Electromagnetic propulsion remote fire extinguishing device

Abstract

The invention discloses an electromagnetic propulsion remote fire extinguishing device, which belongs to the technical field of fire fighting equipment, and comprises a horizontal rotary seat, an electromagnetic propulsion device, a power supply device and a control device, the mounting frame is fixed on the inner ring and is provided with a first gear and a second gear which are meshed with the outer gear ring, the first gear is connected with a first driving assembly, and the second gear is connected with a second driving assembly; the launching pitching frame is arranged on the mounting frame and can rotate around a first axis; a fan-shaped gear sheet meshed with the second gear and a track are arranged on the launching pitching frame; the electromagnetic ejector comprises an ejection tube and a moving block, and the moving block is arranged on the track; the brake can reset the electromagnetic ejector; when the electromagnetic ejector resets, the counter-recoil machine can generate resistance; according to the invention, the azimuth angle can be adjusted by using the horizontal revolving bed, and the pitching angle can be adjusted by using the launching pitching frame, so that the long-distance throwing precision is improved; the recoil energy generated when the fire extinguishing bomb is launched can be consumed and stored by utilizing the sliding block, the track, the counter-recoil machine and the recoil machine.

Description

Technical Field

[0001] The present invention relates to the technical field of vehicle-mounted electromagnetic remote fire-fighting equipment, and particularly relates to an electromagnetic propulsion remote fire-extinguishing device. Background Art

[0002] In fire scenes such as forests, hazardous chemicals, fuels, and traffic accidents, due to conditions such as large fire intensity, frequent secondary deflagrations, and complex geographical environments, it is difficult for rescue equipment and personnel to quickly approach, and in some cases, they cannot even get close to the scene for rescue, making it impossible to suppress the fire in a timely manner and making it difficult to implement fire-fighting and rescue effectively in a timely manner.

[0003] Throwing fire-extinguishing bombs over long distances is an effective means to solve the above situations. Traditional ways of throwing fire-extinguishing bombs include: gas-pushing type, air-dropping type, artillery-firing type, rocket-propelling type, etc. However, these throwing methods have problems such as short throwing distance, poor mobility, poor throwing accuracy, or being restricted by the management of pyrotechnic products. This results in relatively high launching costs and risks for fire-extinguishing bombs, making it difficult to popularize and apply them, and unable to achieve an economical and efficient fire-extinguishing effect.

[0004] In order to increase the effective fire-extinguishing distance of fire-extinguishing bombs, improve their throwing accuracy, and achieve fast mobility, fire-extinguishing bombs can also be thrown using electromagnetic launch technology. Electromagnetic launch technology is based on the principle of electromagnetism, has a shorter acceleration distance and higher acceleration efficiency, and the muzzle velocity can easily exceed the limit velocity of chemical propulsion. In theory, the armature can be accelerated to 100 - 1000 m / s within a few milliseconds. However, this will also inevitably generate a huge launching recoil force, which is incomparable to that of a gunpowder launching device in terms of the harm to the launching device.

[0005] Therefore, researching and designing a vehicle-mounted electromagnetic propulsion remote fire-extinguishing device that can withstand the recoil force when launching large-load fire-extinguishing bombs, is fast and mobile, and can accurately deliver over long distances is an urgent problem to be solved at present. Summary of the Invention

[0006] Regarding the problems existing in the prior art, an electromagnetic propulsion remote fire-extinguishing device provided by the present invention can adjust the azimuth angle of the electromagnetic ejector using a horizontal slewing base, and adjust the pitch angle of the electromagnetic ejector using a launch elevation frame, thereby improving the long-distance throwing accuracy of the fire-extinguishing bomb. At the same time, by using a matching slider and rail, as well as a recoil mechanism and a muzzle brake mechanism provided between the electromagnetic ejector and the launch elevation frame, when launching the fire-extinguishing bomb, the electromagnetic ejector can move relative to the launch elevation frame, which can consume and store the recoil energy, ensure that the electromagnetic ejector is in a ready-to-fire position usually and returns smoothly after launching the fire-extinguishing bomb, and effectively withstand the recoil force when launching large-load fire-extinguishing bombs.

