A method for self-destruction of a precast channel weather modification rocket

Abstract

The application discloses a precast slot type weather modification rocket self-destruction method, relates to the field of precise control of a weather modification rocket self-destruction process, and comprises the following steps: processing segmented precast slots in a 56mm engine shell, assembling a three-explosive self-destruction assembly; a time sequence controller combines with a rocket trajectory to bind self-destruction parameters and adapt to altitude adjustment parameters; after the rocket is launched, flight data is monitored, a self-destruction signal is generated when reaching a predetermined height; a triggering spreading function part is separated and segmented self-destruction is realized, a self-destruction body is detonated to break the shell; and the weight of the residual debris is verified to be less than or equal to 100g, 56mm rocket low-altitude parachute opening is ensured to be in line with regulations, and the self-destruction process is completed. The application is precise in self-destruction, safe and controllable in residual debris; is suitable for different altitudes and rocket calibers, reliable in two-stage rocket parachute opening; has good adaptability to low-temperature environments, high production efficiency, and can comprehensively improve the safety and reliability of weather modification operations.

Description

Technical Field

[0001] This invention relates to the field of precision control technology for the self-destruction process of weather modification rockets, and in particular to a self-destruction method for a precast trough-type weather modification rocket. Background Technology

[0002] With the widespread application of weather modification operations in agricultural disaster prevention and mitigation, ecological water replenishment, and other fields, the use of rain-inducing and hail-suppressing rockets has continued to grow. However, the contradiction between the precision of their self-destruction control process and operational safety has gradually become prominent. Traditional rain-inducing and hail-suppressing rockets rely heavily on simple mechanical timers for self-destruction control, which can only trigger the self-destruction action according to a preset fixed sequence. They cannot dynamically adjust control parameters based on the actual flight trajectory of the rocket (such as altitude deviation and velocity fluctuations). Under the influence of air density changes in mid-to-high altitude areas, the self-destruction timing often occurs too early or too late, resulting in some debris weighing far beyond the safety threshold. During the descent, this debris can easily injure ground personnel, damage crops, or infrastructure. At the same time, traditional self-destruction control lacks an adaptation design for the slenderness ratio of the engine casing, resulting in uneven distribution of self-destruction energy and an inability to achieve precise segmented fragmentation. Some casings are prone to leaving large fragments, making it difficult to meet the requirements for debris control after the operation.

[0003] While two-stage engine-powered rain and hail suppression rockets can increase launch altitude and operational range, the traditional self-destruct-recovery coordinated control mechanism has significant flaws. The parachute deployment control of first and second stage engine debris often employs a fixed-altitude trigger design, failing to dynamically adjust the deployment sequence based on real-time descent speed and air density. Under low-altitude wind disturbances, parachutes are prone to deployment failure or trajectory deviation, leading to excessive debris descent speed. Furthermore, the separation and self-destruct sequences of the two stages lack coordinated control logic. If the self-destruct action is delayed after first-stage separation, it can overlap with the second-stage rocket's flight trajectory, increasing the probability of mid-air collisions, affecting catalyst dispersal accuracy and threatening operational safety. In addition, the traditional self-destruct control module has poor compatibility with the ignition system. When the engine ignition circuit resistance is abnormal (exceeding the 0.55-1.0Ω range), the emergency self-destruct command cannot be triggered in time, potentially causing launch pad explosions and other safety accidents.

[0004] In terms of environmental adaptability and control reliability, the self-destruct control of traditional rain-inducing and hail-suppressing rockets also has shortcomings. The ignition propellant is mostly ordinary black powder, which is highly hygroscopic and has poor compatibility with metals. It easily solidifies and fails in low-temperature environments below -20℃, leading to power outages in the self-destruct control module; in high-temperature environments above 50℃, it easily volatilizes, causing abnormal ignition of the self-destruct delay tube, making it unsuitable for operational needs in different climatic regions. The engine propellant grain uses a fixed loading method, and after combustion, the coating layer easily detaches from the inner wall of the casing, interfering with the control accuracy of the self-destructing body's projection and reducing self-destruct reliability. At the same time, the self-destruct control module lacks a data feedback mechanism, making it impossible to record and analyze the weight and velocity data of the debris after each self-destruction, hindering iterative optimization to improve control performance and failing to meet the requirements of large-scale, high-reliability operations. Summary of the Invention

[0005] This invention proposes a self-destruction method for a prefabricated trough-type artificial weather modification rocket to solve the problems mentioned in the prior art.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a self-destruction method for a prefabricated trough-type artificial weather modification rocket, comprising the following steps: Prefabricated trough processing and self-destruct component assembly steps: three prefabricated troughs (front, middle, and rear) are processed on the engine housing. The trough walls are turned and polished to ensure the flatness meets the standards. The three-explosive self-destruct assembly, including the head self-destruct body, the middle self-destruct body, and the tail self-destruct body, is fixed in the prefabricated trough with threads and adhesive. The self-destruct body contains a mixture of black powder and potassium boronitrate. The bottom of the ejection tube is aligned with the shear groove at the bottom of the prefabricated trough. Self-destruct parameter timing binding steps: Key parameters are bound using a timing controller with an acceleration sensor and in conjunction with the rocket's theoretical trajectory. After parameter binding, the timing logic is verified in the full-missile ground test facility. Post-launch flight status real-time monitoring steps: The rocket is launched from the launch pad, and the timing controller collects data on flight altitude, speed, acceleration, engine ignition circuit resistance, and propellant combustion status in real time; The segmented self-destruct triggering and coordinated control steps are as follows: Based on the key parameters in the configuration and the real-time data collected on flight altitude, speed, acceleration, engine ignition circuit resistance, and propellant combustion status, the timing controller determines that the self-destruction conditions are met and issues a self-destruction preparation signal. First, the separation and dispersing function of the separation ejection cartridge is ignited, and the catalyst dispersal is completed after a delay. Simultaneously, the self-destruct body separation cartridge is ignited, and the self-destruct body is ejected along the corresponding pre-fabricated slots in the order of head, middle, and tail. Self-destruction debris status verification steps: Use a timing controller and over-accelerometer to monitor the debris fragment status, and combine ground observations to confirm that all fragments weigh ≤100 grams; when the 56 mm two-stage rocket debris falls to an altitude of 500-800 meters, trigger the parachute separation cartridge to open the parachute, and when there is no debris remaining exceeding the safety threshold, the self-destruction process is completed.

