A silhouette rocket projectile with accurate control
By using precise control of the timing controller and multi-segment self-destruct components, the problem of inaccurate self-destruction of the artificial weathering rocket was solved, achieving precise catalyst dissemination and safe segmented self-destruction of the rocket, ensuring successful operation and resource conservation.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- BEIJING HOULIDE INSTR CO LTD
- Filing Date
- 2026-05-28
- Publication Date
- 2026-06-30
AI Technical Summary
The existing artificial rainmaking rockets have inaccurate self-destruct control in multiple stages, which prevents the catalyst from being properly spread, causing rain enhancement and hail suppression operations to fail, and also resulting in the waste of ammunition and manpower.
The system employs a precisely controllable artificial rocket, which uses a timing controller to ignite the catalytic flammable agent using a flammable agent igniter. It also utilizes the different timing sequences of multiple self-destruct components and projectile components to ensure that the catalyst is accurately dispersed and then self-destructs in stages. A double self-destruction igniter is set up to prevent accidents caused by unignited self-destruct components.
It achieved precise catalyst dissemination and safe segmented self-destruction of rockets, ensuring that debris fragments were less than 100g, avoiding harm to personnel, improving the success rate of operations and saving resources.
Smart Images
Figure CN122305866A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of weather modification technology, and in particular to a precisely controllable weather modification rocket. Background Technology
[0002] Weather modification is the use of technology to artificially influence the physical and chemical processes of the local atmosphere under appropriate conditions, in order to achieve purposes such as increasing rainfall and snowfall, preventing hail, dissipating rain, dispelling fog, and preventing frost. Weather modification rockets are launched from the ground, carrying catalysts such as silver iodide into clouds, causing water vapor to condense into water droplets or ice crystals, thereby increasing rainfall or mitigating the impact of meteorological disasters such as hail.
[0003] However, the core mission of rainmaking rockets is to precisely deliver the catalytic smoke agent to the target cloud level and complete its dispersal. If the multi-stage self-destruct control is inaccurate and premature detonation occurs, the rocket will disintegrate before reaching the effective operational altitude, preventing the catalyst from being properly dispersed. This directly leads to the failure of rain enhancement and hail suppression operations, resulting in a waste of ammunition and manpower. Therefore, precise control of the multi-stage self-destruct is extremely important.
[0004] Therefore, it is necessary to solve the above problems by using a precisely controllable shadow rocket. Summary of the Invention
[0005] The purpose of this invention is to provide a precisely controllable manipulator rocket to solve the problems mentioned in the background art.
[0006] To achieve the above objectives, the present invention provides the following technical solution: a precisely controllable manned rocket projectile includes a rocket body, a cone-shaped shell, and blade-shaped tail fins. The cone-shaped shell is located at one end of the rocket body, and the blade-shaped tail fins are located on the outer circumferential surface of the rocket body at the end away from the cone-shaped shell. The cone-shaped shell is characterized by being filled with a catalytic flammable agent and equipped with a flammable agent igniter for igniting the catalytic flammable agent. The rocket body is equipped with a timing controller, a multi-stage self-destruct assembly, a projectile assembly, and a double-safety self-destruct igniter. The timing controller is located between the double-safety self-destruct igniter and the multi-stage self-destruct assembly. When the rocket body reaches a preset operating height threshold, the timing controller controls the flammable agent igniter to ignite the catalytic flammable agent, causing the catalytic flammable agent to burn and release the internal catalyst into the cloud at high temperature, thus completing the catalyst seeding. After the catalyst seeding is completed, the timing controller sends a self-destruct trigger signal to control the projectile assembly to start, causing the projectile assembly to drive the multi-stage self-destruct assembly and ignite the multi-stage self-destruct assembly in different time sequences.