[0007] To achieve the above object, the technical solution adopted by the present invention is as follows: The present invention provides an electromagnetic propulsion long-distance fire extinguishing device, comprising: A horizontal slewing base, the horizontal slewing base includes an external gear ring and an inner ring, the inner ring is sleeved inside the external gear ring and can rotate relative to the external gear ring around its axis; A mounting bracket, the mounting bracket is fixed on the inner ring; a first gear meshing with the external gear ring is provided on the mounting bracket, the first gear is connected with a first driving component for driving it to rotate; a second gear is provided on the mounting bracket, the second gear is connected with a second driving component for driving it to rotate; A launching pitching frame, the launching pitching frame is arranged on the mounting bracket and can rotate around a first axis, the first axis is horizontally arranged; a sector gear piece is provided on the launching pitching frame, the axis of the sector gear piece is the first axis, the sector gear piece meshes with the second gear; a track perpendicular to the first axis is provided on the launching pitching frame; An electromagnetic ejector, the electromagnetic ejector includes a launching tube, the axis of the launching tube is perpendicular to and intersects with the first axis; a moving block is provided on the electromagnetic ejector, the moving block is arranged on the track and can move along the track; A recoil brake, the recoil brake is arranged between the electromagnetic ejector and the launching pitching frame, the recoil brake can buffer the recoil force and reset the electromagnetic ejector; A recuperator, the recuperator is arranged between the electromagnetic ejector and the launching pitching frame, when the electromagnetic ejector is reset, the recuperator can generate a resistance to the electromagnetic ejector.

[0008] As a preferred technical solution, the recuperator includes a recuperating rod and an oil storage cylinder, the oil storage cylinder is fixed on the launching pitching frame, an oil cavity is provided inside the oil storage cylinder, and the oil cavity is filled with hydraulic oil; one end of the recuperating rod extends into the oil cavity, the other end of the recuperating rod is fixedly connected with the electromagnetic ejector, a recuperating piston is provided on the part of the recuperating rod located inside the oil cavity, the recuperating piston is in dynamic seal with the oil cavity; a plurality of one-way valves are provided on the recuperating piston; front oil holes and rear oil holes are respectively provided on both sides of the recuperating piston of the recuperating rod, and the front oil holes communicate with the rear oil holes.

[0009] As a preferred technical solution, the recuperating piston divides the oil cavity into a front oil cavity and a rear oil cavity, the front oil holes are located in the front oil cavity, and the rear oil holes are located in the rear oil cavity; a plurality of the front oil holes are provided, the plurality of front oil holes are axially distributed along the recuperating rod, and the apertures of the plurality of front oil holes gradually increase in the direction away from the rear oil holes; And / or, the recoil piston includes piston rings, and a plurality of oil holes are provided on the piston rings. A fixing ring is provided on the recoil rod, and a return spring and an oil drain ring are provided between the fixing ring and the piston rings. The return spring applies an elastic force to the oil drain ring, so that the oil drain ring abuts against the piston rings to block the oil holes.

[0010] As a preferred technical solution, the recoil mechanism includes a recoil rod, an outer cylinder, and a middle cylinder. The outer cylinder is fixed to the launch pitching frame, the middle cylinder is fixed inside the outer cylinder, and pressure medium is filled between the outer cylinder and the middle cylinder and inside the middle cylinder. The middle cylinder has a through hole communicating its interior with the outer cylinder; one end of the recoil rod extends into the middle cylinder, the other end of the recoil rod is fixedly connected to the electromagnetic ejector, and a recoil piston is provided on the part of the recoil rod located inside the middle cylinder, and the recoil piston is movably sealed inside the middle cylinder.

[0011] As a preferred technical solution, the space between the outer cylinder and the middle cylinder is filled with a gas medium and hydraulic oil, and the middle cylinder is filled with hydraulic oil; the axis of the middle cylinder is located below the axis of the outer cylinder; And / or, an air injection hole communicating with its interior is provided on the outer cylinder.

[0012] As a preferred technical solution, the launch tube includes a framework and electromagnetic coils wound around the framework; the moving block is fixed to the framework.

[0013] As a preferred technical solution, multiple stages of the electromagnetic coils are wound on the framework, and the multiple stages of electromagnetic coils are distributed along the axial direction of the launch tube; And / or, the electromagnetic coils are wound with insulated flat copper wires; And / or, the electromagnetic coils are connected to a pulse power supply; And / or, the gap between the framework and the electromagnetic coils is filled with epoxy resin; And / or, the material of the framework is set as epoxy resin material FR4; And / or, a front-mounted cartridge case is provided at the front end of the launch tube, and the front-mounted cartridge case is collinear with the axis of the launch tube.

[0014] As a preferred technical solution, the mounting frame includes a bottom plate, and two vertically arranged side plates are provided on the bottom plate. Bearing outer holes are provided on both of the two side plates; bearing inner holes are provided at positions corresponding to the bearing outer holes on the launch pitching frame, and bearings are provided between the bearing inner holes and the bearing outer holes; the axes of the bearing inner holes and the bearing outer holes are both set as the first axis.