[0007] Furthermore, it also includes a dynamic adjustment step for self-destruct energy. Before the self-destruct parameter timing is set, the dosage of the self-destruct explosive for each component is calculated based on the density of the rocket shell material and the weight of the debris target. The calculation formula is as follows: ,in This refers to the dosage of the self-destructing drug for a single self-destructing device; Density of the engine casing material; This refers to the total volume of the engine casing; The proportion of the target weight of the debris to the total weight of the shell; The number of self-destructing entities; The energy utilization rate of the self-destructing drug.

[0008] Furthermore, the process includes a precast groove shear strength calibration step. After the precast groove is processed, a pressure testing device is used to apply a simulated projectile force to the precast groove and measure the actual force value when the precast groove breaks. The actual force value is compared with the rated projectile force of the self-destructing body separation cartridge. If the actual force value is 10% or more higher than the rated projectile force, the depth of the shear groove is increased by turning. If the actual force value is 10% or less lower than the rated projectile force, the depth of the shear groove is reduced by welding and polishing until the shear strength of the precast groove matches the projectile force.

[0009] Furthermore, the segmented self-destruct triggering and collaborative control steps also include a self-destruct delay time correction step, calculated using the following formula: ,in This is the revised self-destruct delay time; The self-destruct delay time is preset; This is the speed deviation correction factor; This refers to the actual flight speed of the rocket. The rated flight speed of the rocket; This is the height deviation correction factor; This refers to the actual flight altitude of the rocket. This is the rocket's rated flight altitude.

[0010] Furthermore, it also includes a two-stage rocket self-destruction and parachute deployment coordinated control procedure. For a 56mm two-stage engine rocket, after the segmented self-destruction trigger and coordinated control procedure, when the first-stage engine casing debris falls freely to an altitude of 800 meters above the ground, the timing controller triggers the first-stage parachute system deployment command. After the first-stage parachute deploys, the deployment status is monitored by the tension sensor. The second-stage engine debris falls along a quasi-parabolic trajectory under the control of the blade tail fin. When the descent altitude is detected to drop to 500 meters, the second-stage parachute system deployment command is triggered, and the descent speed of the two-stage debris after deployment is recorded.

[0011] Furthermore, it also includes emergency handling procedures for self-destruction anomalies. During the real-time flight status monitoring after launch, if the ignition circuit resistance exceeds the range of 0.55 to 1.0 ohms, or the self-destructing body separation delay exceeds the preset value by 20%, or the flight static stability is below 15%, the timing controller immediately triggers an emergency self-destruct command, skipping the separation delay of the dispersing function and directly detonating the dispersing function. At the same time, the self-destructing body separation interval is shortened to 0.2 seconds to accelerate the self-destruction process. If a parachute system malfunction is detected, for 56mm two-stage rockets, the dosage of the tail self-destructing propellant is increased by 10% to 15%, further fragmenting the debris by enhancing the self-destruction energy, so that the debris weight does not exceed 100 grams.

[0012] Furthermore, the self-destruct parameter timing step also includes an altitude-based self-destruct parameter adaptation step. For medium- and high-altitude areas, the self-destruct parameters are adjusted according to the actual altitude of the operating area: for every 1,000 meters increase in altitude, the separation delay of the dispersing function is extended by 0.1 seconds and the separation delay of the self-destructing body is extended by 0.05 seconds, while the dosage of the self-destructing agent is increased by 5% to 8%; when the altitude is below 1,000 meters, the separation delay of the dispersing function is shortened by 0.05 seconds and the separation delay of the self-destructing body is shortened by 0.02 seconds, while the dosage of the self-destructing agent is reduced by 3% to 5%.

[0013] Furthermore, it also includes a self-destruct effect feedback optimization step. After the debris status verification step is completed, the actual weight and descent velocity data of the debris after each self-destruction are collected and compared with the preset target value. If the deviation rate exceeds 5% for three consecutive times, the reference parameters in the self-destruct parameter timing binding step are adjusted: when the debris weight deviation exceeds the limit, the self-destruct explosive dosage calculation coefficient is corrected; when the descent velocity deviation exceeds the limit, the parachute opening height threshold is adjusted to ±50 meters.

[0014] Furthermore, the prefabrication tank processing and self-destruct component assembly steps also include a low-temperature environment adaptation process. For low-temperature operating environments ranging from -20 degrees Celsius to 0 degrees Celsius, low-temperature toughness materials are used during prefabrication tank processing, and low-temperature curing adhesives are selected for fixing the self-destruct body and the prefabrication tank. Five to ten percent of low-temperature sensitizers are added to the self-destruct kit. The timing controller is wrapped with thermal insulation cotton to ensure that the measurement error of the acceleration sensor at low temperatures is no more than 0.1 meters per second squared.

[0015] Furthermore, it also includes a unified step for multi-launcher coordinated self-destruct parameters. When multiple launchers are operating simultaneously, whether they are of the same or different models, the self-destruct parameter setting data of each launcher rocket is received through the ground control station. The self-destruct separation delay and self-destruct trigger time of rockets of the same caliber are uniformly calibrated. After calibration, unified parameter instructions are issued to each launcher to ensure that the self-destruct process is orderly when multiple rockets are operating in coordination.

[0016] Compared with existing technologies, the beneficial effects of this invention are: The prefabricated trough-type artificial weather modification rocket self-destruction method of this invention, based on precision control technology, achieves breakthroughs in multiple dimensions, including dynamic adjustment of self-destruction timing, coordinated control of self-destruction and parachute deployment, and environmental adaptation control, comprehensively improving the control accuracy and operational safety of the rocket's self-destruction process. Regarding self-destruction timing control, a timing controller with an acceleration sensor collects rocket flight data (altitude, velocity, acceleration) in real time and dynamically corrects the self-destruction delay time. Compared to traditional fixed timing control, this method can accurately match the self-destruction requirements under different altitudes and trajectory deviations, ensuring that the self-destruction action is completed at the predetermined altitude and that the debris remains within a safe control range after self-destruction, effectively eliminating the risk of damage to personnel and facilities on the ground.

[0017] To address the challenge of coordinating self-destruction and recovery in two-stage rockets, this invention constructs a linked control logic. During the descent of first- and second-stage engine debris, the timing controller precisely triggers the parachute system based on real-time altitude and velocity data. Compared to traditional fixed-altitude parachute deployment control, the precision of parachute deployment timing is significantly improved, and the debris's descent velocity is effectively controlled, completely resolving the high-energy impact problem caused by free fall. Simultaneously, through deep coordination between the two-stage rocket separation and self-destruction sequences, the overlapping trajectories of the two-stage debris after separation are avoided, reducing the risk of mid-air collisions, ensuring precise catalyst dispersal into the target cloud layer, and improving operational effectiveness.

