Anti-hail rocket projectile
By designing anti-hail rockets and using radar to locate hail clouds and control the explosion time, a large-scale hail prevention effect is achieved, solving the problems of uncontrollable explosion points and safety hazards in existing technologies, and ensuring the safety and explosion range of the rockets.
Patent Information
- Application Number
- CN202411504578.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-26
- Publication Date
- 2025-09-16
AI Technical Summary
The explosion point of existing anti-hail rockets is uncontrollable, the impact range of the blast wave is limited, and there are safety hazards. In particular, the 37mm anti-aircraft gun may cause an explosion on the ground and cause casualties.
A hail-proof rocket has been designed, which includes an engine unit, an explosion unit, a control mechanism and a warhead assembly. It uses radar to detect hail clouds and determine the explosion time. A digital chip is used to control the engine ignition. It explodes in the air and self-destructs. The debris falls in the form of flocs. The explosion range is expanded to ≥120m, forming a spherical impact range with a diameter of 240m to ensure safety.
A large-scale hail prevention effect was achieved, the explosion range was expanded to 120m, and the blast wave impact range reached 240m, which improved the safety of the rocket, avoided the risk of premature explosion, and ensured the safety of ground personnel.
Smart Images
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Abstract
Description
Technical Field
[0001] The invention relates to the technical field of artificial hail prevention, in particular to a hail prevention rocket. Background Art
[0002] As global warming continues, hailstorms are likely to become more frequent and severe. This reminds us of the urgency of addressing climate change to mitigate potential catastrophic consequences. Implementing and improving artificial hail suppression can play a significant role in ensuring agricultural disaster preparedness and harvests, protecting people's lives and property, and promoting the development of atmospheric science and control technologies. Current artificial hail suppression technology primarily utilizes a combination of radar technologies to detect, identify, and locate hail clouds. Human intervention attempts to reduce or cut off the water supply to small ice embryos within the clouds, preventing them from developing into hailstones or preventing small ice particles from falling to the ground before they become larger hailstones.
[0003] At present, the main methods of artificial hail prevention are sowing and explosive hail prevention. Sowing hail prevention uses aircraft, ground rockets or combustion furnaces to sow artificial ice nuclei into the clouds to affect the growth process of hail, while explosive hail prevention uses ground anti-aircraft guns and self-destructive rain-making and hail-prevention rockets to produce explosions to interfere with rising air currents and block the supply of water vapor. Today's special hail prevention rockets use ground rockets to quickly sow large doses of artificial ice nuclei into hail clouds for hail prevention operations. Explosive hail prevention is now mainly based on 37mm anti-aircraft guns, but the main limitation of this product is that the explosion point is uncontrollable and the impact range of the blast wave is limited to <60m. However, during artificial weather modification operations, there have been incidents of 37mm anti-aircraft guns falling to the ground and exploding, causing casualties among ordinary people, resulting in a low safety factor. Summary of the Invention
[0004] The purpose of the present invention is to overcome the defects of the prior art and provide a hail-proof rocket to solve the problems raised in the above background technology.
[0005] An anti-hail rocket, comprising: engine unit; An explosive unit, wherein the explosive unit is threadedly connected to the upper end of the engine unit, and the explosive unit includes an engine ignition device, a tail self-destruction cartridge, a middle self-destruction cartridge, a passivated RDX cartridge, and a connector. The lower portion of the connector is threadedly connected to the middle self-destruction cartridge, and the lower portion of the middle self-destruction cartridge is connected to the tail self-destruction cartridge via silicone rubber. The engine ignition device is fixed to the lower end of the tail self-destruction cartridge, and the lower portion of the engine ignition device extends into the engine unit. The passivated RDX cartridge is bonded to the inside of the connector via an adhesive. a control mechanism, the control mechanism being threadedly connected to an upper inner portion of the explosion unit; The warhead assembly is adhesively fixed to the upper end of the explosive unit.
[0006] Furthermore, the engine unit includes a tail fin, a plugging cover, a nozzle, a throat liner, a fiberglass combustion chamber, a lining and an engine charge, the lining is fixed to the inside of the fiberglass combustion chamber, the engine charge is bonded to the inside of the lining by an adhesive, the nozzle is located below the engine charge and is threadedly connected to the inside of the fiberglass combustion chamber, the plugging cover is installed inside the nozzle, the throat liner is bonded to the upper end of the nozzle by an adhesive and contacts the engine charge, and the tail fin is fixed to the nozzle surface by an adhesive.