[0015] As a preferred technical solution, two recoil mechanisms and two counter-recoil mechanisms are provided. The two recoil mechanisms and the two counter-recoil mechanisms are respectively arranged on the two side plates. And / or, two tracks are provided, and the two tracks are respectively arranged on the two side plates. And / or, the bottom plate and the side plates are both made of high-strength wear-resistant alloy steel PCrNi3MoV. And / or, the bottom plate and the side plates are both provided with a hollow structure.

[0016] As a preferred technical solution, semi-circular ring grooves are provided on the inner circular surface of the external gear ring and the outer circular surface of the inner ring. The two semi-circular ring grooves can be spliced into an annular raceway, and a number of rolling elements are embedded in the annular raceway. And / or, a vehicle body is further included. The vehicle body has a chassis, and the external gear ring is fixed on the chassis. And / or, the first drive assembly is a servo motor, and the first gear is arranged on the output shaft of the servo motor. And / or, the second drive assembly includes a stepping motor and a harmonic reducer. The stepping motor is in transmission connection with the second gear through the harmonic reducer.

[0017] The beneficial effects of the present invention are as follows: 1. The present invention can accurately adjust the azimuth angle of the electromagnetic ejector by using the horizontal slewing base, and can accurately adjust the pitching angle of the electromagnetic ejector by using the launching pitching frame, thereby improving the long-distance throwing accuracy of the fire extinguishing bomb. At the same time, by using the matching slider and track, and the recoil mechanism and counter-recoil mechanism arranged between the electromagnetic ejector and the launching pitching frame, when the fire extinguishing bomb is launched, the electromagnetic ejector can retreat relative to the launching pitching frame, which can consume and store the recoil energy, ensure that the electromagnetic ejector is in a standby position usually and reset smoothly after launching the fire extinguishing bomb, reduce the force on the electromagnetic ejector to one tenth to one fortieth of the recoil force, and effectively bear the recoil force when launching large-load fire extinguishing bombs.

[0018] 2. The skeleton of the present invention adopts the epoxy resin material FR4, the gap between the skeleton and the electromagnetic coil is filled with epoxy resin, and the bottom plate and the side plates adopt high-strength wear-resistant alloy steel PCrNi3MoV, which can effectively improve the impact resistance.

[0019] 3. The horizontal slewing base of the present invention can be conveniently arranged on the chassis of the vehicle body, which can effectively improve the mobility. Description of the Drawings

[0020] Figure 1 It is a schematic diagram of the overall structure of an embodiment of an electromagnetic propulsion long-distance fire extinguishing device of the present invention. Figure 2For Figure 1 Structural schematic diagram of the horizontal slewing base and the mounting bracket in Figure 3 For Figure 1 Structural schematic diagram of the horizontal slewing base, the mounting bracket and the launch elevation bracket in Figure 4 For Figure 1 Structural schematic diagram of the horizontal slewing base, the mounting bracket, the launch elevation bracket, the recoil mechanism and the buffer mechanism in Figure 5 For Figure 1 Structural schematic diagram of the launch elevation bracket in Figure 6 For Figure 5 Structural schematic diagram of the recoil mechanism and the buffer mechanism in Figure 7 For Figure 6 Cross-sectional view of Figure 8 For Figure 7 Enlarged view of area A in Figure 9 For Figure 1 Structural schematic diagram of the horizontal slewing base in Figure 10 For Figure 9 Cross-sectional view taken along the C-C direction in

[0021] In the figures: 1 - horizontal slewing base, 11 - external gear ring, 12 - inner ring, 13 - semi-circular ring groove, 14 - rolling element, 2 - mounting bracket, 21 - first gear, 22 - servo motor, 23 - second gear, 24 - stepper motor, 25 - harmonic reducer, 26 - bottom plate, 27 - side plate, 271 - bearing outer hole, 3 - launch elevation bracket, 31 - sector gear segment, 32 - track, 33 - bearing inner hole, 4 - electromagnetic ejector, 41 - launch tube, 42 - front cartridge case, 5 - buffer mechanism, 51 - buffer rod, 52 - outer cylinder, 521 - air injection hole, 53 - middle cylinder, 531 - through hole, 54 - buffer piston, 6 - recoil mechanism, 61 - recoil rod, 611 - front oil hole, 612 - rear oil hole, 613 - fixing ring, 62 - oil storage cylinder, 621 - front oil chamber, 622 - rear oil chamber, 63 - recoil piston, 631 - piston ring, 632 - oil drain ring, 633 - return spring, 634 - oil through hole. Detailed implementation manners

[0022] For the convenience of those skilled in the art to understand, the present invention will be further described below with reference to the accompanying drawings.