[0007] In one embodiment, the self-destruct assembly includes a second self-destruct body installed in the middle of the rocket body, and a first self-destruct body and a third self-destruct body distributed on both sides of the second self-destruct body. The first self-destruct body is located between the second self-destruct body and the timing controller. The ejection assembly is activated when it receives a self-destruct trigger signal, driving the first self-destruct body and the third self-destruct body to eject towards the front and rear ends of the rocket body, and igniting the first self-destruct body, the second self-destruct body and the third self-destruct body in different timing sequences.
[0008] In one embodiment, the ejection assembly includes a first ejection device installed between a first self-destructing body and a second self-destructing body, and a second ejection device installed between a second self-destructing body and a third self-destructing body. Both the first and second ejection devices contain propellant and an igniter. The igniter of the ejection assembly is used to receive a self-destruct trigger signal and ignite the propellant according to the self-destruct trigger signal, causing the propellant to burn and generate high-temperature and high-pressure gas to drive the first self-destructing body to eject towards the front end of the rocket body and the third self-destructing body to eject towards the rear end of the rocket body, and ignite the first, second, and third self-destructing bodies.
[0009] In one embodiment, an altitude sensor is installed inside the rocket body. The altitude sensor is linked to a timing controller. The altitude sensor detects the altitude of the rocket body and sends a positioning signal to the timing controller when the rocket body reaches a preset operating altitude threshold. The timing controller controls the flammable igniter to ignite the catalytic flammable ...
[0010] In one embodiment, the inner wall of the rocket body 1 is provided with multiple reinforcing ribs, each of which has a thickness of 0.5 to 0.7 times the thickness of the rocket body, in order to strengthen the rocket body and guide and transmit the explosive force to the inner wall of the rocket body.
[0011] In one embodiment, the rocket body is also equipped with an engine igniter, a dual-base propellant, and a nozzle. The engine igniter, dual-base propellant, and nozzle are all located at the end of the multi-section self-destruct assembly away from the self-destruct dual-safety igniter. The engine igniter consists of three parts: an ignition element, an ignition propellant, and an igniter. The ignition element is used to receive electrical signals from the timing controller and generate an initial spark according to the electrical signals. The ignition propellant is ignited and releases flame under the action of the initial spark. The igniter is used to amplify the flame energy.
[0012] In one embodiment, the dual-base propellant comprises nitrocellulose and nitroglycerin, used to propel the manned rocket into the air. The dual-base propellant is fixed inside the rocket body by wrapping paper tape and applying adhesive, so that the coating layer after the dual-base propellant burns adheres to the inner wall of the rocket body.
[0013] In one embodiment, the nozzle is made of high-silica fiberglass and includes an inlet, a throat, and an expansion section. The inlet and expansion sections are respectively connected to the two ends of the throat. The cross-sectional area of the throat is smaller than that of the inlet and smaller than that of the expansion section. Graphite is embedded in the throat.
[0014] The technical effects and advantages of this invention are as follows: 1. This invention uses a timing controller to precisely control the activation and ignition of multiple self-destruct components and projectile components, enabling the rocket's front, middle, and rear ends to explode and self-destruct separately. Furthermore, it is equipped with a double-safety igniter, which can precisely control the ignition of multiple self-destruct components within the multiple self-destruct components in sequence, thereby ensuring that the first, second, and third self-destruct components explode at different times, ensuring that the debris of the man-made rocket after explosion is less than 100g and that the flocculent fragments fall freely.
[0015] 2. This invention, by filling the output propellant into the engine ignition tube shell and fixing the propellant inside the ignition tube through pressing, closing, and flattening processes, can effectively prevent severe friction between the propellant and the surrounding structure and the impact under the action of the mechanical environment. The engine ignition device ignites the dual-base propellant and generates thrust, which is then ejected outward through the nozzle to propel the man-made rocket into the air. This allows for different timing of explosive disintegration operations in the air. At the same time, the reinforcing ribs not only strengthen the strength of the rocket's main shell, but also absorb some of the explosive energy during the explosive disintegration and transfer it to the entire structure. When the absorbed energy exceeds the strength limit of the reinforcing ribs, the reinforcing ribs will be damaged. Attached Figure Description
[0016] Figure 1 This is a front view of the overall structure of the present invention; Figure 2 This is a cross-sectional view of the overall structure of the present invention; Figure 3 This is a schematic diagram of the reinforcing rib of the present invention; Figure 4 For the present invention Figure 2 A magnified view of a portion of point A in the middle.
