Artificial influence weather rocket projectile three-explosion self-destruction body assembly detection system

Abstract

The invention discloses an artificial influence weather rocket projectile three-explosion self-destruction body assembly detection system, and relates to the technical field of multivariable comprehensive measurement, and the system comprises a multi-dimensional positioning measurement module which is used for measuring the coaxiality and fitting pressure of a self-destruction body and an engine housing; the multi-parameter measuring module is filled with the medicament to measure the weight, density and internal defects of the medicament; the connection strength dynamic measurement module is used for measuring torque, tensile strength and vibration displacement; the igniter performance parameter measuring module is used for measuring resistance, time delay and safety reliability; the measurement data integration analysis module is used for integrating a data generation report and an encryption log; and the system control and exception handling module is used for coordinating module time sequences, monitoring data and handling exceptions. According to the system, multi-parameter integrated measurement of the three-explosion self-destruction body is realized, the measurement precision of positioning, medicament filling, connection strength and igniter performance is improved, the remain after self-destruction is ensured to be compliant, and the data is traceable.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of multivariate comprehensive measurement, and particularly relates to a weather modification rocket bomb three-explosion self-destruction body assembly detection system. BACKGROUND

[0002] The weather modification rocket bomb is the core equipment for rain enhancement and hail prevention operation, and its safety and reliability directly determine the operation effect and the safety of ground personnel and property. The self-destruction body assembly quality is a key link to ensure that the residual debris after the operation of the rocket bomb is in compliance (≤100g) and to avoid ground risks. At present, the assembly of the self-destruction body of the rocket bomb in the industry mainly relies on manual operation and simple tools. The coaxiality and fitting pressure of the self-destruction body and the engine shell in the assembly process lack precise control, and the problem of excessive positioning deviation of the self-destruction body often occurs, which leads to uneven distribution of residual debris after self-destruction, and the weight of part of the residual debris exceeds the safety threshold, increasing the risk of injury to ground personnel.

[0003] In the self-destruction body agent filling link, the existing detection means mainly stays at manual weighing and visual inspection, and cannot accurately measure the agent filling density and internal defects. Uneven agent density will lead to unbalanced self-destruction energy release, and part of the area will have incomplete self-destruction due to low agent density, forming large mass residual debris. Defects such as holes and cracks in the agent will cause local energy concentration, which may cause early explosion accidents. In addition, there is a lack of systematic detection of the environmental adaptability of the self-destruction body after assembly in the industry. In the storage and use environment of -20℃ to 50℃, the agent is easy to absorb moisture and form lumps due to changes in temperature and humidity, and the connection part of the self-destruction body is easy to loosen due to material thermal expansion and cold contraction, leading to self-destruction efficiency decay, which is difficult to meet the reliability requirements of 3 years of storage period.

[0004] Although there are some single parameter detection devices in the current industry, there is a lack of integrated measurement system integrating positioning, agent, connection strength and igniter performance. The data of each detection link is independently stored, and it is impossible to realize multi-parameter correlation analysis and self-destruction efficiency prediction. The detection process relies on manual recording and data comparison, which is not only low in efficiency, but also easy to cause data tampering and omission, leading to unqualified products flowing into the market. At the same time, the detection equipment lacks a regular calibration mechanism, and the accuracy of the sensor decreases with the use time, further affecting the reliability of the detection data, which is difficult to support quality control in the process of large-scale production of rocket bombs, and cannot meet the market demand of doubling the demand for rain enhancement and hail prevention rocket bombs in the next 5-10 years. An efficient, accurate and integrated self-destruction body assembly detection system is needed to solve the above problems. SUMMARY

[0005] An assembly detection system for the three-explosion self-destruction body of an artificial weather modification rocket proposed by the present invention is used to solve the problems mentioned in the above-mentioned prior art.