[0023] Please refer to Figures 1 - 10, which is an embodiment of an electromagnetic propulsion long-range fire extinguishing device provided by the present invention, includes a horizontal slewing base 1. The horizontal slewing base 1 includes an external gear ring 11 and an inner ring 12. The inner ring 12 is sleeved inside the external gear ring 11 and can rotate relative to the external gear ring 11 around its axis. The mounting bracket 2 is fixed on the inner ring 12; a first gear 21 meshing with the external gear ring 11 is provided on the mounting bracket 2. The first gear 21 is connected with a first driving component for driving it to rotate. The first driving component drives the first gear 21 to rotate, and the mounting bracket 2 can be driven to slewing through the external gear ring 11. A second gear 23 is provided on the mounting bracket 2, and the second gear 23 is connected with a second driving component for driving it to rotate; a launching pitching frame 3 is arranged on the mounting bracket 2 and can rotate around a first axis. The first axis is horizontally arranged; a sector gear piece 31 is provided on the launching pitching frame 3. The axis of the sector gear piece 31 is the first axis, and the sector gear piece 31 meshes with the second gear 23. The second driving component drives the second gear 23 to rotate, and the launching pitching frame 3 can be driven to pitch through the sector gear piece 31. A track 32 perpendicular to the first axis is provided on the launching pitching frame 3; the electromagnetic ejector 4 includes a launching tube 41. The axis of the launching tube 41 is perpendicular to and intersects with the first axis; a moving block is provided on the electromagnetic ejector 4. The moving block is arranged on the track 32 and can move along the track 32; a recoil brake 5 is arranged between the electromagnetic ejector 4 and the launching pitching frame 3. The recoil brake 5 can buffer the recoil force when the electromagnetic ejector 4 fires and reset in time; a recuperator 6 is arranged between the electromagnetic ejector 4 and the launching pitching frame 3. When the electromagnetic ejector 4 resets, the recuperator 6 can generate a resistance force that decreases from large to small on the electromagnetic ejector 4; when firing a fire extinguishing bomb, the electromagnetic ejector 4 can move along the track 32 under the recoil force. At the same time, the recoil brake 5 consumes and stores the recoil energy. After the firing is completed, while the recoil brake 5 releases the energy, the recuperator 6 can make the electromagnetic ejector 4 reset smoothly, and can effectively bear the recoil force when launching a large-load fire extinguishing bomb and reset reliably.

[0024] It should be noted that the present invention should include a vehicle body. The vehicle body has a chassis, and the external gear ring 11 is fixed on the flange base at the tail of the chassis. The vehicle body can quickly and maneuverably transport the present invention to a suitable position; further, the chassis is preferably a special fire vehicle chassis. Straight ladders that can go up and down the chassis can be provided on both sides of the middle of the chassis. Legs are provided at the front and tail of the chassis to increase the support base and reduce the pressure on the tires caused by the recoil force. The legs are preferably of a hydraulic transmission T-shaped structure and can be telescoped in the horizontal and vertical directions to realize the ground support and horizontal calibration of the vehicle body during the launching process.

[0025] In this embodiment, please refer to Figure 1 、 Figures 4 - 8The recoil mechanism 6 is used to generate effective hydraulic resistance when the electromagnetic ejector 4 is recoiled, and control the movement law of the electromagnetic ejector 4 recoiling; specifically, the recoil mechanism 6 includes a recoil rod 61 and an oil storage cylinder 62, the oil storage cylinder 62 is fixed on the launch pitch frame 3, and the oil storage cylinder 62 has an oil chamber, and the oil chamber is filled with hydraulic oil; one end of the recoil rod 61 extends into the oil chamber, and the other end of the recoil rod 61 is fixedly connected to the electromagnetic ejector 4, and a recoil piston 63 is provided on the part of the recoil rod 61 located in the oil chamber, and the recoil piston 63 is dynamically sealed with the oil chamber; a plurality of one-way valves are provided on the recoil piston 63, only When the return rod 61 is forced to move backward, the hydraulic oil in the oil chamber can flow through the one-way valve; the return rod 61 is located on both sides of the return piston 63 and is respectively provided with a front oil hole 611 and a rear oil hole 612, and the front oil hole 611 and the rear oil hole 612 are in communication. When the return rod 61 is reset, the hydraulic oil can only flow from the front oil hole 611 to the rear oil hole 612, effectively controlling the reset speed of the return rod 61; the recoil mechanism 6 adopts a control rod structure and a rod recoil method, which can generate effective hydraulic resistance when the electromagnetic ejector 4 is reset, ensuring the smoothness and accuracy of the reset of the electromagnetic ejector 4.