[0018] This invention also demonstrates excellent environmental adaptability and control reliability. The ignition propellant uses a mixture of black powder and potassium borate nitrate, possessing low hygroscopicity, high metal compatibility, and wide temperature range adaptability. Combined with the thermal insulation design of the timing controller, it can stably trigger self-destruct control commands in both low and high temperature environments, overcoming the limitations of traditional self-destruct control modules with poor climate adaptability, and meeting the operational needs of different regions and seasons. The engine propellant uses a free-loading design, combined with paper tape winding and adhesive positioning processes, ensuring that the coating layer adheres tightly to the inner wall of the casing after combustion, reducing interference with the self-destruct body's projection action and further improving self-destruct control accuracy.

[0019] Furthermore, the three-explosion self-destruct assembly adopts an integrated, fully enclosed structure, effectively blocking the fire propagation path through threads and adhesive bonding, significantly reducing the probability of premature detonation. The stability and consistency of self-destruction control are significantly superior to traditional split-type designs. The addition of a self-destruction effect feedback optimization step allows for the recording and analysis of debris data after each self-destruction, continuously improving control reliability through iterative adjustments to control parameters (such as self-destruct explosive dosage and parachute opening height threshold). The reserved space for a digital chip box also provides the possibility for future upgrades to a digitally electronically controlled self-destruction system, allowing for flexible expansion of control functions according to operational needs and enhancing long-term applicability. Overall, this invention achieves comprehensive optimization in self-destruction control accuracy, collaborative control capabilities, environmental adaptability, and reliability, providing strong control technology support for large-scale, high-safety-standard weather modification operations. Attached Figure Description

[0020] Figure 1 This is a schematic block diagram of a prefabricated trough-type artificial weather modification rocket self-destruction method proposed in this invention; Figure 2 A graph showing the relationship between self-destruction time and wreckage weight; Figure 3 A comparison chart of catalyst utilization rates at different cloud altitudes; Figure 4 This is a graph showing the relationship between assembly steps and rocket production efficiency. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0023] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; and they may refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances. The invention will now be described in further detail with reference to the accompanying drawings.

[0024] Reference Figures 1 to 4 A method for the self-destruction of a prefabricated trough-type artificial weather modification rocket, comprising the following steps: The prefabricated slot processing and self-destruct component assembly steps involve machining segmented prefabricated slots on the engine casing of the weather modification rocket. The front prefabricated slot corresponds to the installation position of the head self-destruct component, the middle prefabricated slot corresponds to the installation position of the middle self-destruct component, and the rear prefabricated slot corresponds to the installation position of the tail self-destruct component. The depth of the prefabricated slot is set to one-third to one-half of the casing wall thickness, and the width is adapted to the self-destruct component's ejection stroke. Turning and polishing processes are used to ensure the flatness of the slot wall. The three-explosive self-destruct assembly (head self-destruct component, middle self-destruct component, and tail self-destruct component) is fixed in the prefabricated slot using threads and adhesives. The self-destruct component contains a non-high explosive charge, namely a mixture of black powder and potassium borate nitrate. The bottom of the ejection tube is aligned with the shear groove at the bottom of the prefabricated slot so that the self-destruct component can be directionally ejected along the prefabricated slot when triggered. The self-destruct parameter timing setting process involves using a timing controller with an acceleration sensor and combining it with the rocket's theoretical trajectory to set key self-destruct parameters. The 56mm two-stage rocket has a launch altitude of 5 to 7.5 kilometers. The set parameters include a separation delay of 0.8 to 1.2 seconds for the dispersal function, a separation delay of 1 second for the self-destruct body, and an overall self-destruct trigger time of 24 ± 2.5 seconds. At the same time, the baseline threshold of rocket static stability of not less than 15% and the normal range of ignition circuit resistance of 0.55 to 1.0 ohms are recorded. After the parameters are set, the accuracy of the timing logic is verified in the full-missile ground test facility. The real-time flight status monitoring steps after launch: After the rocket is launched from the launch pad, the timing controller collects the rocket's flight altitude, speed, and acceleration data in real time, and simultaneously receives signals of engine ignition circuit resistance and propellant combustion status. When the flight altitude reaches the predetermined operating altitude, which is 5 to 7.5 kilometers for the 56mm rocket, a self-destruct preparation trigger signal is generated. The segmented self-destruct triggering and coordinated control steps involve a timing controller that, based on key parameters and real-time data collected on flight altitude, speed, acceleration, engine ignition circuit resistance, and propellant combustion status, determines if the self-destruct conditions are met and issues a self-destruct preparation signal. First, the separation ejection cartridge is ignited by the dispersing function unit separation and ignition control module, separating the dispersing function unit from the projectile body. After a delay of 0.8 to 1.2 seconds, the dispersing function unit is detonated to complete catalyst dispersal. Simultaneously with the separation of the dispersing function unit, the engine ignition and self-destruct body separation control module ignites the self-destruct body separation cartridge. The head self-destruct body is ejected along the front pre-fabrication groove to the front of the engine. After a delay of 0.3 seconds, the middle self-destruct body is ejected along the middle pre-fabrication groove to the middle of the casing. After another delay of 0.3 seconds, the tail self-destruct body is ejected along the rear pre-fabrication groove to the rear of the casing. Subsequently, the short-delay self-destruct delay tubes of each self-destruct body are ignited, and after a 1-second delay, the head, middle, and tail self-destruct bodies are detonated sequentially, achieving segmented fragmentation of the engine casing. The self-destruction debris status verification steps involve using a timing controller and acceleration sensors to monitor the movement of debris fragments, and combining this with ground observations to confirm the debris weight, ensuring that all fragments weigh no more than 100 grams. For a 56mm two-stage rocket, when the first and second stage engine casing debris falls to a height of 500 to 800 meters, the parachute separation cartridge is triggered to open the parachute. The self-destruction process is completed when the debris fall velocity is verified to be no more than 8 meters per second and no debris remains exceeding the safety threshold.

[0025] This invention also includes a self-destruct energy dynamic adjustment step. Before the self-destruct parameter timing is set, the self-destruct explosive dosage of each component is calculated based on the rocket shell material density and the target weight of the debris. The calculation formula is as follows: ,in The dosage of the self-destructing agent for a single self-destructing body is in grams. Density of the engine casing material, expressed in grams per cubic centimeter; This refers to the total volume of the engine casing, in cubic centimeters. The value is the proportion of the target weight of the debris to the total weight of the shell, ranging from 0.1 to 0.15, corresponding to a debris weight of no more than 100 grams; This represents the number of self-destructing components, with a value of 3, corresponding to a three-explosion self-destructing combination. The energy utilization rate of the self-destruct explosive is set to 0.6 to 0.8, determined based on the characteristics of non-high explosives. This calculation ensures that the dosage of the self-destruct explosive is precisely matched to the shell fragmentation requirements, avoiding insufficient explosive charge leading to excessively large debris or excessive explosive charge causing energy waste. At the same time, it ensures that there is no violent detonation during the self-destruction process, thus improving operational safety.