[0006] To achieve the above object, the present invention adopts the following technical solutions: A multi-parameter measurement system for the assembly of the three-explosion self-destruction body of an artificial weather modification rocket includes the following modules: A multi-dimensional positioning measurement module measures the assembly positioning parameters of the three-explosion self-destruction body and the rocket engine housing, equipped with an adjustable positioning tooling suitable for an engine housing with a diameter of φ55.9mm~φ56.26mm, integrating a laser displacement sensor and a pressure sensor, and outputting coaxiality data and fitting pressure data in real time; A multi-parameter measurement module for propellant loading works in coordination with the multi-dimensional positioning measurement module to comprehensively measure the propellant loading parameters of the self-destruction medicine box of the three-explosion self-destruction body, including a weight measurement unit, a density measurement unit, and a defect detection unit; A dynamic measurement module for connection strength measures the connection strength parameters between the three-explosion self-destruction bodies and between the self-destruction body and the housing, including a torque measurement unit, a tensile force measurement unit, and a vibration displacement measurement unit; A measurement module for the performance parameters of the igniter measures the key performance parameters of the igniter supporting the three-explosion self-destruction body, including a resistance measurement unit, a delay measurement unit, and an insurance reliability measurement unit; A measurement data integration and analysis module is connected to the above-mentioned measurement modules, receives and integrates multi-dimensional measurement data, has a built-in standard database, compares the real-time data with the standard data, calculates the deviation rate, generates a multi-parameter measurement report, and encrypts and stores the measurement log with a non-tamperable hash value; A system control and exception handling module, as the core coordination unit, is connected to each measurement module and the data integration and analysis module, controls the measurement timing, monitors the data in real time, stops the process and triggers an alarm when the tolerance is exceeded, and at the same time monitors the status of the measurement equipment and records the operating parameters.

[0007] Furthermore, it further includes a self-destruction efficiency correlation measurement module, which is connected to the multi-parameter measurement module for propellant loading and the dynamic measurement module for connection strength, and calculates the predicted value of the maximum debris mass after self-destruction through an association formula. The formula is Where is the predicted value of the maximum debris mass after self-destruction, is the total mass of the three-explosion self-destruction body and the corresponding housing part, is the efficiency correlation coefficient, is the actual propellant loading density, obtained by the density measurement unit, is the designed standard density of the propellant, is the actual connection strength, obtained by the tensile force measurement unit, The standard value for connection strength is designed; the relationship between agent loading, connection strength and the mass of self-destructing debris is established through this formula.

[0008] Furthermore, it also includes an environmental adaptability measurement module, which is connected to the system control and anomaly handling module. This module simulates the storage and use environment of rockets, measures the impact of environmental factors on assembly parameters, controls environmental parameters through an environmental test chamber, and calculates the parameter attenuation rate using an environmental impact measurement formula. The formula is as follows: in The overall attenuation rate of assembly parameters. This refers to the measured mass of the reagent after environmental testing. This refers to the measured mass of the reagent before the experiment. This is the measured value of the connection strength after the test. The connection strength measurement value is the value measured before the test; ≤5%, indicating that the environmental impact on assembly parameters meets the requirements.

[0009] Furthermore, the laser displacement sensor of the multi-dimensional positioning measurement module adopts a two-dimensional scanning mode. The measurement data is transmitted to the system control and anomaly handling module in real time via industrial Ethernet. When the coaxiality deviation exceeds 0.3mm, the system automatically controls the fine-tuning mechanism of the positioning fixture to make corrections until the deviation meets the requirements. The pressure sensor adopts a piezoelectric structure and outputs a fitting pressure curve in real time.

[0010] Furthermore, the X-ray flaw detector of the reagent loading multi-parameter measurement module is equipped with an image recognition unit. It uses a deep learning model to identify defects in the flaw detection images. The model training sample contains more than 1,000 reagent images of different defect types. The recognition results automatically mark the defect location, size and type. Defect types include cavities and cracks. The defect parameters are converted into quantitative data and stored in the measurement data integration and analysis module. The quantitative data includes cavity volume and crack length.

[0011] Furthermore, the electromagnetic vibration table of the connection strength dynamic measurement module supports two modes: sinusoidal vibration and random vibration. Sinusoidal vibration is used to simulate the transient impact of launch, while random vibration is used to simulate the flight process. During vibration, the frame rate of the high-speed camera can be adjusted, and the displacement of the connection part is automatically calculated through image processing algorithms.