[0026] Based on the above examples, please refer to Figure 7 and Figure 8 The recoil piston 63 divides the oil chamber into a front oil chamber 621 and a rear oil chamber 622. The front oil hole 611 is located in the front oil chamber 621, and the rear oil hole 612 is located in the rear oil chamber 622. The front oil hole 611 is set to be multiple, and the multiple front oil holes 611 are distributed along the axial direction of the recoil rod 61. The apertures of the multiple front oil holes 611 gradually increase in the direction away from the rear oil hole 612. During the reset process of the recoil rod 61, starting from the front oil hole 611 farthest from the rear oil hole 612, they are blocked by the oil storage cylinder 62 in turn, so that the return oil amount from the front oil chamber 621 to the rear oil chamber 622 gradually changes from large to small, so that the withdrawal speed of the recoil rod 61 also changes from fast to slow until it is zero, so as to keep the electromagnetic ejector 4 reset smoothly.

[0027] For further information, please refer to Figure 7 and Figure 8 The return piston 63 includes a piston ring 631, and a plurality of oil holes 634 are provided on the piston ring 631. A fixing ring 613 is provided on the return rod 61, and the fixing ring 613 is located in the front oil chamber 621. A return spring 633 and an oil drain ring 632 are provided between the fixing ring 613 and the piston ring 631. The return spring 633 applies elastic force to the oil drain ring 632, so that the oil drain ring 632 abuts against the piston ring 631 to block the oil holes 634. Only when the hydraulic oil in the rear oil chamber 622 can push the oil drain ring 632 open under the action of the pressure difference, the hydraulic oil in the rear oil chamber 622 can flow into the front oil chamber 621 through the oil holes 634, thereby realizing the function of a one-way valve and ensuring that the return rod 61 can smoothly retreat when subjected to force.

[0028] In this embodiment, please refer to Figure 1 and Figures 4 - 7 . The recoil mechanism 5 includes a recoil rod 51, an outer cylinder 52 and a middle cylinder 53. The outer cylinder 52 is fixed to the launch pitching frame, and the middle cylinder 53 is fixed inside the outer cylinder 52. The space between the outer cylinder 52 and the middle cylinder 53 and inside the middle cylinder 53 are both filled with a pressure medium. There is a through hole 531 on the middle cylinder 53 that connects its interior with the outer cylinder 52, and the through hole 531 is submerged by hydraulic oil. One end of the recoil rod 51 extends into the middle cylinder 53, and the other end of the recoil rod 51 is fixedly connected to the electromagnetic ejector. A recoil piston 54 is provided on the part of the recoil rod 51 located inside the middle cylinder 53. The recoil piston 54 is movably sealed inside the middle cylinder 53. When firing the fire extinguishing bomb, the recoil mechanism 5 is subject to a recoil force, the recoil rod 51 is forced to retreat, and the recoil piston 54 compresses the pressure medium. While the pressure medium plays a buffering role, after the recoil force disappears, the pressure medium expands and can automatically push the recoil piston 54 to reset the recoil rod 51.

[0029] On the basis of the foregoing embodiment, please refer to Figure 7 . The space between the outer cylinder 52 and the middle cylinder 53 is filled with a gas medium and hydraulic oil, and the middle cylinder 53 is filled with hydraulic oil. The gas medium is specifically nitrogen, and the gas medium is more easily compressed when under pressure. The hydraulic oil is specifically aviation hydraulic oil. The axis of the middle cylinder 53 is located below the axis of the outer cylinder 52. The recoil mechanism 5 adopts an eccentric structure with an internal middle cylinder 53 and a rod-recoil liquid-gas pressure method. When firing the fire extinguishing bomb, the recoil mechanism 5 can store the energy of the recoil force, and after the recoil force disappears, it can make the electromagnetic ejector 4 return to the position before firing and keep the electromagnetic ejector 4 in the standby position.

[0030] It should be noted that an air injection hole 521 communicating with its interior is provided on the outer cylinder 52, and gas medium can be injected into the outer cylinder 52, thereby adjusting the initial air pressure inside the outer cylinder 52 and controlling the buffering effect on the electromagnetic ejector 4.

[0031] In this embodiment, the launch tube 41 should include a framework and electromagnetic coils wound around the framework; the moving block is fixed to the framework, so that the launch tube 41 can move along the track 32; specifically, preferably multiple-stage electromagnetic coils are wound on the framework, and the multiple-stage electromagnetic coils are distributed along the axial direction of the launch tube 41. The electromagnetic coils are connected to a pulse power supply, and the pulse power supply is installed in the middle of the vehicle chassis to provide short-pulse and high-power current for the electromagnetic coils. After the multiple-stage electromagnetic coils are energized, they can push the fire extinguishing bomb in multiple stages, effectively increasing the speed of the fire extinguishing bomb; the electromagnetic coils are preferably wound with insulated flat copper wires.

[0032] Furthermore, the gap between the framework and the electromagnetic coils is preferably filled with epoxy resin, and the material of the framework is preferably set as the epoxy resin material FR4, which can effectively improve the structural strength, coaxiality and impact resistance of the launch tube 41.

[0033] Furthermore, please refer to Figure 1 , a front-mounted cartridge case 42 is provided at the front end of the launch tube 41. The front-mounted cartridge case 42 is collinear with the axis of the launch tube 41. The front-mounted cartridge case 42 can guide the moving direction of the fire extinguishing bomb and ensure the long-distance throwing accuracy.

[0034] In this embodiment, please refer to Figures 1 - 4 , the mounting frame 2 includes a bottom plate 26. Two vertically arranged side plates 27 are welded on the bottom plate 26. Bearing outer holes 271 are provided on both side plates 27; bearing inner holes 33 are provided at positions corresponding to the bearing outer holes 271 on the launch elevation frame 3. The axes of the bearing inner holes 33 and the bearing outer holes 271 are both set as the first axis. A heavy-duty bearing is provided between the bearing inner hole 33 and the bearing outer hole 271 to achieve the rotational connection between the launch elevation frame 3 and the mounting frame 2. The rotational connection between the launch elevation frame 3 and the mounting frame 2 uses a heavy-duty bearing instead of the traditional coaxial connection method, which can enable the electromagnetic ejector 4 to be installed in the middle of the launch elevation frame 3, ensuring that the central axis of the electromagnetic ejector 4 always intersects with the first axis under any allowable elevation angle, ensuring that the recoil force is transmitted to the mounting frame 2 through the recoil mechanism 6 and the recoil brake 5, reducing the impact on the overall mounting frame 2, saving space and reducing weight; further, a scale dial should also be provided on the side plate 27 corresponding to the bearing outer hole 271 to facilitate visually observing the elevation angle of the launch tube 41.

[0035] Specifically, please refer to Figures 5 - 8 , square sliding columns are symmetrically provided on both sides of the electromagnetic ejector 4. Corresponding matching tracks 32 are provided on the two side plates 27 of the mounting frame 2. The square sliding columns and the tracks 32 form a sliding pair. The electromagnetic ejector 4 passes through this sliding pair to ensure the smoothness and accuracy of the buffer displacement.

[0036] Similarly, the recoil mechanism 6 and the recoil brake 5 are both preferably set to two. The two recoil mechanisms 6 and the two recoil brakes 5 are respectively provided on the two side plates 27, which can stably buffer the electromagnetic ejector 4 and enable the electromagnetic ejector 4 to be reset smoothly.

[0037] It should be noted that the materials of the bottom plate 26 and the side plates 27 are both preferably set as high-strength wear-resistant alloy steel PCrNi3MoV to ensure the structural strength and impact resistance of the mounting frame 2; further, the bottom plate 26 is preferably set as a hollow structure to minimize the weight to the greatest extent.

[0038] In this embodiment, please refer to Figure 1 、 Figure 9 and Figure 10A semicircular annular groove 13 is provided on the inner circumferential surface of the outer gear ring 11 and the outer circumferential surface of the inner ring 12. The two semicircular annular grooves 13 can be spliced ​​into an annular raceway. A plurality of rolling bodies 14 are embedded in the annular raceway. The outer gear ring 11 and the inner ring 12 form a structure similar to a deep groove ball bearing to ensure that the inner ring 12 can rotate smoothly relative to the outer gear ring 11. Specifically, the rolling bodies 14 are preferably configured as steel balls. At the same time, a flange stop is machined on the upper surface of the inner ring 12 for fixing the mounting frame 2, and a flange is machined on the lower surface of the outer gear ring 11 for fixed connection with the chassis of the vehicle body.

[0039] Specifically, the first drive component is preferably set to a servo motor 22, and the first gear 21 is arranged on the output shaft of the servo motor 22; at the same time, the second drive component preferably includes a stepper motor 24 and a harmonic reducer 25, and the stepper motor 24 is connected to the second gear 23 through the harmonic reducer 25; further, the harmonic reducer 25 has a worm gear structure, which can perform high-precision adjustment and self-locking of the pitch angle of the launch tube 41.

[0040] Please refer to Figures 1 - 10 , the specific use of the present invention is as follows: In actual use, the present invention can also be integrated with an unmanned aerial vehicle reconnaissance system and artificial intelligence (AI) technology. The unmanned aerial vehicle reconnaissance system provides preliminary reconnaissance, three-dimensional terrain modeling and damage assessment functions. In combination with artificial intelligence (AI) technology, parameters are input into a controller for optimal calculation. The calculation results form the launch parameters of the present invention and the final launch command is completed through the present invention. The present invention, the unmanned aerial vehicle reconnaissance system and artificial intelligence (AI) technology form a full closed-loop control system, which controls the entire process of the fire extinguishing process, and can achieve efficient, accurate and economical fire fighting.

