A spreading device for artificial rainmaking hail-prevention rocket

Abstract

The utility model discloses a kind of artificial rainmaking hail prevention rocket bomb is used to scatter device, comprising: shell structure, gas generation system, catalyst storage release system and airflow uniform distribution system. Shell structure is composed of outer shell and inner lining, outer shell both ends are equipped with front connecting flange and rear connecting flange, and inner lining is high-temperature-resistant ceramic composite material. Gas generation system includes multiple propellant grain units and ignition controller, propellant grain unit is arranged along axial interval and is separated by isolating ring. Catalyst storage release system includes multiple catalyst bins and release control mechanism, catalyst bin is evenly distributed peripherally, and release control mechanism includes baffle assembly and drive unit. Airflow uniform distribution system includes flow guide cover and flow uniform plate, and flow guide cover is conical structure, and multiple flow uniform holes are set on flow uniform plate. The device realizes the sectional timing release of catalyst by independently controlled propellant grain unit and catalyst bin, and airflow uniform distribution system ensures the uniform scattering of catalyst particle.

Description

Technical Field

[0001] This utility model relates to the technical field of weather modification equipment, and in particular to a seeding device for artificial rain enhancement and hail suppression rockets. Background Technology

[0002] Artificial rainmaking and hail suppression rockets are important tools in meteorological intervention operations, with their core component being a catalyst-laden dispersing device. In existing technologies, such dispersing devices typically employ a simple shell structure with a central propellant grain burning to generate combustion gases, which are then injected into the clouds through openings in the shell. However, this design has inherent flaws. Uneven distribution of the combustion gas flow field within the shell leads to insufficient uniformity in catalyst particle dispersion, affecting nucleation efficiency. Furthermore, the linear combustion mode of the central propellant grain makes it difficult to achieve segmented or timed catalyst release, limiting precise control of the operation. In addition, under high-speed flight conditions, the structural integrity of traditional devices is susceptible to external airflow loads, posing a risk of shell rupture or premature catalyst leakage. Current dispersing device designs have shortcomings in terms of catalyst release uniformity, controllability, and device reliability. Utility Model Content

[0003] The purpose of this utility model is to provide a spraying device for rockets used in artificial rainmaking and hail suppression, which solves the problems mentioned in the background art.

[0004] This invention is implemented as follows: a dispersing device for rockets used in artificial rainmaking and hail suppression includes a shell structure, a gas generation system, a catalyst storage and release system, and an airflow distribution system. The shell structure includes an outer shell and an inner liner. The outer shell is a cylindrical structure with a front connecting flange and a rear connecting flange at both ends. The inner liner is located on the inner wall of the outer shell and is made of high-temperature resistant ceramic composite material. The gas generation system includes multiple propellant units and an ignition controller. The multiple propellant units are spaced apart axially along the shell structure, and each propellant unit is separated from adjacent units by an isolation ring. The ignition controller is located at the rear of the shell structure and is connected to each propellant unit via wires. The catalyst storage and release system includes multiple catalyst chambers and a release control mechanism. The multiple catalyst chambers are evenly distributed circumferentially along the shell structure, and each catalyst chamber contains a catalyst receiving cavity. The release control mechanism includes multiple baffle assemblies and a drive unit. The baffle assemblies are located at the catalyst chamber outlets, and the drive unit is drively connected to the baffle assemblies. The airflow distribution system includes a flow guide and a flow equalization plate. The flow guide is located at the front end of the shell structure and has a conical shape. The flow equalization plate is located behind the flow guide and has multiple flow equalization holes on its body.

[0005] Both the front and rear connecting flanges of the outer casing have annular sealing grooves on their sealing surfaces, within which metal sealing rings are installed. Reinforcing rings are provided on the outer surface of the outer casing, evenly spaced along the axial direction. The inner lining layer is three to five millimeters thick and is bonded to the inner wall of the outer casing using a high-temperature adhesive.

[0006] The propellant unit of the gas generating system includes a propellant body and a coating layer. The propellant body is a cylindrical structure, composed of a mixture of potassium perchlorate and metallic fuel. The coating layer, made of flame-retardant rubber, covers the outer surface of the propellant body. The isolation ring is an annular plate structure, with its outer edge contacting the inner wall of the inner lining layer, and a vent hole in its center. The ignition controller includes a control circuit board and multiple ignition heads. The control circuit board is fixed inside the housing structure by a bracket, and the ignition heads are connected to the ignition propellant of each propellant unit via wires.