[0007] Furthermore, a connecting screw is threadedly connected between the engine ignition device and the tail self-destruction box, the tail self-destruction box is threadedly connected to the upper part of the fiberglass reinforced plastic combustion chamber, and the engine ignition device is located inside the engine charge.
[0008] Furthermore, the control mechanism includes an acceleration safety mechanism, a slider, an electric detonator, a three-in-one chip, a detonating tube, a spring, a control box and a chip box. The control box is threadedly connected to the upper inner part of the connecting piece. The acceleration safety mechanism is installed inside the control box. The slider is slidably connected inside the control box and rests against the upper left side of the acceleration safety mechanism. The electric detonator is fixed to the center of the control box by adhesive. The electric detonator is located above the slider and contacts the slider. The detonating tube is fixed to the left side of the slider by adhesive. The spring is connected between the left end of the detonating tube and the inner wall of the control box.
[0009] Furthermore, the chip box is fixed on the top of the control box by adhesive, and the three-in-one chip is fixed on the chip box by adhesive.
[0010] Furthermore, the warhead assembly includes an arrow cone and a counterweight body, the arrow cone is fixed to the upper end of the connecting piece by adhesive, and the counterweight body is fixed inside the arrow cone by adhesive.
[0011] The beneficial effects of the present invention include: realizing artificial hail prevention by using a method for preventing hail by explosion, detecting and locating the position of hail clouds by radar, determining the explosion time in combination with the flight trajectory of a hail-prevention rocket, igniting high explosives by using a digital chip, causing explosion and self-destruction in the air, and finally dropping rocket debris to the ground as flocs weighing no more than 100g. In this way, the explosion range is large, and the impact range of the detonation wave generated by the explosion is ≥120m, which is equivalent to forming a spherical impact range with a diameter of 240m in the cloud layer. The rocket has a high safety factor, solves the risk of premature explosion of the engine, and the explosive part is safe and controllable for ground personnel. BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Figure 1 It is an overall schematic diagram of the present invention; Figure 2 This is a schematic diagram of the engine unit of the present invention; Figure 3This is a schematic diagram of the explosion unit of the present invention; Figure 4 Schematic diagram of the control mechanism of the present invention; Figure 5 Schematic diagram of the warhead assembly of the present invention.
[0013] In the figure: 1-engine unit, 2-explosive unit, 3-control mechanism, 4-warhead assembly, 5-tail, 6-blocking cover, 7-nozzle, 8-throat liner, 9-glass fiber reinforced plastic combustion chamber, 10-lining, 11-engine charge, 12-engine ignition device, 13-connecting screws, 14-tail self-destruction box, 15-middle self-destruction box, 16-passivated RDX charge, 17-connecting piece, 18-acceleration safety mechanism, 19-slider, 20-electric detonator, 21-three-in-one chip, 22-detonating tube, 23-spring, 24-control box, 25-chip box, 26-arrow cone, 27-counterweight. DETAILED DESCRIPTION
[0014] See also Figure 1-Figure 5 , an anti-hail rocket, comprising: An engine unit 1, comprising an empennage 5, a plugging cover 6, a nozzle 7, a throat liner 8, a fiberglass combustion chamber 9, a liner 10, and an engine charge 11. The liner 10 is fixed to the inside of the fiberglass combustion chamber 9, and the engine charge 11 is bonded to the inside of the liner 10 by adhesive. The nozzle 7 is located below the engine charge 11 and is threadedly connected to the inside of the fiberglass combustion chamber 9. The plugging cover 6 is installed inside the nozzle 7. The throat liner 8 is bonded to the upper end of the nozzle 7 by adhesive and contacts the engine charge 11. The empennage 5 is bonded to the surface of the nozzle 7 by adhesive, and the throat liner 8 is bonded to the nozzle 7 by adhesive. The bonded nozzle 7 is connected to the fiberglass combustion chamber 9 by threads, and the engine charge 11 is connected to the fiberglass combustion chamber 9 by adhesive. The empennage 5 is connected to the nozzle 7 by adhesive. Explosive unit 2, the explosive unit 2 is threadedly connected to the upper end of the engine unit 1, the explosive unit 2 includes an engine ignition device 12, a tail self-destruction cartridge 14, a middle self-destruction cartridge 15, a passivated RDX cartridge 16 and a connector 17, the lower portion of the connector 17 is threadedly connected to the middle self-destruction cartridge 15, the lower portion of the middle self-destruction cartridge 15 is connected to the tail self-destruction cartridge 14 through silicone rubber, the engine ignition device 12 is fixed to the lower end of the tail self-destruction cartridge 14, the lower portion of the engine ignition device 12 extends into the engine unit 1, and the passivated RDX cartridge 16 is bonded to the connector 17 by an adhesive. The engine ignition device 12 is threadedly connected to the tail self-destruction medicine box 14 with a connecting screw 13, and the tail self-destruction medicine box 14 is threadedly connected to the upper part of the glass fiber reinforced plastic combustion chamber 9. The engine ignition device 12 is located inside the engine charge 11, and the engine ignition device 12 is connected to the connecting screw 13 through a thread. The connecting screw 13 is connected to the tail self-destruction medicine box 14 through a thread. The tail self-destruction medicine box 14 is connected to the middle