[0017] In the diagram: 1. Rocket body; 101. Timing controller; 102. First self-destruct device; 103. Second self-destruct device; 104. Third self-destruct device; 105. First ejection device; 106. Second ejection device; 107. Self-destruct double-safety igniter; 108. Altitude sensor; 109. Reinforcing rib; 2. Rocket cone shell; 201. Catalytic flare; 202. Flare igniter; 3. Blade tail fin; 4. Engine igniter; 5. Dual-base propellant; 6. Nozzle. Detailed Implementation
[0018] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.
[0019] This invention provides, for example Figures 1 to 4 The image shown is a precisely controllable manipulator rocket. This manipulator rocket includes a rocket body 1, a conical shell 2, and blade-shaped tail fins 3. The conical shell 2 is located at one end of the rocket body 1, and the blade-shaped tail fins 3 are located on the outer circumferential surface of the rocket body 1 away from the conical shell 2. The conical shell 2 is filled with a catalytic flare 201, and an ignition device 202 for igniting the catalytic flare 201 is installed inside. The rocket body 1 houses a timing controller 101, a multi-stage self-destruct assembly, a projectile assembly, and a self-destruct double-safety ignition device 107. The timing controller 101 is located between the self-destruct double-safety ignition device 107 and the multi-stage self-destruct assembly.
[0020] When the rocket body 1 reaches the preset operating altitude threshold, the timing controller 101 controls the flaming agent igniter 202 to ignite the catalytic flaming agent 201, causing the catalytic flaming agent 201 to burn and release the internal catalyst into the cloud at high temperature to complete the catalyst seeding. After the catalyst seeding is completed, the timing controller 101 sends a self-destruct trigger signal to control the launch assembly to start, so that the launch assembly drives the multi-stage self-destruct body assembly and ignites the multi-stage self-destruct body assembly in different time sequences.
[0021] By setting up multiple self-destruct components, the rocket body 1 can be detonated and fragmented at the front, middle and rear ends respectively. The ejection component can eject the self-destruct components in the multiple self-destruct components to the front, middle and rear ends of the rocket body 1 respectively, so as to facilitate the self-destruction and disintegration of the rocket body 1. The self-destruct double-safety igniter 107 is mainly used to provide secondary ignition for unignited self-destruct components, so as to avoid a major accident caused by the failure of a self-destruct component to ignite.
[0022] Inside the main body 1 of the rocket are installed sequentially the engine ignition device 4, the double-base propellant 5 and the nozzle 6 located at the tail. The ignition device 202 is used to ignite the catalytic flare 201. The catalytic flare 201 burns and releases the catalyst inside the catalytic flare 201 into the cloud at high temperature, so that it can fully exert its catalytic effect in the cloud.
[0023] The self-destruct assembly includes a second self-destruct body 103 installed in the middle of the rocket body 1, and a first self-destruct body 102 and a third self-destruct body 104 distributed on both sides of the second self-destruct body 103. The first self-destruct body 102 is located between the second self-destruct body 103 and the timing controller 101. The ejection assembly is activated upon receiving a self-destruct trigger signal, driving the first self-destruct body 102 and the third self-destruct body 104 to eject towards the front and rear ends of the rocket body 1, and igniting the first self-destruct body 102, the second self-destruct body 103, and the third self-destruct body 104 in different timing sequences. Because the lengths of the front, middle, and tail ends of the rocket body 1 are different, the length of the first self-destruct body 102 is greater than that of the second self-destruct body 103, and the length of the third self-destruct body 104 is greater than that of the first self-destruct body 102. This allows for better explosive disintegration of each part. The second self-destruct body 103 is used to explosively disintegrate the middle section of the rocket body 1, while the first self-destruct body 102 and the third self-destruct body 104 are ejected to the front and tail ends of the rocket body 1 respectively by the ejection assembly. This allows for separate explosive disintegration of the front, middle, and tail ends of the rocket body 1, and the resulting debris weighs less than 100g, preventing injury to the human body after it falls into the air.