[0007] The catalyst storage and release system's catalyst chamber is made of corrosion-resistant aluminum alloy and has a fan-shaped cross-section. A release port is located at the bottom of the catalyst container, and a filter screen is installed at the release port. The baffle assembly includes a baffle body and a rotating shaft; the baffle body is hinged to the edge of the release port via the rotating shaft. The drive unit is a micro-motor, and its output shaft is connected to the rotating shaft of the baffle body via a linkage mechanism. The release control mechanisms of multiple catalyst chambers are independently controlled.

[0008] The airflow distribution system's shroud has a pointed, conical front end, and its rear end is threadedly connected to the front end of the outer casing. Multiple pressure-reducing holes are formed on the surface of the shroud. The flow distribution plate is a perforated plate structure with a thickness of two millimeters, and the flow distribution holes are arranged in a honeycomb pattern. The edge of the flow distribution plate is fixedly connected to the inner wall of the outer casing using retaining rings.

[0009] The housing structure also houses a pressure balancing device. This device includes a pressure sensor and a pressure relief valve. The pressure sensor is located on the inner wall of the housing structure, with its probe extending into the internal cavity. The pressure relief valve is mounted on the side wall of the housing, and its valve core engages with the valve seat via a spring.

[0010] In the gas generation system, multiple propellant units are ignited sequentially according to a preset time sequence. The gas generated by the combustion of each propellant unit is propelled forward through the vents of the isolation ring. In the catalyst storage and release system, after the corresponding propellant unit is ignited, the baffle assembly in each catalyst chamber is opened by the drive unit to achieve segmented release of the catalyst. The airflow distribution system's guide shroud and flow equalization plate rectify and homogenize the high-speed airflow, ensuring uniform dispersion of catalyst particles.

[0011] This invention relates to a spraying device for rocket-borne artificial rainmaking and hail suppression. By incorporating multiple independently controlled propellant units and a catalyst chamber, it achieves segmented, timed catalyst release. An airflow distribution system effectively improves the gas flow field distribution, enhancing the uniformity of catalyst spraying. A reinforced structural design and pressure balancing device ensure the reliability and safety of the device during high-speed flight. This device significantly improves the effectiveness and controllability of artificial rainmaking and hail suppression operations.

[0012] As a further improvement, reinforcing ribs are pre-embedded inside the reinforcing ring of the outer shell. The reinforcing ribs have a mesh structure and are made of the same material as the outer shell.

[0013] As a further improvement, the inner surface of the liner is provided with a wear-resistant coating. The wear-resistant coating is made of silicon carbide and has a thickness of 0.5 mm.

[0014] As a further improvement, a buffer layer is provided between the propellant units of the gas generation system. The buffer layer is made of porous ceramic material and is two millimeters thick.

[0015] As a further improvement, the catalyst storage and release system is equipped with a stirrer inside the catalyst chamber. The stirrer has a helical blade structure and is driven by a micro motor.

[0016] As a further improvement, the surface of the airflow distribution system's shroud is coated with an antistatic coating. The antistatic coating is made of a conductive polymer material.

[0017] As a further improvement, a protective mesh is installed at the outlet of the pressure relief valve of the pressure balancing device. The protective mesh is made of stainless steel wire mesh with a mesh size of one millimeter.

[0018] As a further improvement, a stabilizing fin is provided at the tail of the shell structure. There are four stabilizing fins, evenly distributed along the circumference, and they are made of high-strength composite material.

[0019] As a further improvement, the ignition controller's control circuit board integrates a timing control module. The timing control module sets the ignition sequence and time interval of each propellant unit through programming.

[0020] As a further improvement, the drive unit of the catalyst storage and release system is equipped with a position sensor. The position sensor is used to detect the opening angle of the baffle assembly.

[0021] As a further improvement, the outer surface of the housing is coated with a heat-protective layer. The heat-protective layer is made of silicone rubber and is two millimeters thick.