[0026] This invention also includes a prefabricated groove shear strength calibration step. After the prefabricated groove is processed, a pressure testing device is used to apply a simulated projectile force to the prefabricated groove and measure the actual force value when the prefabricated groove breaks. The actual force value is compared with the rated projectile force of the self-destructing body separation cartridge. If the actual force value is 10% or more higher than the rated projectile force, the depth of the shear groove is appropriately increased through a turning process. If the actual force value is 10% or less lower than the rated projectile force, the depth of the shear groove is reduced through welding and polishing processes until the shear strength of the prefabricated groove matches the projectile force. This ensures that the self-destructing body can accurately separate along the prefabricated groove when triggered, avoiding jamming or premature separation of the self-destructing body due to improper shear strength, which would affect the self-destruction effect.

[0027] In this invention, the segmented self-destruct triggering and coordinated control steps also include a self-destruct delay time correction step. Based on the actual flight speed and altitude of the rocket collected in real time by the timing controller, the preset self-destruct delay time is dynamically corrected, and the calculation formula is as follows: ,in This is the revised self-destruct delay time, in seconds; The preset self-destruct delay time for the 56mm rocket is 24 seconds, in seconds. This is the speed deviation correction factor, ranging from 0.02 to 0.05, with units of seconds squared per meter; This represents the actual flight speed of the rocket, measured in meters per second. The rated flight speed of the rocket, measured in meters per second; This is the height deviation correction factor, ranging from 0.001 to 0.003, with units of meters per second. The actual flight altitude of the rocket, in meters; The rated flight altitude of the rocket is measured in meters. This calculation eliminates the influence of flight speed and altitude deviations on the self-destruct timing, ensuring that the self-destruction maneuver is completed at the predetermined altitude and avoiding excessive debris fall speed due to low-altitude self-destruction.

[0028] This invention also includes a two-stage rocket self-destruct-parachute deployment coordinated control step. For a 56mm two-stage engine rocket, after the segmented self-destruct triggering and coordinated control steps, when the first-stage engine casing debris falls freely to an altitude of 800 meters above the ground, the timing controller triggers the first-stage parachute system deployment command. After the first-stage parachute deploys, the deployment status is monitored by a tension sensor. The second-stage engine debris falls along a quasi-parabolic path under the control of the tail fin. When the falling altitude drops to 500 meters, the second-stage parachute system deployment command is triggered. At the same time, the falling speed of the two-stage debris after deployment is recorded to ensure that the falling speed does not exceed 8 meters per second. This step combines pre-formed slot directional self-destruction with low-altitude parachute deployment, ensuring that the weight of the self-destructed debris from the seeding function does not exceed 100 grams and achieving safe recovery of the engine casing debris, thus adapting to the operational needs of two-stage rockets in medium and high altitude regions.

[0029] This invention also includes emergency handling steps for self-destruct anomalies. During the real-time flight status monitoring step after launch, if the ignition circuit resistance exceeds the range of 0.55 to 1.0 ohms, or the self-destruct body separation delay exceeds a preset value by 20%, or the flight static stability is below 15%, the timing controller immediately triggers an emergency self-destruct command, skipping the separation delay of the dispersing function and directly detonating the dispersing function. At the same time, the self-destruct body separation interval is shortened to 0.2 seconds to accelerate the self-destruct process. If a parachute system malfunction is detected, for 56mm two-stage rockets, the dosage of the tail self-destruct body propellant is increased by 10% to 15%, further fragmenting the debris by enhancing the self-destruct energy, ensuring that the debris weight does not exceed 100 grams, and avoiding ground safety hazards caused by self-destruct anomalies.

[0030] In this invention, the self-destruct parameter timing binding step also includes an altitude-based self-destruct parameter adaptation step. For medium-to-high altitude areas (1000 to 3000 meters), the self-destruct parameters are adjusted according to the actual altitude of the operating area: for every 1000 meters increase in altitude, the separation delay of the dispersing function is extended by 0.1 seconds and the separation delay of the self-destructing body is extended by 0.05 seconds, while the dosage of the self-destructing agent is increased by 5% to 8% to compensate for the attenuation of self-destruction energy caused by the thin air at high altitudes; when the altitude is below 1000 meters, the separation delay of the dispersing function is shortened by 0.05 seconds and the separation delay of the self-destructing body is shortened by 0.02 seconds, and the dosage of the self-destructing agent is reduced by 3% to 5% to avoid excessive fragmentation of debris due to the dense air at low altitudes. This step ensures consistent self-destruction effects across different altitude areas, meeting the needs of all-area artificial weather modification operations.

[0031] This invention also includes a self-destruction effect feedback optimization step. After the debris status verification step is completed, the actual weight and fall velocity data of the debris after each self-destruction are collected and compared with preset target values. The preset target values ​​are debris weight not exceeding 100 grams and fall velocity not exceeding 8 meters per second. The deviation rate is calculated. If the deviation rate exceeds 5% for three consecutive times, the benchmark parameters in the self-destruction parameter timing binding step are adjusted: when the debris weight deviation exceeds the limit, the self-destruction explosive dosage calculation coefficient is corrected, for example, the λ value is adjusted to ±0.05; when the fall velocity deviation exceeds the limit, the parachute opening height threshold is adjusted to ±50 meters. Through continuous feedback optimization, the reliability of the self-destruction method is improved, so that the rocket self-destruction effect compliance rate is stabilized at over 99.9% with a confidence level of 0.7.

[0032] In this invention, the prefabrication tank processing and self-destruct component assembly steps also include a low-temperature environment adaptation process. For low-temperature operating environments ranging from -20 degrees Celsius to 0 degrees Celsius, low-temperature toughness materials, such as modified stainless steel, are used during prefabrication tank processing. The adhesive used to fix the self-destruct body and the prefabrication tank is a low-temperature curing type with a curing temperature above -15 degrees Celsius. Five to ten percent of a low-temperature sensitizer, such as ultrafine aluminum powder, is added to the self-destruct cartridge to reduce the ignition temperature of the agent. The timing controller is wrapped with thermal insulation cotton to ensure that the accelerometer measurement accuracy at low temperatures meets the requirement of an error of no more than 0.1 meters per second squared. This step avoids the prefabrication tank from becoming brittle, the self-destruct body from falling off, or the agent from failing to ignite due to low temperatures, ensuring that the self-destruct process executes normally in low-temperature environments.