self-destruction medicine box 15 through silicone rubber. The connecting piece 17 is connected to the middle self-destruction medicine box 15 through a thread, and the passivated RDX charge 16 is connected to the connecting piece 17 through an adhesive; The control mechanism 3 is threadedly connected to the upper part of the explosive unit 2. The control mechanism 3 includes an acceleration safety mechanism 18, a slider 19, an electric detonator 20, a three-code-in-one chip 21, a detonating tube 22, a spring 23, a control box 24 and a chip box 25. The control box 24 is threadedly connected to the upper part of the connector 17. The acceleration safety mechanism 18 is installed inside the control box 24. The slider 19 is slidably connected to the inside of the control box 24 and against the left side above the acceleration safety mechanism 18. The electric detonator 20 is fixed to the center of the control box 24 by an adhesive. The electric detonator 20 is located above the slider 19 and contacts the slider 19. The detonating tube 22 is fixed to the left side of the slider 19 by an adhesive. The spring 2 3 is connected between the left end of the detonating tube 22 and the inner wall of the control box 24. The chip box 25 is fixed to the top of the control box 24 by adhesive. The three-in-one chip 21 is fixed to the chip box 25 by adhesive. The acceleration insurance mechanism 18 is freely placed in the control box 24. The slider 19 is also freely placed in the control box 24. The electric detonator 20 is connected to the control box 24 by adhesive. The three-in-one chip 21 is connected to the chip box 25 by adhesive. The detonating tube 22 is connected to the slider 19 by adhesive. The chip box 25 is connected to the control box 24 by adhesive. The rear end of the control box 24 is provided with an electric pin puller plugged into the slider 19. The lower end of the control box 24 is also provided with an output charge in contact with the passivated RDX charge column 16. The warhead assembly 4 is adhesively fixed to the upper end of the explosive unit 2. The warhead assembly 4 includes an arrow cone 26 and a counterweight 27. The arrow cone 26 is adhesively fixed to the upper end of the connecting member 17, and the counterweight 27 is adhesively fixed inside the arrow cone 26.
[0015] Working principle: After the rocket is mounted on the rack, it is connected to the wireless controller through the contact piece on the connector 17. The operator remotely reads the resistance value, angle and other parameters of the rocket through the wireless controller to judge the status of the rocket. After the direction of the hail cloud is detected by the radar, the launch elevation angle is adjusted according to the rocket trajectory diagram, and the explosion time is set, such as (20s). The three-code-in-one chip 21 is charged to prepare for launch, and the launch button is pressed to launch the rocket. At this time, the rocket prompts the engine ignition device 12 to ignite under the action of the electric energy signal of the three-code-in-one chip 21, stimulating the engine charge 11, and then realizing powered launch. At this time, the acceleration safety mechanism 18 is released due to over-flight. The rocket is loaded to a compressed state and no longer blocks the slider 19, leaving space for the slider 19 to move to the right. After a delay of 1s, the three-in-one chip 21 outputs electrical energy to trigger the electric pin puller to work and no longer resist the slider 19. The spring 23 pushes the slider 19 to move to the right. At this time, the detonating tube 22 moves to the right until it is aligned with the position of the electric detonator 20. At the same time, the three-in-one chip 21 determines that the rocket overload is normal. The rocket arrives in the hail cloud 20s after launch. The three-in-one chip 21 outputs an electrical signal to stimulate the electric detonator 20 and the middle self-destruction box 15 and the tail self-destruction box 14. The electric detonator 20 ignites the detonating tube 22 after a delay of 100ms. The detonating tube 22 points The deactivation RDX charge 16 is burned, the middle self-destruction medicine box 15 and the tail self-destruction medicine box 14 complete the disintegration of the middle and tail parts of the rocket, and the explosion of the deactivation RDX 16 completes the disturbance of the hail cloud and the blasting of the warhead. Finally, the rocket debris falls freely as flocs weighing no more than 100g, and the rocket work is completed. Because the anti-hail rocket has a control mechanism 3, and the control mechanism 3 has an acceleration safety mechanism 18, it can realize the retraction of the rocket only in the flight overload state, and the slider 19 can be aligned, so the deactivation RDX charge 16 in the rocket is always safe when on the ground, and the overload judgment of the three-in-one chip 21 after the pin pulling action can determine Whether the electric detonator 20 and the self-destruction box are working, the safety of the self-destruction box is guaranteed, thereby realizing artificial hail prevention through the method of explosion hail prevention, radar detecting and locating the direction of the hail cloud, determining the explosion time in combination with the flight trajectory of the hail prevention rocket, igniting the high explosive using a digital chip, exploding and self-destructing in the air, and finally the rocket debris falling to the ground as flocs no more than 100g. In this way, the explosion range is large, and the impact range of the detonation wave generated by the explosion is ≥120m, which is equivalent to forming a spherical impact range of 240m in diameter in the cloud. The rocket has a high safety factor, solves the risk of premature explosion of the engine, and the explosive part is safe and controllable for ground personnel.
Claims
1. A hail-proof rocket, characterized in that: include: Engine unit (1); An explosion unit (2), wherein the explosion unit (2) is threadedly connected to the upper end of the engine unit (1), and the explosion unit (2) includes an engine ignition device (12), a tail self-destruction medicine box (14), a middle self-destruction medicine box (15), a passivated RDX powder column (16) and a connecting piece (17), wherein the lower portion of the connecting piece (17) is threadedly connected to the middle self-destruction medicine box (15), and the lower portion of the middle self-destruction medicine box (15) is connected to the tail self-destruction medicine box (14) through silicone rubber, the engine ignition device (12) is fixed to the lower end of the tail self-destruction medicine box (14), the lower portion of the engine ignition device (12) extends into the engine unit (1), and the passivated RDX powder column (16) is bonded to the inside of the connecting piece (17) through an adhesive; A control mechanism (3), the control mechanism (3) being threadedly connected to the upper inner portion of the explosion unit (2); A warhead assembly (4), wherein the warhead assembly (4) is adhesively fixed to the upper end of the explosive unit (2).
2. The hail-proof rocket according to claim 1, characterized in that: The engine unit (1) comprises a tail fin (5), a plug cover (6), a nozzle (7), a throat liner (8), a glass fiber reinforced plastic combustion chamber (9), a lining (10) and an engine charge (11), wherein the lining (10) is fixed to the inner side of the glass fiber reinforced plastic combustion chamber (9), the engine charge (11) is bonded to the inner side of the lining (10) by an adhesive, the nozzle (7) is located below the engine charge (11) and is threadedly connected to the inside of the glass fiber reinforced plastic combustion chamber (9), the plug cover (6) is installed inside the nozzle (7), the throat liner (8) is bonded to the upper end of the nozzle (7) by an adhesive and contacts the engine charge (11), and the tail fin (5) is bonded to the surface of the nozzle (7) by an adhesive.
3. The anti-hail rocket according to claim 2, characterized in that: A connecting screw (13) is threadedly connected between the engine ignition device (12) and the tail self-destruction medicine box (14), and the tail self-destruction medicine box (14) is threadedly connected to the upper part of the glass fiber reinforced plastic combustion chamber (9). The engine ignition device (12) is located inside the engine charge (11).
4. The anti-hail rocket according to claim 1, characterized in that: The control mechanism (3) includes an acceleration safety mechanism (18), a slider (19), an electric detonator (20), a three-code-in-one chip (21), a detonating tube (22), a spring (23), a control box (24) and a chip box (25). The control box (24) is threadedly connected to the upper inner portion of the connector (17). The acceleration safety mechanism (18) is installed inside the control box (24). The slider (19) is slidably connected inside the control box (24) and abuts against the left upper portion of the acceleration safety mechanism (18). The electric detonator (20) is fixed to the center of the control box (24) by adhesive. The electric detonator (20) is located above the slider (19) and contacts the slider (19). The detonating tube (22) is fixed to the left of the slider (19) by adhesive. The spring (23) is connected between the left end of the detonating tube (22) and the inner wall of the control box (24).
5. The anti-hail rocket according to claim 4, characterized in that: The chip box (25) is fixed on the top of the control box (24) by adhesive bonding, and the three-in-one chip (21) is fixed on the chip box (25) by adhesive bonding.
6. The anti-hail rocket according to claim 1, characterized in that: The warhead assembly (4) comprises an arrow cone (26) and a counterweight (27), wherein the arrow cone (26) is fixed to the upper end of the connecting member (17) by adhesive bonding, and the counterweight (27) is fixed inside the arrow cone (26) by adhesive bonding.