[0022] This invention relates to a seeding device for rocket-propelled artificial rainmaking and hail suppression. Through its unique structural design, it effectively solves the technical challenges of traditional seeding devices in terms of catalyst release uniformity, controllability, and structural reliability. The segmented gas generation system and independently controlled catalyst chamber achieve precise release control, while the optimized airflow distribution system ensures uniform distribution of catalyst particles. The reinforced structural design guarantees the device's operational stability in harsh environments. This device features a reasonable structure, precise control, and high reliability, significantly improving the scientific rigor and effectiveness of artificial rainmaking and hail suppression operations. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0024] Figure 2 This is a cross-sectional view of the internal structure of this utility model;

[0025] Figure 3 This is a structural diagram of the catalyst storage and release system in this utility model;

[0026] Figure 4 This is a structural diagram of the gas generation system in this utility model.

[0027] Explanation of reference numerals in the attached drawings: 1. Shell structure; 2. Gas generation system; 3. Catalyst storage and release system; 4. Airflow distribution system; 5. Outer shell; 6. Inner liner; 7. Front connecting flange; 8. Rear connecting flange; 9. Propellant unit; 10. Ignition controller; 11. Catalyst chamber; 12. Release control mechanism; 13. Flow guide; 14. Flow equalization plate; 15. Isolation ring; 16. Propellant body; 17. Coating layer; 18. Baffle assembly; 19. Drive unit; 20. Flow equalization orifice; 21. Reinforcing ring; 22. Vent; 23. Control circuit board; 24. Ignition head; 25. Catalyst containment chamber; 26. Release port; 27. Filter screen; 28. Baffle body; 29. ​​Rotating shaft; 30. Pressure reducing hole; 31. Pressure balancing device; 32. Pressure sensor; 33. Pressure relief valve; 34. Reinforcing rib; 35. Wear-resistant coating; 36. Buffer layer; 37. Stirrer. Detailed Implementation

[0028] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Those skilled in the art should understand that the embodiments described below are only some, not all, of the embodiments of the present utility model. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0029] Example 1

[0030] Please see Figures 1 to 4 This invention provides a spraying device for rockets used in artificial rainmaking and hail suppression, which mainly includes a shell structure 1, a gas generation system 2, a catalyst storage and release system 3, and an airflow distribution system 4. The shell structure 1 forms the overall frame and support of the device, housing and protecting the other systems. The gas generation system 2, located inside the shell structure 1, generates high-temperature, high-pressure gas as the power source for catalyst release. The catalyst storage and release system 3, also located inside the shell structure 1, stores the catalyst and releases it according to preset instructions. The airflow distribution system 4, located at the front end of the shell structure 1, rectifyes and homogenizes the gas flow field to achieve uniform catalyst spraying.

[0031] Specifically, the shell structure 1 includes an outer shell 5 and an inner liner 6. The outer shell 5 is a cylindrical structure made of aerospace-grade high-strength aluminum alloy or carbon fiber composite material through precision CNC machining or winding molding. Its outer diameter is approximately 80 mm to 150 mm, its length is approximately 300 mm to 600 mm, and its wall thickness is approximately 2 mm to 4 mm, exhibiting excellent pressure resistance and impact resistance. A front connecting flange 7 and a rear connecting flange 8 are respectively provided at both ends of the outer shell 5. Both the front connecting flange 7 and the rear connecting flange 8 are made of high-strength stainless steel or titanium alloy and are firmly connected to the two ends of the outer shell 5 by circumferential welding or threaded connection. Their sealing surfaces are precision ground and have annular sealing grooves. The annular sealing grooves have a rectangular cross-section, a width of approximately 3 mm, and a depth of approximately 2 mm. A metal sealing ring is installed inside the annular sealing groove. The metal sealing ring is made of elastic stainless steel or nickel-based alloy and has excellent high-temperature and high-pressure sealing performance. Multiple reinforcing rings 21 are provided on the outer surface of the outer shell 5. The reinforcing ring 21 is made of high-strength aluminum alloy or carbon fiber composite material, and has a ring-shaped structure with a rectangular cross-section. Its width is approximately 10 mm to 15 mm, and its thickness is approximately 2 mm to 3 mm. It is firmly connected to the outer surface of the outer shell 5 by bonding or riveting, and is evenly distributed along the axial direction of the outer shell 5 at intervals of approximately 50 mm to 80 mm. This enhances the radial stiffness and bending resistance of the outer shell 5. The inner lining layer 6 is disposed on the inner wall of the outer shell 5. Its material is a high-temperature resistant ceramic composite material, such as alumina fiber-reinforced aluminum silicate-based composite material, with a thickness of three to five mm. It is tightly connected to the inner wall of the outer shell 5 by a high-temperature adhesive, forming a layer that is resistant to ablation and provides heat insulation, protecting the outer shell 5 from direct corrosion by the high temperature of the combustion gas.