[0024] The projectile assembly includes a first projectile device 105 installed between the first self-destruct body 102 and the second self-destruct body 103, and a second projectile device 106 installed between the second self-destruct body 103 and the third self-destruct body 104. The first projectile device 105 and the second projectile device 106 are respectively used to control the projectile and ignition of the first self-destruct body 102 and the third self-destruct body 104 towards both sides of the second self-destruct body 103. Both the first projectile device 105 and the second projectile device 106 are equipped with propellant and igniter. The igniter of the projectile assembly is used to receive the self-destruct trigger signal and ignite the propellant according to the self-destruct trigger signal, so that the propellant burns and generates high-temperature and high-pressure gas to drive the first self-destruct body 102 to be ejected towards the front end of the rocket body 1 and the third self-destruct body 104 to be ejected towards the rear end of the rocket body 1, and ignite the first self-destruct body 102, the second self-destruct body 103 and the third self-destruct body 104. When the timing controller 101 sends a self-destruct trigger signal, the high-temperature and high-pressure gas generated by the combustion of the propellant will push the self-destruct component along the inner cavity of the rocket body 1 until it is locked by the pre-set wedge-shaped ring on the inner wall of the rocket body 1. This achieves precise positioning of the head, middle and tail self-destruct components at different positions on the rocket body, preparing for subsequent synchronous explosion. Furthermore, the ejection component does not conflict with the self-destruct double-safety igniter 107. If the ejection component extinguishes or fails to ignite a self-destruct component during the ignition process, the self-destruct double-safety igniter 107 needs to precisely control the unignited self-destruct component for secondary ignition.
[0025] An altitude sensor 108 is installed inside the rocket body 1. This altitude sensor 108 is linked to a timing controller 101. The altitude sensor 108 is used to detect the altitude of the rocket body 1 and sends a positioning signal to the timing controller 101 when the rocket body 1 reaches a preset operating altitude threshold. The timing controller 101 controls the flare igniter 202 to ignite the catalytic flare 201 based on the positioning signal. The catalytic flare 201 burns and releases the internal catalyst into the cloud at high temperature to complete the catalyst dispersal. After the catalyst dispersal is completed, the timing controller 101 sends a self-destruct trigger signal to control the launch assembly to start. The launch assembly drives and ignites multiple self-destruct components. The altitude sensor 108, in conjunction with the timing controller 101, can collect the rocket's flight altitude data in real time, enabling more precise triggering of dispersal or self-destruction at a predetermined altitude. When the preset operating altitude threshold is reached, the timing controller 101 can perform subsequent dispersal or self-destruction functions.
[0026] The inner wall of the rocket body 1 is provided with multiple reinforcing ribs 109, each rib having a thickness of 0.5 to 0.7 times the thickness of the rocket body 1 (including the endpoints). These ribs are used to strengthen the rocket body 1 and guide and transmit the explosive force to the inner wall of the rocket body 1. The thickness design of the reinforcing ribs 109 ensures that they enhance the structural strength during normal use, but also makes them more susceptible to damage from the stress and energy generated by the explosion during an explosion, thus breaking them into fragments. Furthermore, the connection between the reinforcing ribs 109 and the inner wall of the rocket body 1 is designed with a smooth transition, such as rounded corners, to avoid stress concentration. During an explosion, these stress concentration points are more likely to fail first, leading to the overall breakage of the reinforcing ribs 109. At the same time, the surface of the reinforcing ribs 109 is provided with a draft angle, which not only facilitates smooth demolding during production but also makes the connection between the reinforcing ribs 109 and the rocket body 1 easier to break during an explosion, allowing the reinforcing ribs 109 to be more easily separated from the body and broken.