[0033] This invention also includes a unified self-destruct parameter step for multiple launchers. When multiple launchers operate simultaneously, whether they are of the same or different models, the self-destruct parameter data of the rockets on each launcher is received by the ground control station. The self-destruct separation delay and self-destruct trigger time of rockets of the same caliber are uniformly calibrated, with the deviation controlled within ±0.05 seconds. The self-destruct trigger altitude gradient is set according to the difference in firing altitude, with 5 kilometers for 56 mm rockets. After calibration, unified parameter instructions are issued to each launcher, so that the self-destruct process is orderly and the debris is evenly distributed when multiple rockets operate in coordination, thereby improving the safety and effectiveness of large-area artificial weather modification operations.

[0034] The following two examples further illustrate the specific implementation of this system: Example 1: Self-destruction application of a 56mm caliber two-stage engine rain-enhancing and hail-suppressing rocket in a mid-to-high altitude region in southern China. This embodiment was applied to rain enhancement and hail suppression operations in a mid-to-high altitude mountainous area of ​​a certain county. The operation area was at an altitude of 2200 meters, covering 180 square kilometers of farmland. A 56mm caliber two-stage engine rain enhancement and hail suppression rocket was used, and a pre-fabricated trough self-destruct method was employed to ensure safe operation. The specific operation is as follows: I. Self-Destruct Process and Key Steps: Prefabricated Groove Machining and Self-Destruct Component Assembly: Two prefabricated grooves are machined on the 56mm diameter first-stage engine casing, with a casing wall thickness of 3mm. The front prefabricated groove is 150mm long, corresponding to the head self-destruct component installation position, and the rear prefabricated groove is 180mm long, corresponding to the tail self-destruct component installation position. Three prefabricated grooves are machined on the second-stage engine casing, with a casing wall thickness of 2.8mm. The front prefabricated groove is 120mm long, the middle one is 160mm long, and the rear one is 140mm long, corresponding to the head, middle, and tail self-destruct component installation positions, respectively. All prefabricated grooves are 1.2mm deep and 10mm wide to accommodate the self-destruct component projection stroke. They are machined using CNC turning and then polished, with a groove wall roughness ≤ Ra0.8 micrometers. The first-stage self-destruct assembly contains two self-destruct bodies, each filled with a mixture of 60 grams of black powder and potassium borate nitrate. The second-stage self-destruct assembly contains three self-destruct bodies, each filled with a mixture of 55 grams. All are secured with M4 threads and high-temperature adhesive. The shear groove at the bottom of the launch tube is aligned with the bottom of the prefabricated trough to ensure that the launch direction deviation does not exceed 1 degree. The first and second-stage parachute systems are respectively installed at the tail of the first-stage engine and the middle of the second-stage engine, with a parachute surface area of ​​0.8 square meters. The parachute deployment trigger device is linked to the timing controller.

[0035] Self-destruct energy dynamic adjustment and parameter calculation: Before the self-destruct parameter sequence is finalized, the self-destruct explosive dosage for each component is calculated based on the engine casing material density, wall thickness, and target weight of the debris. The engine casing is made of stainless steel with a density of 7.9 g / cm³. The first-stage engine casing is 800 mm long, and the second-stage engine casing is 750 mm long. The calculated total volume of the first-stage casing is approximately 1.32 × 10⁻⁶ mm. 5 132 cubic millimeters (132 cubic centimeters), the total volume of the secondary shell is approximately 1.18 × 10⁻⁶. 5 118 cubic centimeters. η is the ratio of the target debris weight to the total shell weight, taken as 0.12, corresponding to a debris weight not exceeding 100 grams; the number of first-level self-destruct devices is 2, and the number of second-level self-destruct devices is 3; λ is the energy utilization rate of the self-destruct explosive, taken as 0.7. Substituting these values, the calculated dosage of a single first-level self-destruct device is approximately 58 grams, and the dosage of a single second-level self-destruct device is approximately 52 grams. After rounding, the dosage is calculated as 60 grams for first-level and 55 grams for second-level.

[0036] Self-destruct parameter timing and altitude adaptation: Parameters are set using a timing controller with an accelerometer, with a measurement accuracy of ±0.05 meters per second squared. The 56mm two-stage rocket has a rated launch altitude of 6.0 kilometers. The first-stage self-destruct trigger time is set to 15 seconds, the second-stage self-destruct trigger time to 24 seconds, the dispersal function separation delay to 1.0 second, and the self-destruct component separation delay to 1 second. Parameters are adjusted based on the operating area's altitude of 2200 meters: for every 1000 meters increase in altitude, the dispersal function separation delay is increased by 0.1 seconds, the self-destruct component separation delay is increased by 0.05 seconds, and the self-destruct propellant dosage is increased by 5% to 8%. Therefore, the dispersal function separation delay is increased by 0.22 seconds, the self-destruct component separation delay is increased by 0.11 seconds, the first-stage self-destruct propellant dosage is increased from 60 grams to 67 grams, and the second-stage self-destruct propellant dosage is increased from 55 grams to 61 grams to compensate for energy attenuation caused by the thin air at high altitudes. The baseline threshold of 15% for rocket static stability and the normal range of 0.55 to 1.0 ohms for ignition circuit resistance were entered. After the parameters were set, they were verified in the full-missile ground test room. The timing logic response delay did not exceed 0.02 seconds.

[0037] Post-launch flight status monitoring and emergency response: The rocket was launched from the cage-type automated launch pad. The timing controller collected flight data in real time: the launch velocity was 90 meters per second; 8 seconds after liftoff, the first-stage engine propellant burned out, the altitude was 2.5 kilometers, and the velocity was 280 meters per second, triggering the first and second stage separation commands. The first-stage engine casing debris fell freely at a velocity of 18 meters per second, and the second-stage engine ignited and continued to accelerate. 15 seconds after liftoff, the altitude was 4.0 kilometers, and the velocity was 320 meters per second. The ignition circuit resistance was monitored to be 0.75 ohms, within the normal range, and the propellant combustion pressure was 5.5 MPa. 20 seconds after liftoff, an instantaneous wind speed increase to 9 meters per second was detected, and the rocket's actual altitude was 4.8 kilometers, 5.0 kilometers below the rated altitude, triggering the self-destruct delay time correction. The preset self-destruct delay time is 24 seconds, the speed deviation correction factor is 0.03 seconds squared per meter, the actual flight speed is 315 meters per second, and the rated flight speed is 330 meters per second; the altitude deviation correction factor is 0.002 seconds per meter, the actual flight altitude is 4800 meters, and the rated flight altitude is 5000 meters. After correction, the self-destruct delay time is adjusted to 23.15 seconds.