[0032] The gas generating system 2 includes multiple propellant units 9 and an ignition controller 10. The multiple propellant units 9 are arranged axially along the housing structure 1, typically three to five units, each cylindrical. Each propellant unit 9 is separated from adjacent units by an isolation ring 15. Each propellant unit 9 includes a propellant body 16 and a coating layer 17. The propellant body 16 is a cylindrical structure with an outer diameter of approximately 30 mm to 60 mm and a length of approximately 50 mm to 100 mm. Its composition is a mixture of potassium perchlorate and metallic fuel (such as aluminum or magnesium powder), formed by pressing or casting, exhibiting a stable combustion rate and high gas production characteristics. The coating layer 17 wraps around the outer surface of the propellant body 16, and its material is flame-retardant rubber or polyurethane composite material, with a thickness of approximately 1 mm to 2 mm. It is used to control the combustion surface of the propellant body, ensuring that the propellant body burns in a preset direction and at a predetermined rate. The isolation ring 15 is an annular plate structure made of high-temperature resistant stainless steel or ceramic material. Its outer edge is in close contact with the inner wall of the inner lining layer 6 and is sealed by an interference fit or a high-temperature resistant sealing ring, forming independent gas chambers between each propellant unit 9. A vent 22 is provided at the center of the isolation ring 15. The vent 22 is circular with a diameter of approximately 10 mm to 20 mm, used to guide the gas produced by the combustion of the previous propellant unit 9 to the next chamber or the dispensing outlet. The ignition controller 10 is located at the rear of the housing structure 1, typically within the internal space of the rear connecting flange 8, and is connected to each propellant unit 9 via wires. The ignition controller 10 includes a control circuit board 23 and multiple ignition heads 24. The control circuit board 23 consists of a high-temperature resistant integrated circuit and a microprocessor, and is fixed inside the housing structure 1 by a bracket made of high-strength heat-resistant material to ensure the stability of the circuit board under high-temperature vibration environments. The ignition head 24 is an electric detonator or electric igniter, which is electrically connected to the control circuit board 23 through a high-temperature resistant insulated wire, and is connected to the ignition powder (such as black powder or sensitive mixture) of each of the propellant column units 9 through physical contact or close arrangement, for receiving ignition signals and rapidly igniting the propellant column 16.