[0027] The engine ignition device 4 consists of three parts: an ignition element, an ignition propellant, and a priming propellant. It is powered and triggered by a timing controller 101 to precisely control the ignition timing of the dual-base propellant 5. The ignition element in the engine ignition device 4 receives electrical signals from the timing controller 101, generates an initial spark, and ignites the ignition propellant to release a large amount of heat and flame. The priming propellant amplifies the flame energy to ensure that the dual-base propellant 5 is fully and evenly ignited. Powered and triggered by the timing controller 101, it can precisely control the ignition timing and ensure the consistency of the rocket launch trajectory.
[0028] The dual-base propellant 5 is composed of nitrocellulose and nitroglycerin as its basic energy components and is used to propel the manned rocket into the air. The dual-base propellant 5 is positioned inside the rocket body 1 shell by wrapping paper tape and applying adhesive, so that the coating layer after combustion of the dual-base propellant 5 can also adhere tightly to the inner wall of the rocket body 1 shell, minimizing the impact on the ejection of the self-destructing object. The dual-base propellant 5 has the advantages of uniform composition, small batch-to-batch performance fluctuation range, long storage life, and stable performance. Moreover, by adjusting the combustion catalyst, it can obtain a plateau combustion characteristic with the burning rate basically unchanged with pressure within a certain pressure range. Furthermore, its combustion products have a very small attenuation effect on electromagnetic wave propagation, making it a relatively ideal smokeless propellant.
[0029] The nozzle 6 is made of high-silica fiberglass and includes an inlet, a throat, and an expansion section. The inlet and expansion sections are connected to the two ends of the throat, respectively. The cross-sectional area of the throat is smaller than that of the inlet and the expansion section. The throat of the nozzle 6 is inlaid with graphite. The key dimensions of the nozzle 6 are matched with the combustion characteristics of the dual-base propellant 5. At the same time, the diameter of the throat of the nozzle 6 determines the gas flow rate, which directly affects the thrust. The expansion section is used to further accelerate the gas, thereby improving thrust efficiency. The graphite inlaid in the throat of the nozzle 6 can enhance the ablation resistance of the nozzle 6, prevent the throat from deforming due to the scouring of high-temperature gas, and ensure the stability of thrust during the flight of the rocket.
[0030] The following describes the explosion and fragmentation of the rocket body 1 at the front, middle, and rear ends. The rocket body 1 can be internally divided axially into three independent sealed sections: the front catalyst compartment, the middle control self-destruct compartment, and the rear engine compartment. Multiple self-destruct components and ejection assemblies are coaxially mounted within the middle control self-destruct compartment. The engine ignition device 4, dual-base propellant 5, and nozzle 6 are mounted in the rear engine compartment.
[0031] First, the first ejection device 105 and the second ejection device 106 are activated simultaneously, pushing the first self-destruct device 102 to the connection between the front catalyst compartment and the central control self-destruct compartment of the rocket body 1, and pushing the third self-destruct device 104 to the connection between the rear engine compartment and the central control self-destruct compartment of the rocket body 1. The second self-destruct device 103 remains in the center of the central control self-destruct compartment. Subsequently, the timing controller 101 detonates the three self-destruct devices in a preset order: first, the first self-destruct device 102 is detonated, shattering the front cone shell 2 of the rocket body 1 and the remaining structure of the catalyst compartment; after a preset interval, the second self-destruct device 103 is detonated, shattering the central control compartment and related electronic components of the rocket body 1; after another preset interval, the third self-destruct device 104 is detonated, shattering the rear engine compartment, nozzle, and tail fins of the rocket body 1. This segmented sequential explosion method can avoid the energy from multiple self-destruct devices detonating simultaneously and ensure that each part receives sufficient explosive energy, thereby breaking all debris to below a safe mass.
[0032] The first projectile device 105 and the second projectile device 106 are sealed cylindrical shells with openings at both ends. They are filled with propellant and an electric igniter. The two ends of the shells are sealed and fitted to the end faces of the adjacent self-destruct bodies. When the timing controller 101 sends a self-destruct trigger signal, the electric igniter ignites the propellant. The propellant burns rapidly in the sealed shell, generating a large amount of high-temperature and high-pressure gas. Since the two ends of the shell are sealed by the self-destruct bodies, the gas cannot leak out, thus forming extremely high pressure inside the shell. This pressure acts simultaneously on the rear end face of the first self-destruct body 102 and the front end face of the third self-destruct body 104, generating axial thrust of equal magnitude and opposite direction. Under the action of this thrust, the first self-destruct body 102 overcomes the sliding friction between itself and the inner wall of the rocket body 1 and moves towards the front end of the rocket body 1; the third self-destruct body 104 moves towards the rear end of the rocket body 1 until both are respectively locked by the wedge-shaped annular limiting structure preset on the inner wall of the rocket body 1, thus completing the positioning.
[0033] The working principle of this invention is as follows: When it is necessary to artificially influence the weather, firstly, after mounting the artificial weathering rocket on the rack, adjust the launch elevation angle and connect the ignition cable. The operator reads the resistance value of the rocket on the controller panel. After the resistance is detected, the high-voltage function is activated to prepare for launch. The rocket is launched by pressing the launch button. At this time, the rocket is ignited by the power signal provided by the system and the timing controller 101, which causes the engine igniter 4 to ignite and ignite the dual-base propellant 5. The dual-base propellant 5 burns the fuel and is ejected from the nozzle 6, thereby achieving powered liftoff.
[0034] Secondly, through the mutual linkage of the altitude sensor 108 and the timing controller 101, the dispersal function can be precisely activated when the rocket reaches the effective working height of the target cloud and is in the core area of the cloud. This allows the timing controller 101 to control the flammable igniter 202 to ignite the catalytic flammable ...
[0035] Finally, after the seeding is completed, the projectile assembly simultaneously activates multiple self-destruct components, causing the first projectile device 105 and the second projectile device 106 to eject and ignite the first self-destruct component 102 and the third self-destruct component 104 towards the front and rear ends of the rocket body 1. At the same time, the second self-destruct component 103 is also ignited, thus working at high altitude to complete the disintegration of multiple parts after the rocket seeding operation, ensuring that the rocket debris falls freely as fragments weighing less than 100g, and the rocket operation is completed.
[0036] Finally, it should be noted that the above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. A precisely controllable shadow rocket, comprising a rocket body (1), a cone-shaped shell (2), and a blade-shaped tail fin (3), wherein the cone-shaped shell (2) is disposed at one end of the rocket body (1), and the blade-shaped tail fin (3) is disposed on the outer peripheral surface of the rocket body (1) away from the cone-shaped shell (2), characterized in that, The interior of the arrow cone shell (2) is filled with a catalytic flammable agent (201) and a flammable agent igniter (202) for igniting the catalytic flammable agent (201). The interior of the rocket body (1) is equipped with a timing controller (101), a multi-stage self-destruct assembly, a projectile assembly, and a self-destruct double-safety igniter (107). The timing controller (101) is located between the self-destruct double-safety igniter (107) and the multi-stage self-destruct assembly. When the rocket body (1) reaches the preset operating altitude threshold, the timing controller (101) controls the flaming agent igniter (202) to ignite the catalytic flaming agent (201), causing the catalytic flaming agent (201) to burn and release the internal catalyst into the cloud at high temperature to complete the catalyst seeding. After the catalyst seeding is completed, the timing controller (101) sends a self-destruct trigger signal to control the launch assembly to start, so that the launch assembly drives the multi-segment self-destruct body assembly and ignites the multi-segment self-destruct body assembly in different time sequences.