[0038] Segmented self-destruct triggering and debris verification: 23.5 seconds after liftoff, the second-stage rocket reached an altitude of 6.0 km, generating a self-destruct preparation signal. First, the separation ejection cartridge was ignited by the separation and ignition control module of the seeding function section. The seeding function section separated from the rocket body at a speed of 1.5 m / s, and after a delay of 1.22 seconds, it detonated to complete the catalyst seeding (containing 10.8 g AgI). Simultaneously, the second-stage self-destruct separation cartridge was ignited. The head self-destruct cartridge was ejected along the front pre-formed groove, followed by the middle self-destruct cartridge after a delay of 0.3 seconds, and then the tail self-destruct cartridge after another delay of 0.3 seconds. The short-delay self-destruct delay tubes were ignited, and after a delay of 1 second, they detonated sequentially, causing the second-stage engine casing to shatter into segments. When the first-stage engine debris reached an altitude of 800 meters, the timing controller triggered the first-stage parachute deployment command, and the parachute fully deployed within 3 seconds, reducing the debris's descent velocity to 7.5 meters per second. When the second-stage engine debris reached an altitude of 500 meters, the second-stage parachute deployment command was triggered, reducing the descent velocity to 7.2 meters per second. Accelerometer monitoring and ground observation confirmed that all debris fragments weighed no more than 92 grams, and the descent velocity met safety requirements, completing the self-destruct process.

[0039] II. Data Representation and Interpretation Table 1: Comparison of self-destruct performance of a 56mm two-stage rocket in a medium-to-high altitude region in southern China

[0040] Table 1 shows that the present invention is suitable for the operational needs of two-stage rockets at medium and high altitudes. The maximum weight of the debris after self-destruction is much lower than that of traditional methods. The core reason is the directional ejection design of the prefabricated slot and the precise control of the propellant dosage, which avoids leaving large fragments in the shell, meeting the safety requirement of less than 100 grams. The self-destruction timing deviation is greatly reduced due to the application of altitude adaptation adjustment and dynamic correction mechanisms, ensuring that the self-destruction action is completed at the predetermined altitude, avoiding the safety hazards caused by low-altitude self-destruction. The success rate of cryogenic self-destruction is significantly improved, thanks to the adaptation design of adding cryogenic sensitizers to the ignition propellant and using cryogenic curing adhesives, which avoids the failure of self-destruction components in cryogenic environments. The uniformity of engine shell fragmentation is improved, relying on the synergistic effect of the two-stage prefabricated slots of the first stage and the three-stage prefabricated slots of the second stage, and multiple self-destruction components to achieve precise segmented fragmentation. Production and assembly efficiency is doubled because the integrated assembly process of prefabricated slot processing and self-destruction components is simplified, eliminating the need for special fixtures, and meeting the needs of large-scale production while ensuring operational safety.

[0041] Example 2: Self-destruction application of a 56mm caliber two-stage engine rain-enhancing and hail-suppressing rocket in a grassland in northern China. This embodiment was applied to hail suppression operations on a grassland in northern China. The operation area was at an altitude of 1000 meters, covering a pasture of 400 square kilometers. A two-stage rain-enhancing and hail-suppressing rocket with a 56mm caliber engine was used. The two stages achieved coordinated self-destruction through a pre-fabricated trough-type self-destruction method. The specific operation is as follows: I. Self-destruction process and key steps execution Prefabricated slot fabrication and two-stage self-destruct assembly: The first-stage engine casing is fabricated with two prefabricated slots. The first-stage engine casing has a wall thickness of 3 mm, with the front prefabricated slot being 150 mm long and the rear prefabricated slot being 180 mm long. The second-stage engine casing is fabricated with three prefabricated slots. The second-stage engine casing has a wall thickness of 2.8 mm, with the front prefabricated slot being 120 mm long, the middle prefabricated slot being 160 mm long, and the rear prefabricated slot being 140 mm long. All prefabricated slots have a depth of 1.2 mm, which is two-fifths of the casing wall thickness, and a width of 10 mm. The first-stage self-destruct assembly contains two self-destruct bodies, each containing 60 grams of a mixture of black powder and potassium borate nitrate. The second-stage self-destruct assembly contains three self-destruct bodies, each containing 55 grams of the agent. All are fixed to the corresponding prefabricated slots by threads and adhesives, with the projectile shearing groove aligned with the prefabricated slots. The first and second-stage parachute systems are installed at the tail of the first-stage engine and the middle of the second-stage engine, respectively. The parachute system has a canopy area of ​​0.8 square meters, and the parachute opening trigger device is linked to the timing controller.

[0042] Self-destruct parameter setting and coordinated control: The timing controller sets the parameters as follows: first-stage rocket rated separation altitude 2.5 km, rated separation velocity 280 m / s, second-stage rocket rated launch altitude 6.0 km; first-stage self-destruct trigger time is set to 15 seconds, second-stage self-destruct trigger time to 24 seconds, and dispersal function part separation delay to 1.2 seconds; parameters are adjusted based on the operating area altitude of 1000 meters: when the altitude is below 1000 meters, the dispersal function part separation delay is shortened by 0.05 seconds, and the self-destruct explosive dosage is reduced by 3%, thus reducing the first-stage self-destruct explosive dosage from 60 grams to 58 grams, and the second-stage self-destruct explosive dosage from 55 grams to 53 grams. Simultaneously, the first-stage parachute deployment altitude is set to 800 meters, and the second-stage parachute deployment altitude to 600 meters, with the parachute deployment trigger threshold being 0.5 seconds earlier when the descent velocity is ≥15 m / s.

[0043] Flight monitoring and two-stage separation: The rocket is launched via a variable-trajectory launcher, and the timing controller collects flight data in real time: the first-stage engine burns for 8 seconds, using a dual-base propellant with an initial total burn area of ​​5.967 × 10⁻⁶. -2 The rocket, with a propellant area of ​​[square meters], reached an altitude of 2.5 kilometers and a speed of 280 meters per second 8 seconds after launch, triggering the first and second stage separation commands. The first-stage engine casing debris fell freely at a speed of 18 meters per second, the second-stage engine ignited, and the initial propellant equilibrium pressure of the second-stage engine was 5.5 MPa. It continued to accelerate until it reached an altitude of 4.5 kilometers and a speed of 350 meters per second 15 seconds after launch.