[0033] The catalyst storage and release system 3 includes multiple catalyst chambers 11 and a release control mechanism 12. The multiple catalyst chambers 11 are evenly distributed circumferentially along the shell structure 1, typically six to eight chambers, arranged in a fan or wedge shape around the periphery of the gas generating system 2. Each catalyst chamber 11 is made of corrosion-resistant aluminum alloy, formed by precision casting or CNC machining, and has a fan-shaped cross-section, forming a tight fit with the inner wall of the outer shell 5 and adjacent catalyst chambers. Each catalyst chamber 11 has a catalyst receiving cavity 25, which is a fan-shaped cylindrical space used to store catalyst particles for artificial rainmaking and hail suppression, such as silver iodide or dry ice particles. A release port 26 is provided at the bottom of the catalyst receiving cavity 25. The release port 26 is rectangular or elliptical, with its long side parallel to the axis of the shell structure 1, a width of approximately 10 to 20 millimeters, and a length of approximately 30 to 50 millimeters. A filter screen 27 is installed at the release port 26. The filter screen 27 is made of stainless steel wire mesh, and the mesh size is determined according to the size of the catalyst particles, for example, 0.5 mm to 1 mm. It is used to prevent accidental leakage of catalyst particles before release and to ensure that the released particles are of uniform size. The release control mechanism 12 includes multiple baffle assemblies 18 and a drive unit 19. The baffle assembly 18 is located at the outlet of the catalyst chamber 11 and is usually a rotating baffle. The baffle assembly 18 includes a baffle body 28 and a rotating shaft 29. The baffle body 28 is made of corrosion-resistant stainless steel or titanium alloy and is rectangular in shape, with its size slightly larger than the release port 26. The baffle body 28 is hinged to the edge of the release port 26 by the rotating shaft 29. The rotating shaft 29 is a precision-machined stainless steel round shaft, and its two ends are supported on the side wall of the catalyst chamber 11 by bearing seats to achieve smooth rotation of the baffle body 28. The drive unit 19 is a compact micro-motor, typically a stepper motor or a DC geared motor, bolted to the outer wall of the catalyst chamber 11. Its output shaft is connected to the rotating shaft 29 of the baffle body 28 via a linkage mechanism composed of high-strength stainless steel connecting rods and pins, converting the rotational motion of the micro-motor into the opening or closing motion of the baffle body 28. The release control mechanisms 12 of the multiple catalyst chambers 11 are independently controlled, and each drive unit 19 is electrically connected to the ignition controller 10.

[0034] The airflow equalization system 4 includes a shroud 13 and a flow equalization plate 14. The shroud 13 is located at the front end of the shell structure 1. Its front end is a pointed cone shape, precision-machined from high-strength aluminum alloy or composite materials, with a cone angle of approximately 20 to 30 degrees to reduce air resistance. Its rear end is tightly connected to the front end of the outer shell 5 via a threaded connection. The surface of the shroud 13 has multiple pressure-reducing holes 30, which are circular with a diameter of approximately 5 to 10 millimeters and evenly distributed along the conical surface of the shroud 13 to balance the air pressure inside and outside the shroud, preventing damage during high-speed flight. The flow equalization plate 14 is located behind the shroud 13, typically at the entrance of the outer shell 5. The plate is two millimeters thick and made of high-temperature resistant alloy or porous ceramic material. Multiple flow equalization holes 20 are formed on the plate. These holes are arranged in a honeycomb pattern, with a diameter of approximately 3 to 5 millimeters and a spacing of approximately 1 millimeter, to further rectify and equalize the airflow passing through the shroud 13. The edge of the flow equalization plate 14 is fixedly connected to the inner wall of the outer shell 5 by a retaining ring. The retaining ring is fixed by an elastic steel ring or bolts to ensure that the flow equalization plate 14 remains stable under the impact of airflow.

[0035] The housing structure 1 is also equipped with a pressure balancing device 31. The pressure balancing device 31 includes a pressure sensor 32 and a pressure relief valve 33. The pressure sensor 32 is a high-temperature and high-pressure piezoresistive sensor with a measurement range of approximately 0 to 10 MPa. It is located on the inner wall of the middle part of the housing structure 1, and its probe extends into the internal cavity to monitor the internal air pressure of the housing in real time. The pressure relief valve 33 is installed on the side wall of the outer shell 5 and is made of high-temperature resistant alloy material. Its valve seat is connected to the outer shell 5 by welding or threading, and its valve core cooperates with the valve seat through a spring. The preload of the spring is precisely calibrated. When the internal pressure of the housing exceeds a preset safety threshold, the pressure relief valve 33 automatically opens to discharge excess gas and protect the integrity of the housing structure 1.

[0036] When this device is in operation, the multiple propellant units 9 of the gas generating system 2 are ignited sequentially according to a preset time sequence. The ignition controller 10 sends an electrical signal to the corresponding ignition head 24 according to a preset program to ignite the propellant body 16. The gas generated by the combustion of each propellant unit 9 is propelled forward through the vent 22 of the isolation ring 15, forming a continuous or segmented gas flow. After the corresponding propellant unit 9 is ignited, each catalyst chamber 11 of the catalyst storage and release system 3 sends a command to the corresponding drive unit 19 by the ignition controller 10. The drive unit 19 drives the baffle body 28 of the baffle assembly 18 to open, so that the catalyst particles in the catalyst receiving chamber 25 are sprayed out from the release port 26, realizing the segmented release of the catalyst. The sprayed catalyst particles mix with the gas flow. Under the action of the flow guide shroud 13 and flow equalization plate 14 of the airflow equalization system 4, the high-speed airflow is rectified and homogenized, ensuring that the catalyst particles can be evenly distributed to the target airspace.