[0012] Furthermore, the timing recorder of the ignition device performance parameter measurement module supports multi-channel synchronous measurement, and can simultaneously measure the delay time of multiple ignition devices. During measurement, the ignition devices are connected through a special gold-plated test fixture. The drop hammer impact tester of the safety reliability measurement unit is equipped with an impact force sensor to monitor the actual impact force in real time during the impact process.

[0013] Furthermore, the standard database of the measurement data integration and analysis module contains the design parameters, measurement thresholds, and qualification standards for the 56mm caliber rocket triple self-destruct system. The database supports regular updates, which require administrator authorization and must be logged. The hash value of the measurement log is bound to the measurement report. Each log entry contains a unique hash value and forms a chain relationship with the hash value of the previous entry. Modifying any log entry will cause the hash chain to break. Log storage uses a combination of local encryption and cloud backup.

[0014] Furthermore, the system control and anomaly handling module adopts an industrial-grade PLC controller, equipped with a 10.1-inch touch screen human-machine interface. The interface displays the measurement data of each module, the working status of the equipment, and abnormal information in real time. The measurement data is presented in numerical and curve form. In automatic mode, each module starts measurement in sequence according to the preset process. In manual mode, a certain module can be controlled independently. The system also has a data export function. Measurement reports and logs can be exported. The exported files require password verification.

[0015] Furthermore, it also includes a measurement equipment calibration module, which connects to all measurement equipment in the system and periodically calibrates the measurement accuracy of the equipment. The calibration cycle is configured according to the equipment type. The calibration cycle for weighing sensors is once a quarter, and the calibration cycle for laser displacement sensors is once every six months. Calibration is performed using standard parts, including standard weights, standard length gauge blocks, and standard resistors. Calibration data is automatically recorded to the measurement data integration and analysis module. When the equipment calibration error exceeds the allowable range, the module issues a calibration warning and locks the equipment until calibration is completed.

[0016] Compared with existing technologies, the beneficial effects of this invention are: This invention achieves precise assembly of the self-destructing device and the engine housing through a multi-dimensional positioning and measurement module. Laser displacement and pressure sensors work in tandem to effectively control coaxiality deviation and fitting pressure, ensuring consistent positioning of the self-destructing device and reducing the risk of substandard debris quality from the assembly stage. The multi-parameter measurement module for the chemical agent filling integrates weight, density, and defect detection functions to accurately identify uneven filling and internal defects, preventing incomplete self-destruction or premature detonation due to chemical issues, and improving the stability and safety of the self-destruction process.

[0017] The connection strength dynamic measurement module comprehensively evaluates the connection reliability between self-destructing components and between the self-destructing component and the shell through multi-dimensional testing of torque, tension, and vibration, avoiding self-destruction failures caused by loose connections or insufficient strength. The ignition device performance parameter measurement module accurately detects resistance, delay, and fuse reliability, ensuring stable operation of the ignition device in complex environments and preventing accidental ignition or delay deviations from affecting the self-destruction sequence. The measurement data integration and analysis module realizes multi-parameter correlation and standardized comparison, generating tamper-proof audit logs to ensure the authenticity and traceability of test data, reduce human operation errors, and improve testing efficiency and quality control.

[0018] The environmental adaptability measurement module and the self-destruct effectiveness correlation measurement module further expand the system's functionality. The former simulates complex environments to verify assembly stability, ensuring that the rockets meet the requirements for long-term storage and use in different regions; the latter predicts self-destruct effectiveness in advance, avoiding rework of defective products and reducing production costs. The overall system achieves integrated, automated, and precise self-destruct body assembly and testing, significantly improving the assembly quality and safety of rocket self-destruct bodies, providing reliable equipment support for weather modification operations, and adapting to the needs of large-scale production, thus contributing to the high-quality development of the industry. Attached Figure Description

[0019] Figure 1 This is a schematic block diagram of an assembly and testing system for a three-stage self-destruct mechanism of a weather modification rocket, as proposed in this invention. Figure 2 A bar chart comparing the weight of the debris after self-destruction of 44mm and 56mm rockets; