability and reduce its influence from external airflow and fire field airflow. The spin mechanism includes a locking cylinder 203, a rotating disk 205, a transmission annular groove 206, a passive wheel 214, and an elastic linkage 215. The rotating disk 205 is rotatably connected to the inner side of the UAV operating box 201. The central axis of the rotating disk 205 is fixedly connected to the power output end of the power component 204. The outer peripheral surface of the rotating disk 205 is provided with a transmission annular groove 206. The outer peripheral surface of the passive wheel 214 is provided with an elastic linkage 215. The elastic linkage 215 is movably engaged with the transmission annular groove 206. The inner wall of the transmission annular groove 206 is provided with friction texture. The power component 204 includes a reducer and a motor. The reducer is located on the lower side of the UAV operating box 201. The power input end of the reducer is fixedly connected to the power output end of the motor.

[0040] The power unit 204 controls the rotation of the rotating disk 205. The rotating disk 205 rotates along with the elastic linkage 215 and the driven wheel 214. The driven wheel 214 rotates along with the control column 216. The control column 216, through the control plate 218 and the locking plate 217, engages with the locking groove 306 to rotate the tail 303, thereby causing the fire extinguishing bomb 300 to rotate and giving it spin stability. The loading cylinder of the UAV carrying the fire extinguishing bomb is arranged around the rotating disk 205.

[0041] The elastic linkage 215 on the outer periphery of the passive wheel 214 extends into the inner side of the transmission annular groove 206. The elastic linkage 215 presses against the inner side of the transmission annular groove 206, and the elastic linkage 215 is in frictional connection with the inner wall of the transmission annular groove 206. The bottom wall of the inner side of the transmission annular groove 206 supports the elastic linkage 215, limits the elastic linkage 215, and restricts the position of the passive wheel 214. The transmission annular groove 206 and the elastic linkage 215 cooperate, and the iron column 211 cooperates with the electromagnet 210, so that the control column 216 is lifted. The fire extinguishing bomb 300 is lifted by the hook on the control column 216.

[0042] The hammer head of the control rod 213 is movably connected to the inner top wall of the movable cavity 224, and the diameter of the hammer head is larger than the diameter of the control rod 213. The hammer head and the control rod 213 are rotatably connected.

[0043] The carrier component 200 also includes an elastic ring 1 207 and an elastic ring 208. The bottom wall of the inner cavity of the UAV operating box 201 is provided with the elastic ring 208. The control column 216 passes through the elastic ring 208. The passive wheel 214 is in movable contact with the elastic ring 208. The top of the passive wheel 214 is provided with the elastic ring 1 207. The control rod 213 is movably inserted into the elastic ring 1 207. The elastic ring 1 207 reduces the impact of the piston 212.

[0044] The movable hook also includes a limiting block 221. A mating recess 220 is provided on the control plate 218. The inner walls of the mating recess 220 are perpendicular to each other. The hammer of the control rod 213 moves and abuts against the inner wall of the mating recess 220. A recycling groove 222 is provided at the bottom of the middle part of the movable cavity 224. The circumference of the recycling groove 222 is composed of four identical arc surfaces. The top of the arc surface forms a step with the inner bottom wall of the movable cavity 224. The step is movably connected to the limiting block 221, which restricts the upward movement of the control plate 218. The outer side of the limiting block 221 is slidably connected to the arc surface of the recycling groove 222. A spring is connected between the limiting blocks 221.

[0045] The spring compresses the limiting block 221, causing the two locking plates 217 to move away from each other and extend out of the movable cavity 224. During the rotation of the control column 216, due to centrifugal force, the locking plates 217 tend to continue to extend outward.

[0046] The release cap 302 is composed of two identical half-structures joined together by hot melt adhesive, which fails at temperatures exceeding 70 degrees Celsius. This allows the release cap 302 to release the extinguishing agent through two methods: impact breakage and damage from high-temperature baking.

[0047] The high-pressure gas supply pipeline is connected to a high-pressure gas cylinder located in the carrier component 200 via a solenoid valve, and the piston 212 is given ejection capability by injecting high-pressure gas into the piston chamber.

[0048] Electromagnet 210 generates a magnetic field that attracts iron column 211, causing piston 212 to block piston chamber. High-pressure gas is injected into piston chamber. After the magnetic field attraction of electromagnet 210 is released, the high-pressure gas compresses piston 212 and moves it within piston chamber, achieving the purpose of ejecting piston 212. This allows piston 212 and control rod 213 to compress passive wheel 214 and control plate 218, causing control plate 218 to overcome centrifugal force and compress spring, causing locking plate 217 to disengage from locking groove 306 and thus unlock. Passive wheel 214 moves control column 216, which pushes fire extinguishing bomb 300 away from UAV loading cylinder 202 and gives fire extinguishing bomb 300 a certain initial velocity, making it fly more stably.

[0049] High-pressure gas compresses piston 212 and driven wheel 214 to move, causing driven wheel 214 to move relative to rotating disk 205, and elastic linkage 215 to disengage from the inner cavity of transmission annular groove 206.

[0050] The specific implementation method is as follows: the fire extinguishing bomb 300 is inserted into the drone loading cylinder 202, the edge of the bottom of the bomb body 301 is squeezed to avoid the release cover 302 and the bomb body 301 is moved upward until the tail 303 contacts the control post 216. As the bomb body 301 continues to move upward, the control post 216 enters the indentation groove 305. During the process, the locking plate 217 is squeezed into the inner wall of the indentation groove 305 and retracts into the movable cavity 224. When the locking plate 217 reaches the corresponding position of the locking groove 306, the spring squeezes the control plate 218 to separate from each other, so that the locking plate 217 extends out of the movable cavity 224 and inserts into the locking groove 306, thereby locking the fire extinguishing bomb 300 and the control post 216 relative to each other.

[0051] The fire extinguishing bomb 300 continues to press the control column 216 upward, causing the elastic linkage 215 to embed into the transmission annular groove 206. The driven wheel 214 and the elastic ring 207 carry the piston 212 and the iron column 211 into the piston chamber. The electromagnet 210 generates a magnetic field to attract the iron column 211, causing the iron column 211 to move upward and come into contact with the electromagnet 210 and be attracted.

[0052] Electromagnet 210 generates a magnetic field that attracts iron column 211, causing piston 212 to block piston chamber. High-pressure gas is injected into piston chamber. After the magnetic field attraction of electromagnet 210 is released, the high-pressure gas compresses piston 212 and moves it within piston chamber, achieving the purpose of ejecting piston 212. This allows piston 212 and control rod 213 to compress passive wheel 214 and control plate 218, causing control plate 218 to overcome centrifugal force and compress spring, causing locking plate 217 to disengage from locking groove 306 and thus unlock. Passive wheel 214 moves control column 216, which pushes fire extinguishing bomb 300 away from UAV loading cylinder 202 and gives fire extinguishing bomb 300 a certain initial velocity, allowing it to fly more stably into the fire scene. Fire extinguishing bomb 300 releases fire extinguishing agent to extinguish the fire.

[0053] 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.

[0054] 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 fire-fighting drone for power facilities, characterized in that: The system includes an aircraft and a delivery mechanism. The aircraft has a mounting mechanism at its bottom, which includes a loading unit and a delivery unit. The loading unit includes a locking component that locks the fire extinguishing bomb, enabling the aircraft to load and transport the fire extinguishing bomb. The delivery unit includes a limiting launch component and an unlocking component. The limiting launch component is located at the top of the loading unit, and the unlocking component is located inside the loading unit. The unlocking component quickly releases the locking component from the fire extinguishing bomb, and the limiting launch component ejects the fire extinguishing bomb, causing the fire extinguishing bomb to leave the mounting mechanism and gain initial velocity. The locking mechanism includes a control column and a hook. The bottom of the control column has a hook that extends into and locks the fire extinguishing bomb. The hook includes two movable hooks connected by a spring. Each movable hook includes a guide roller, a control plate, and a locking plate. The two control plates are symmetrically arranged. A movable cavity is formed on the inner side of the bottom of the control column, with two symmetrical connecting ports on each cavity. A control plate is movably connected to each side of the movable cavity. Each control plate has a locking plate that movably inserts into the connecting port. A guide roller extends through the control plate, connecting the guide roller to the control plate. Rotary connection; the fire extinguishing bomb also includes a locking groove, with two locking grooves symmetrically opened inside the groove, the locking plate being movably inserted into the locking groove, and two symmetrically arranged limiting grooves being opened on opposite surfaces inside the movable cavity, with the two ends of the guide rollers respectively extending into one limiting groove, the guide rollers being slidably connected to the limiting grooves, the bottom end of the control rod being movably abutting against the upper side of the control plate, the locking plate being a right trapezoid in shape, and when the locking plate is locked to the locking groove, the release cover being made of a fragile material, the inner cavity of the bomb containing the fire extinguishing agent, the fragile material including porous foam ceramic, the porous foam ceramic being made of alumina; The delivery system also includes a spin mechanism, which enables the fire extinguishing bomb to rotate, improving its flight stability and reducing its susceptibility to external airflow and fire-related airflow. The spin mechanism includes a rotating disk, a transmission annular groove, a driven wheel, and an elastic linkage. The rotating disk is rotatably connected to the inner side of the UAV's operating box. The central axis of the rotating disk is fixedly connected to the power output end of the power component. The outer circumferential surface of the rotating disk has a transmission annular groove, and the outer circumferential surface of the driven wheel has an elastic linkage that is movably engaged with the transmission annular groove.

2. The fire-fighting drone for power facilities according to claim 1, characterized in that: The aircraft includes a drone, which consists of a fuselage and a support frame. The fuselage has two symmetrically distributed support frames at its bottom.

3. The fire-fighting drone for power facilities according to claim 1, characterized in that: The loading unit includes a transport component, which includes a drone operation box and drone loading cylinders. The drone operation box is located at the bottom of the main body, and several drone loading cylinders are located at the bottom of the drone operation box. Fire extinguishing bombs are installed inside some of the drone loading cylinders.

4. The fire-fighting drone for power facilities according to claim 1, characterized in that: The unlocking component includes a control lever, which is movably inserted into the inner side of the control column, and the bottom end of the control lever engages with the hook.

5. A fire-fighting drone for power facilities according to claim 3, characterized in that: The limiting launch component includes a locking cylinder, an iron column, an electromagnet, and a piston. The locking cylinder is located on the inner top wall of the drone's operating box. An electromagnet is located on the top of the locking cylinder. A piston chamber is opened at the bottom of the locking cylinder. A piston is movably connected to the inner side of the piston chamber. An iron column is located at the top of the piston. The top of the iron column cooperates with the electromagnet. The bottom of the piston is fixedly connected to the unlocking component. A high-pressure gas supply pipe is connected to the top of the piston chamber.

6. The fire-fighting drone for power facilities according to claim 4, characterized in that: The fire extinguishing bomb includes a body, a tail, and a depth groove. The tail is located at the top of the body, and the depth groove is located on the inner side of the tail. Both sides of the opening at the top of the depth groove are rounded. The hook is movably connected to the depth groove.

7. A fire-fighting drone for power facilities according to claim 6, characterized in that: The fire extinguishing bomb also includes stabilizing fins and a release cover. The release cover is located at the bottom of the bomb body, and four stabilizing fins are evenly distributed on the outer circumference of the tail, with adjacent stabilizing fins perpendicular to each other.

8. A fire-fighting drone for power facilities according to claim 1, characterized in that: A hammer is provided at the bottom of the control lever, and a rubber layer is provided at the lower end of the hammer. The rubber layer of the hammer is in contact with the control panel.

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