[0037] Example 2

[0038] In another embodiment of this utility model, a reinforcing rib 34 is pre-embedded inside the reinforcing ring 21 of the outer shell 5. The reinforcing rib 34 is composed of high-strength carbon fiber bundles or a stainless steel mesh structure, and its material is the same as that of the outer shell 5. It is pre-embedded inside the reinforcing ring 21 by winding or welding, and is integrally formed with the reinforcing ring 21 material, further enhancing the radial stiffness and torsional resistance of the reinforcing ring 21, and improving the structural stability of the device under high-speed flight and high overload conditions. Other structures in this embodiment are basically the same as in Embodiment 1, and will not be described again here.

[0039] Example 3

[0040] In another embodiment of this utility model, a wear-resistant coating 35 is provided on the inner surface of the liner layer 6. The wear-resistant coating 35 is made of silicon carbide and is uniformly coated on the inner surface of the liner layer 6 by plasma spraying or chemical vapor deposition (CVD) processes. Its thickness is 0.5 mm, forming a protective layer with extremely high hardness and wear resistance, effectively resisting the erosion and abrasion of high-speed particles in the combustion gas, and extending the service life of the liner layer 6. The other structures of this embodiment are basically the same as in Embodiment 1, and will not be described again here.

[0041] Example 4

[0042] In another embodiment of this utility model, a buffer layer 36 is provided between the propellant units 9 of the gas generating system 2. The buffer layer 36 is made of a porous ceramic material, such as porous alumina or silicon nitride ceramic, with a thickness of two millimeters, and is arranged in annular sheet shape on both sides of each isolation ring 15. It is used to absorb the vibration and impact generated during the combustion of the propellant units 9, and serves as an additional heat insulation layer to prevent premature ignition between the propellant units, thereby improving the safety of the system. Other structures in this embodiment are basically the same as in Embodiment 1, and will not be described again here.

[0043] Example 5

[0044] In another embodiment of this invention, a stirrer 37 is provided inside the catalyst chamber 11 of the catalyst storage and release system 3. The stirrer 37 has a helical blade structure, made of corrosion-resistant stainless steel or titanium alloy, with its blades spirally distributed along the axis of rotation. It is driven by a micro-motor integrated into the side wall of the catalyst chamber 11, with its output shaft extending into the catalyst receiving cavity 25. This micro-motor is used to stir the catalyst particles before or during release, preventing particle agglomeration or bridging, and ensuring smooth and uniform release of the catalyst. Other structures in this embodiment are basically the same as in Embodiment 1, and will not be described again here.

[0045] Example 6

[0046] In another embodiment of this invention, the surface of the airflow distribution system 4's guide shroud 13 is coated with an antistatic coating. The antistatic coating is a conductive polymer material, such as polyaniline or polypyrrole, and is uniformly coated on the inner and outer surfaces of the guide shroud 13 by spraying or brushing. Its thickness is approximately 0.1 mm to 0.3 mm. This coating is used to dissipate static charges generated by the friction between the high-speed airflow and powder particles, preventing static electricity accumulation from causing sparks or affecting the uniform distribution of catalyst particles. Other structures in this embodiment are basically the same as in Embodiment 1, and will not be described again here.

[0047] Example 7

[0048] In another embodiment of this utility model, a protective net is provided at the outlet of the pressure relief valve 33 of the pressure balancing device 31. The protective net is made of high-temperature resistant stainless steel wire mesh with a mesh size of one millimeter. It is fixed to the outlet end of the pressure relief valve 33 by welding or riveting to prevent large particles or fragments of the propellant from being discharged with the gas during pressure relief, while ensuring the smooth release of the gas. The other structures of this embodiment are basically the same as those in Embodiment 1, and will not be described again here.