[0044] Segmented self-destruction and parachute deployment coordination: 24 seconds after liftoff, the second-stage rocket reaches an altitude of 6.0 km, the predetermined launch altitude, and generates a self-destruct preparation signal. The dispersing component detaches from its propellant cartridge and detonates 1.2 seconds after separation, dispersing the catalyst through combustion. Simultaneously, the second-stage self-destruct component detaches from its propellant cartridge, and the head, middle, and tail self-destruct components are sequentially ejected along their corresponding pre-fabricated slots, detonating 1 second later. The second-stage engine casing fragments, and the debris from the self-destructing dispersing component weighs ≤92 grams. When the first-stage engine debris falls to an altitude of 800 meters, the timing controller triggers the first-stage parachute deployment command, and the parachute fully deploys within 3 seconds, reducing the debris's descent velocity to 7.5 m / s. The second-stage engine debris falls along a quasi-parabolic trajectory under the control of the blade tail fins, triggering the second-stage parachute deployment command at an altitude of 600 meters, reducing the debris's descent velocity to 7.2 m / s. The descent velocities of both stages are ≤8 m / s.

[0045] Anomaly Response and Effect Feedback: During the operation, the resistance of the secondary ignition circuit was detected to momentarily rise to 1.1 ohms, exceeding the normal range of 0.55 to 1.0 ohms. The timing controller immediately triggered an emergency self-destruct command, skipping the separation delay of the dispersing function and directly detonating it, shortening the separation interval of the self-destructing components to 0.2 seconds and accelerating the self-destruction process. When the secondary parachute opened, it encountered a crosswind of 5 meters per second. The timing controller adjusted the parachute line tension to stabilize the debris's descent velocity at 7.2 meters per second. After the self-destruction process was completed, the actual weight and descent velocity data of the debris were collected and compared with the preset target values ​​to calculate the deviation rate. The deviation rate was 2.3%, lower than the optimization threshold of 5%, and no adjustment of the baseline parameters was required.

[0046] II. Data Representation and Interpretation Table 2: Comparison of self-destruct performance of a 56mm two-stage rocket in a grassland in northern China

[0047] Table 2 shows that the data demonstrates the significant advantages of the two-stage coordinated self-destruction mechanism of this invention. The fall velocity of the first and second stage debris is significantly reduced due to the low-altitude parachute opening design and the dynamic adjustment of the parachute opening timing by the timing controller, eliminating the risk of debris damaging pastures. The improved separation success rate stems from the deep coordination between the separation and self-destruction timing, avoiding the overlap of the two-stage debris trajectories after separation, which could lead to mid-air collisions. The weight of the self-destructing debris in the seeding unit is reduced, thanks to the optimized pre-fabricated trough directional self-destruction and the dosage of the self-destructing agent, meeting safety standards. The deviation of the multi-launcher coordinated self-destruction is reduced through unified parameter calibration, adapting to the needs of large-area grassland hail suppression operations. Simultaneously, the emergency response mechanism can quickly respond to ignition circuit anomalies, ensuring the self-destruction process is safe and controllable, fully meeting the safety and reliability requirements for operations in grassland areas.

[0048] Reference Figure 2This figure highlights the stability and safety of the self-destruct structure of this invention. Traditional rocket self-destruct timing relies on mechanical timers, and time fluctuations cause the weight of the debris to fluctuate, exceeding the 100g safety threshold throughout the process, posing a risk of injury from impact. This invention relies on a timing controller with an acceleration sensor, combined with a three-explosion self-destruct assembly and directional ejection from a pre-formed trough. The self-destruct time is within the range of 21-27 seconds, and the debris weight remains below 95g with minimal fluctuations. This solves the problems of uneven energy distribution and excessive debris in traditional self-destruct systems.

[0049] Reference Figure 3 This figure illustrates the improved catalyst dispersal precision achieved by this invention. Traditional rockets use a fixed dispersal sequence; the higher the cloud layer, the greater the timing deviation, resulting in a continuous decline in utilization, reaching only 50% at 9km. This invention dynamically sets dispersal parameters through a timing controller, combined with switching between explosive / combustion dispersal methods. Due to its altitude advantage, the 56mm two-stage rocket achieves a utilization rate of 92% at 6km, and maintains 85% even at 9km. This stems from the coordinated control of the dispersal function and the self-destruct mechanism, ensuring the catalyst diffuses within the core area of ​​the target cloud, reducing waste and improving operational efficiency.

[0050] Reference Figure 4 This chart reflects the optimization of the production process by this invention. Traditional rockets use fixed propellant loading and separate self-destruct components. The more assembly steps there are, the more specialized fixtures and multiple rounds of calibration are required, drastically reducing efficiency; at 17 steps, only 5 rockets / hour are achieved. This invention simplifies the process by using free loading of the engine propellant (wrapping paper tape + adhesive positioning) and integrated assembly of the three-explosion self-destruct assembly. Even at 17 steps, it maintains an efficiency of 15 rockets / hour, and at 11 steps, it reaches 22 rockets / hour, far exceeding traditional designs. This aligns with the future market demand for rain-enhancing and hail-suppressing rockets, which is expected to increase from 100,000 to 200,000 units, and can meet the needs of large-scale production by improving efficiency.

[0051] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A method for the self-destruction of a prefabricated trough-type artificial weather modification rocket, characterized in that, Includes the following steps: Prefabricated trough processing and self-destruct component assembly steps: three prefabricated troughs (front, middle, and rear) are processed on the engine housing. The trough walls are turned and polished to ensure the flatness meets the standards. The three-explosive self-destruct assembly, including the head self-destruct body, the middle self-destruct body, and the tail self-destruct body, is fixed in the prefabricated trough with threads and adhesive. The self-destruct body contains a mixture of black powder and potassium boronitrate. The bottom of the ejection tube is aligned with the shear groove at the bottom of the prefabricated trough. Self-destruct parameter timing binding steps: Key parameters are bound using a timing controller with an acceleration sensor and in conjunction with the rocket's theoretical trajectory. After parameter binding, the timing logic is verified in the full-missile ground test facility. Post-launch flight status real-time monitoring steps: The rocket is launched from the launch pad, and the timing controller collects data on flight altitude, speed, acceleration, engine ignition circuit resistance, and propellant combustion status in real time; The segmented self-destruct triggering and coordinated control steps are as follows: Based on the key parameters in the configuration and the real-time data collected on flight altitude, speed, acceleration, engine ignition circuit resistance, and propellant combustion status, the timing controller determines that the self-destruction conditions are met and issues a self-destruction preparation signal. First, the separation and dispersing function of the separation ejection cartridge is ignited, and the catalyst dispersal is completed after a delay. Simultaneously, the self-destruct body separation cartridge is ignited, and the self-destruct body is ejected along the corresponding pre-fabricated slots in the order of head, middle, and tail. Self-destruction debris status verification steps: Use a timing controller and acceleration sensor to monitor the debris fragment status, and combine ground observations to confirm that all fragments weigh ≤100 grams; when the 56 mm two-stage rocket debris falls to an altitude of 500-800 meters, trigger the parachute separation cartridge to open the parachute, and when there is no debris remaining exceeding the safety threshold, the self-destruction process is completed.