2. The precisely controllable shadow rocket as described in claim 1, characterized in that, The self-destruct assembly includes a second self-destruct body (103) installed in the middle of the rocket body (1), and a first self-destruct body (102) and a third self-destruct body (104) distributed on both sides of the second self-destruct body (103). The first self-destruct body (102) is located between the second self-destruct body (103) and the timing controller (101). The ejection assembly is activated when it receives the self-destruct trigger signal, driving the first self-destruct body (102) and the third self-destruct body (104) to eject towards the front and rear ends of the rocket body (1), and igniting the first self-destruct body (102), the second self-destruct body (103) and the third self-destruct body (104) in different time sequences.
3. The precisely controllable shadow rocket as described in claim 2, characterized in that, The projectile assembly includes a first projectile device (105) installed between the first self-destruct body (102) and the second self-destruct body (103), and a second projectile device (106) installed between the second self-destruct body (103) and the third self-destruct body (104). Both the first projectile device (105) and the second projectile device (106) are equipped with propellant and igniter. The igniter of the projectile assembly is used to receive the self-destruct trigger signal and ignite the propellant according to the self-destruct trigger signal, so that the propellant burns and generates high-temperature and high-pressure gas to drive the first self-destruct body (102) to be ejected towards the front end of the rocket body (1), and the third self-destruct body (104) to be ejected towards the rear end of the rocket body (1), and ignite the first self-destruct body (102), the second self-destruct body (103) and the third self-destruct body (104).
4. The precisely controllable shadow rocket as described in claim 1, characterized in that, The rocket body (1) is equipped with an altitude sensor (108) inside. The altitude sensor (108) is linked with the timing controller (101). The altitude sensor (108) is used to detect the altitude of the rocket body (1) and send a positioning signal to the timing controller (101) when the rocket body (1) reaches the preset operating altitude threshold. The timing controller (101) controls the flaming igniter (202) to ignite the catalytic flaming agent (201) according to the positioning signal, so that the catalytic flaming agent (201) burns and releases the internal catalyst into the cloud at high temperature to complete the catalyst dispersal. After the catalyst dispersal is completed, the timing controller (101) sends a self-destruct trigger signal to control the launch assembly to start, so that the launch assembly drives the multi-section self-destruct body assembly and ignites the multi-section self-destruct body assembly.
5. The precisely controllable shadow rocket as described in claim 1, characterized in that, The inner wall of the rocket body (1) is provided with multiple reinforcing ribs (109), and the thickness of each reinforcing rib (109) is 0.5 to 0.7 times the thickness of the rocket body (1), which are used to strengthen the strength of the rocket body (1) and to guide and transmit the explosive force to the inner wall of the rocket body (1).
6. The precisely controllable shadow rocket as described in claim 1, characterized in that, The rocket body (1) is also equipped with an engine ignition device (4), a dual-base propellant (5) and a nozzle (6). The engine ignition device (4), the dual-base propellant (5) and the nozzle (6) are all located at the end of the multi-section self-destruct assembly away from the self-destruct double-insurance ignition device (107). The engine ignition device (4) consists of three parts: an ignition element, an ignition propellant and an igniter. The ignition element is used to receive the electrical signal sent by the timing controller (101) and generate an initial spark according to the electrical signal. The ignition propellant is ignited and releases flame under the action of the initial spark. The igniter is used to amplify the flame energy.
7. The precisely controllable shadow rocket as described in claim 6, characterized in that, The components of the dual-base propellant (5) include nitrocellulose and nitroglycerin, which are used to propel the man-made rocket into the air. The dual-base propellant (5) is fixed inside the rocket body (1) by wrapping paper tape and applying glue, so that the coating layer after the dual-base propellant (5) burns adheres to the inner wall of the rocket body (1).
8. The precisely controllable shadow rocket as described in claim 6, characterized in that, The nozzle (6) is made of high silica fiberglass. The nozzle (6) includes an inlet, a throat and an expansion section. The inlet and the expansion section are respectively connected to the two ends of the throat. The cross-sectional area of the throat is smaller than that of the inlet and smaller than that of the expansion section. The throat is inlaid with graphite.