[0049] Example 8

[0050] In another embodiment of this utility model, a stabilizing wing is provided at the tail of the shell structure 1. The stabilizing wing consists of four pieces, made of high-strength carbon fiber composite material, with rectangular or trapezoidal wing surfaces, evenly distributed circumferentially at the tail of the outer shell 5, and fixed to the outer shell 5 by bolt connection or integral molding. The stabilizing wing provides aerodynamic stability during flight, ensuring the stability of the rocket's flight attitude and improving the accuracy of catalyst dispersal. Other structures in this embodiment are basically the same as in Embodiment 1, and will not be described again here.

[0051] Example 9

[0052] In another embodiment of this invention, the control circuit board 23 of the ignition controller 10 integrates a timing control module. This timing control module consists of a dedicated programmable logic device (such as an FPGA) or microcontroller. It sets the ignition sequence and time interval of each propellant column unit 9 through programming. The time interval can be precisely adjusted between milliseconds and seconds, achieving a high degree of controllability in the catalyst release timing to adapt to different weather conditions and dissemination requirements. Other structures in this embodiment are basically the same as in Embodiment 1, and will not be described again here.

[0053] Example 10

[0054] In another embodiment of this invention, the drive unit 19 of the catalyst storage and release system 3 is equipped with a position sensor. The position sensor is a miniature Hall effect sensor or a photoelectric encoder, installed near the output shaft of the drive unit 19 or the rotating shaft 29 of the baffle body 28. It is used to detect the opening angle of the baffle assembly 18 in real time and feed the angle signal back to the ignition controller 10 to precisely control the release amount and rate of the catalyst. Other structures in this embodiment are basically the same as in Embodiment 1, and will not be described again here.

[0055] Example 11

[0056] In another embodiment of this utility model, the outer surface of the outer shell 5 is coated with a heat-protective layer. The heat-protective layer is made of silicone rubber and is two millimeters thick. It is uniformly coated on the outer surface of the outer shell 5 by spraying or molding, and has excellent high-temperature resistance and heat insulation properties, protecting the outer shell 5 from aerodynamic heating during the high-speed flight of the rocket. It also serves as an anti-corrosion layer. Other structures in this embodiment are basically the same as in Embodiment 1, and will not be described again here.

[0057] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A seeding device for rocket-propelled artificial rainmaking and hail suppression, comprising: The shell structure (1) is characterized in that the shell structure (1) includes an outer shell (5) and an inner liner (6); the outer shell (5) is a cylindrical structure with a front connecting flange (7) and a rear connecting flange (8) respectively provided at both ends; the inner liner (6) is disposed on the inner wall of the outer shell (5) and its material is a high-temperature resistant ceramic composite material; the device also includes a gas generating system (2), the gas generating system (2) includes multiple propellant units (9) and an ignition controller (10); the multiple propellant units (9) are arranged along... The shell structure (1) is axially spaced, and each of the propellant grain units (9) is separated from adjacent units by an isolation ring (15); the ignition controller (10) is located at the tail of the shell structure (1) and is connected to each propellant grain unit (9) by a wire; the device also includes a catalyst storage and release system (3), which includes multiple catalyst chambers (11) and a release control mechanism (12); the multiple catalyst chambers (11) are evenly distributed circumferentially along the shell structure (1), and each of the catalyst chambers (11) The device is equipped with a catalyst receiving chamber (25) inside; the release control mechanism (12) includes multiple baffle assemblies (18) and a drive unit (19); the baffle assembly (18) is located at the outlet of the catalyst chamber (11), and the drive unit (19) is connected to the baffle assembly (18) in a transmission manner; the device also includes an airflow equalization system (4), which includes a flow guide hood (13) and a flow equalization plate (14); the flow guide hood (13) is located at the front end of the shell structure (1) and has a conical structure; the flow equalization plate (14 ... the drive unit (19) is connected to the catalyst receiving chamber (11) in a transmission manner; the release control mechanism (12) includes multiple baffle assemblies (18) and a drive unit (19); the release control mechanism (12) includes multiple baffle assemblies (18) and a drive unit (19) in a transmission manner; the release control mechanism (12) includes multiple baffle assemblies (18) and a drive unit (19) in a transmission manner; the release control mechanism (12) includes multiple baffle assemblies (18) and a drive unit (19) in a transmission manner; the release control mechanism (12) includes multiple baffle assemblies (18) and a drive unit (19) in a transmission manner; the release control mechanism (12) includes The plate (14) is located behind the flow guide (13), and multiple flow equalization holes (20) are opened on its plate body; the sealing surfaces of the front connecting flange (7) and the rear connecting flange (8) of the outer shell (5) are provided with annular sealing grooves, and metal sealing rings are installed in the annular sealing grooves; the outer surface of the outer shell (5) is provided with reinforcing rings (21), and the reinforcing rings (21) are distributed at equal intervals along the axial direction of the outer shell (5); the thickness of the inner lining layer (6) is three to five millimeters, and it is connected to the inner wall of the outer shell (5) by a high-temperature adhesive.