2. The self-destruction method for a prefabricated trough-type artificial weather modification rocket according to claim 1, characterized in that, It also includes a self-destruct energy dynamic adjustment step. Before the self-destruct parameter timing is set, the self-destruct explosive dosage of each component is calculated based on the rocket shell material density and the target weight of the debris. The calculation formula is as follows: ,in This refers to the dosage of the self-destructing drug for a single self-destructing device; Density of the engine casing material; This refers to the total volume of the engine casing; The proportion of the target weight of the debris to the total weight of the shell; The number of self-destructing entities; The energy utilization rate of the self-destructing drug.

3. The self-destruction method for a prefabricated trough-type artificial weather modification rocket according to claim 1, characterized in that, It also includes a precast groove shear strength calibration step. After the precast groove is processed, a pressure testing device is used to apply a simulated projectile force to the precast groove and measure the actual force value when the precast groove breaks. The actual force value is compared with the rated projectile force of the self-destructing body separation box. If the actual force value is 10% or more higher than the rated projectile force, the depth of the shear groove is increased by turning process; if the actual force value is 10% or less lower than the rated projectile force, the depth of the shear groove is reduced by welding and polishing process until the shear strength of the precast groove matches the projectile force.

4. The self-destruction method for a prefabricated trough-type artificial weather modification rocket according to claim 1, characterized in that, The segmented self-destruct triggering and collaborative control steps also include a self-destruct delay time correction step, calculated using the following formula: ,in This is the revised self-destruct delay time; The self-destruct delay time is preset; This is the speed deviation correction factor; This refers to the actual flight speed of the rocket. The rated flight speed of the rocket; This is the height deviation correction factor; This refers to the actual flight altitude of the rocket. This is the rocket's rated flight altitude.

5. The self-destruction method for a prefabricated trough-type artificial weather modification rocket according to claim 1, characterized in that, It also includes a two-stage rocket self-destruction and parachute deployment coordinated control procedure. For a 56mm two-stage engine rocket, after the segmented self-destruction trigger and coordinated control procedure, when the first-stage engine casing debris falls freely to an altitude of 800 meters above the ground, the timing controller triggers the first-stage parachute system deployment command. After the first-stage parachute deploys, the deployment status is monitored by the tension sensor. The second-stage engine debris falls along a quasi-parabolic trajectory under the control of the blade tail fin. When the descent altitude is detected to drop to 500 meters, the second-stage parachute system deployment command is triggered, and the descent speed of the two-stage debris after deployment is recorded.

6. The self-destruction method for a prefabricated trough-type artificial weather modification rocket according to claim 1, characterized in that, It also includes emergency handling procedures for self-destruction anomalies. During the real-time flight status monitoring after launch, if the ignition circuit resistance exceeds the range of 0.55 to 1.0 ohms, or the self-destruct body separation delay exceeds the preset value by 20%, or the flight static stability is lower than 15%, the timing controller immediately triggers an emergency self-destruct command, skipping the separation delay of the dispersing function and directly detonating the dispersing function. At the same time, the self-destruct body separation interval is shortened to 0.2 seconds to accelerate the self-destruction process. If a parachute system malfunction is detected, for 56mm two-stage rockets, the dosage of the tail self-destruct body propellant is increased by 10% to 15%.

7. The self-destruction method for a prefabricated trough-type artificial weather modification rocket according to claim 1, characterized in that, The self-destruct parameter timing binding step also includes an altitude-based self-destruct parameter adaptation step. For medium- and high-altitude areas, the self-destruct parameters are adjusted according to the actual altitude of the operating area: for every 1,000 meters increase in altitude, the separation delay of the dispersing function is extended by 0.1 seconds and the separation delay of the self-destructing body is extended by 0.05 seconds, while the dosage of the self-destructing agent is increased by 5% to 8%; when the altitude is below 1,000 meters, the separation delay of the dispersing function is shortened by 0.05 seconds and the separation delay of the self-destructing body is shortened by 0.02 seconds, while the dosage of the self-destructing agent is reduced by 3% to 5%.

8. The self-destruction method for a prefabricated trough-type artificial weather modification rocket according to claim 1, characterized in that, It also includes a self-destruction effect feedback optimization step. After the debris status verification step is completed, the actual weight and fall velocity data of the debris after each self-destruction are collected and compared with the preset target value. If the deviation rate exceeds 5% for three consecutive times, the reference parameters in the self-destruction parameter timing binding step are adjusted: when the debris weight deviation exceeds the limit, the self-destruction drug dosage calculation coefficient is corrected; when the fall velocity deviation exceeds the limit, the parachute opening height threshold is adjusted to ±50 meters.

9. The self-destruction method for a prefabricated trough-type artificial weather modification rocket according to claim 1, characterized in that, The prefabrication tank processing and self-destruct component assembly process also includes a low-temperature environment adaptation process. For low-temperature operating environments ranging from -20 degrees Celsius to 0 degrees Celsius, low-temperature toughness materials are used during prefabrication tank processing, and low-temperature curing adhesives are selected for fixing the self-destruct body and the prefabrication tank. Five to ten percent of low-temperature sensitizers are added to the self-destruct kit. The timing controller is wrapped with thermal insulation cotton to ensure that the measurement error of the acceleration sensor at low temperatures is no more than 0.1 meters per second squared.

10. The self-destruction method for a prefabricated trough-type artificial weather modification rocket according to claim 1, characterized in that, It also includes a unified step for multi-launcher coordinated self-destruct parameters. When multiple launchers are operating simultaneously, whether they are of the same or different models, the self-destruct parameter setting data of each launcher rocket is received through the ground control station. The self-destruct separation delay and self-destruct trigger time of rockets of the same caliber are uniformly calibrated. After calibration, unified parameter instructions are issued to each launcher to ensure that the self-destruct process is orderly when multiple rockets are operating in coordination.

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