[0041] Specifically, the UAV reconnaissance system may include two six-rotor UAVs, one of which is equipped with an optoelectronic pod, and the other is equipped with a communication pod; the two six-rotor UAVs carry the optoelectronic pod and the communication pod respectively and rise to the vicinity of the fire source. The optoelectronic pod is used to scout the area of ​​the fire source, assess the size of the fire, and conduct long-distance fire reconnaissance activities; the communication pod is used to provide on-site communication tasks and perform 3D modeling of the vehicle body around the fire source.

[0042] Further, the controller receives the fire and geographical information measured by the optoelectronic pod and the communication pod, digitizes the fire and geographical information through artificial intelligence (AI) technology, establishes a fire situation sand table around the fire scene, and provides data and geographical information support. At the same time, based on the digitized fire and geographical information, the controller calculates the launch angle and exit velocity of the fire extinguishing bomb. Specifically, the azimuth angle of the electromagnetic ejector 4 is adjusted by the horizontal slewing base 1, and the pitch angle of the electromagnetic ejector 4 is adjusted by the launch elevation frame 3 to achieve the adjustment of the launch angle of the fire extinguishing bomb. The voltage and timing of the electromagnetic coil are controlled by the pulse power supply to achieve the adjustment of the exit velocity of the fire extinguishing bomb. Then, the fire extinguishing bomb can be launched to complete the launch mission.

[0043] After the launch mission is completed, the optoelectronic pod transmits the re-captured image information of the fire source scene back to the controller, evaluates the damage situation through artificial intelligence (AI) technology, and sends the evaluated result to the controller. The controller determines whether it is necessary to continue launching the fire extinguishing bomb until the fire source is extinguished, thus forming a full-closed-loop fire control system.

[0044] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An electromagnetic propulsion remote fire extinguishing device, characterized in that: include: A horizontal swivel seat (1), the horizontal swivel seat (1) comprising an outer gear ring (11) and an inner ring (12), the inner ring (12) being sleeved inside the outer gear ring (11) and being capable of rotating relative to the outer gear ring (11) around its axis; A mounting frame (2), the mounting frame (2) being fixed on the inner ring (12); the mounting frame (2) being provided with a first gear (21) meshing with the outer gear ring (11), the first gear (21) being connected to a first driving component for driving the first gear (21) to rotate; the mounting frame (2) being provided with a second gear (23), the second gear (23) being connected to a second driving component for driving the first gear (23) to rotate; a launching pitch frame (3), the launching pitch frame (3) being arranged on the mounting frame (2) and being capable of rotating about a first axis, the first axis being arranged horizontally; the launching pitch frame (3) being provided with a sector gear piece (31), the axis of the sector gear piece (31) being the first axis, the sector gear piece (31) being meshed with the second gear (23); the launching pitch frame (3) being provided with a track (32) arranged perpendicularly to the first axis; An electromagnetic ejector (4), the electromagnetic ejector (4) comprising a launching tube (41), the axis of the launching tube (41) being perpendicular to and intersecting the first axis; a moving block is provided on the electromagnetic ejector (4), the moving block is provided on the track (32) and is capable of moving along the track (32); A recoil brake (5), the recoil brake (5) being arranged between the electromagnetic ejector (4) and the launch pitch frame (3), the recoil brake (5) being capable of buffering recoil and resetting the electromagnetic ejector (4); A recoil mechanism (6) is provided between the electromagnetic ejector (4) and the launch pitch frame (3), and when the electromagnetic ejector (4) is reset, the recoil mechanism (6) can generate resistance to the electromagnetic ejector (4).

2. The electromagnetic propulsion remote fire extinguishing device according to claim 1, characterized in that: The recoil mechanism (6) comprises a recoil rod (61) and an oil storage cylinder (62). The oil storage cylinder (62) is fixed on the launch pitch frame (3). The oil storage cylinder (62) has an oil chamber inside. The oil chamber is filled with hydraulic oil. One end of the recoil rod (61) extends into the oil chamber. The other end of the recoil rod (61) is fixedly connected to the electromagnetic ejector (4). A recoil piston (63) is provided on the part of the recoil rod (61) located in the oil chamber. The recoil piston (63) is dynamically sealed with the oil chamber. A plurality of one-way valves are provided on the recoil piston (63). The recoil rod (61) is provided with a front oil hole (611) and a rear oil hole (612) at both sides of the recoil piston (63). The front oil hole (611) and the rear oil hole (612) are in communication.

3. The electromagnetic propulsion remote fire extinguishing device according to claim 2, characterized in that: The recoil piston (63) divides the oil chamber into a front oil chamber (621) and a rear oil chamber (622); the front oil hole (611) is located in the front oil chamber (621), and the rear oil hole (612) is located in the rear oil chamber (622); a plurality of front oil holes (611) are provided, and the plurality of front oil holes (611) are distributed along the axial direction of the recoil rod (61); and the apertures of the plurality of front oil holes (611) gradually increase in a direction away from the rear oil hole (612); And / or, the recoil piston (63) comprises a piston ring (631), a plurality of oil holes (634) are provided on the piston ring (631), a fixing ring (613) is provided on the recoil rod (61), a return spring (633) and an oil drain ring (632) are provided between the fixing ring (613) and the piston ring (631), and the return spring (633) applies an elastic force to the oil drain ring (632), so that the oil drain ring (632) abuts against the piston ring (631) to block the oil holes (634).

4. An electromagnetic propulsion remote fire extinguishing device according to claim 1 or 2, characterized in that: The recoil mechanism (5) comprises a recoil rod (51), an outer tube (52) and a middle tube (53); the outer tube (52) is fixed on the launch pitch frame (3); the middle tube (53) is fixed inside the outer tube (52); the space between the outer tube (52) and the middle tube (53) and inside the middle tube (53) are filled with pressure medium; the middle tube (53) has a through hole (531) for connecting its interior with the outer tube (52); one end of the recoil rod (51) extends into the middle tube (53); the other end of the recoil rod (51) is fixedly connected to the electromagnetic ejector (4); a recoil piston (54) is provided on the portion of the recoil rod (51) located inside the middle tube (53); the recoil piston (54) is dynamically sealed and arranged inside the middle tube (53).

5. The electromagnetic propulsion remote fire extinguishing device according to claim 4, characterized in that: The space between the outer cylinder (52) and the middle cylinder (53) is filled with gas medium and hydraulic oil, and the middle cylinder (53) is filled with hydraulic oil; the axis of the middle cylinder (53) is located below the axis of the outer cylinder (52); And / or, the outer cylinder (52) is provided with an air injection hole (521) communicating with the interior thereof.

6. The electromagnetic propulsion remote fire extinguishing device according to claim 1, characterized in that: The transmitting tube (41) comprises a frame and an electromagnetic coil wound on the frame; the moving block is fixed on the frame.

7. The electromagnetic propulsion remote fire extinguishing device according to claim 6, characterized in that: A plurality of stages of electromagnetic coils are wound on the frame, and the plurality of stages of electromagnetic coils are distributed along the axial direction of the transmitting tube (41); And / or, the electromagnetic coil is wound with insulated flat copper wire; And / or, the electromagnetic coil is connected to a pulse power supply; and / or, the gap between the skeleton and the electromagnetic coil is filled with epoxy resin; And / or, the material of the frame is set to epoxy resin material FR4; And / or, a front end of the launch tube (41) is provided with a front cartridge (42), and the front cartridge (42) is colinear with the axis of the launch tube (41).

8. The electromagnetic propulsion remote fire extinguishing device according to claim 6, characterized in that: The mounting frame (2) comprises a bottom plate (26), two vertically arranged side plates (27) are provided on the bottom plate (26), and the two side plates (27) are both provided with a bearing outer hole (271); a bearing inner hole (33) is provided at a position corresponding to the bearing outer hole (271) on the launch pitch frame (3), and a bearing is provided between the bearing inner hole (33) and the bearing outer hole (271); and the axis centers of the bearing inner hole (33) and the bearing outer hole (271) are both set as the first axis.

9. The electromagnetic propulsion remote fire extinguishing device according to claim 8, characterized in that: The recoil machine (6) and the recoil machine (5) are both provided in pairs, and the two recoil machines (6) and the two recoil machines (5) are respectively provided on the two side plates (27); And / or, the number of the rails (32) is two, and the two rails (32) are respectively arranged on the two side panels (27); And / or, the material of the bottom plate (26) and the side plate (27) is set to be high-strength wear-resistant alloy steel PCrNi3MoV; And / or, the bottom plate (26) and the side plate (27) are both configured as hollow structures.

10. The electromagnetic propulsion remote fire extinguishing device according to claim 1, characterized in that: The inner circumferential surface of the outer gear ring (11) and the outer circumferential surface of the inner ring (12) are both provided with a semicircular annular groove (13), and the two semicircular annular grooves (13) can be spliced ​​into an annular raceway, and a plurality of rolling bodies (14) are embedded in the annular raceway; And / or, further comprising a vehicle body, the vehicle body having a chassis, the outer gear ring (11) being fixed on the chassis; And / or, the first driving component is configured as a servo motor (22), and the first gear (21) is disposed on an output shaft of the servo motor (22); And / or, the second driving component comprises a stepping motor (24) and a harmonic reducer (25), and the stepping motor (24) is drivingly connected to the second gear (23) via the harmonic reducer (25).

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