2. The seeding device for artificial rainmaking and hail suppression rockets according to claim 1, characterized in that, The propellant column unit (9) includes a propellant column body (16) and a covering layer (17); the propellant column body (16) is a cylindrical structure, and its composition is a mixture of potassium perchlorate and metallic fuel; the covering layer (17) is wrapped around the outer surface of the propellant column body (16), and its material is flame-retardant rubber; the isolation ring (15) is an annular plate structure, and its outer edge contacts the inner wall of the inner lining layer (6), and a vent hole (22) is opened in the center of the isolation ring (15); the ignition controller (10) includes a control circuit board (23) and multiple ignition heads (24); the control circuit board (23) is fixed inside the housing structure (1) by a bracket, and the ignition heads (24) are connected to the ignition propellant of each propellant column unit (9) by wires.

3. The seeding device for artificial rainmaking and hail suppression rockets according to claim 1, characterized in that, The catalyst chamber (11) is made of corrosion-resistant aluminum alloy and has a fan-shaped cross-section. The bottom of the catalyst receiving cavity (25) is provided with a release port (26) and a filter screen (27) is installed at the release port (26). The baffle assembly (18) includes a baffle body (28) and a rotating shaft (29). The baffle body (28) is hinged to the edge of the release port (26) through the rotating shaft (29). The drive unit (19) is a micro motor, and its output shaft is connected to the rotating shaft (29) of the baffle body (28) through a linkage mechanism. The release control mechanism (12) of the multiple catalyst chambers (11) is independently controlled.

4. The seeding device for artificial rainmaking and hail suppression rockets according to claim 1, characterized in that, The front end of the flow guide (13) is a pointed cone shape, and its rear end is connected to the front end of the outer shell (5) by a thread; the surface of the flow guide (13) is provided with multiple pressure reducing holes (30); the flow equalization plate (14) is a porous plate structure with a plate thickness of two millimeters, and the flow equalization holes (20) are arranged in a honeycomb pattern; the edge of the flow equalization plate (14) is fixedly connected to the inner wall of the outer shell (5) by a retaining ring.

5. The seeding device for artificial rainmaking and hail suppression rockets according to claim 1, characterized in that, The housing structure (1) is also equipped with a pressure balancing device (31); the pressure balancing device (31) includes a pressure sensor (32) and a pressure relief valve (33); the pressure sensor (32) is located on the inner wall of the middle part of the housing structure (1), and its probe extends into the internal cavity; the pressure relief valve (33) is installed on the side wall of the outer shell (5), and its valve core cooperates with the valve seat through a spring.

6. The seeding device for artificial rainmaking and hail suppression rockets according to claim 1, characterized in that, The reinforcing ring (21) of the outer shell (5) has a reinforcing rib (34) embedded inside; the reinforcing rib (34) has a mesh structure and its material is the same as that of the outer shell (5); the inner surface of the inner lining layer (6) is provided with a wear-resistant coating (35); the wear-resistant coating (35) is made of silicon carbide and its thickness is 0.5 mm.

7. The seeding device for artificial rainmaking and hail suppression rockets according to claim 1, characterized in that, A buffer layer (36) is provided between the propellant column units (9) of the gas generation system (2); the buffer layer (36) is a porous ceramic material with a thickness of two millimeters; a stirrer (37) is provided in the catalyst chamber (11) of the catalyst storage and release system (3); the stirrer (37) is a spiral blade structure and is driven by a micro motor.

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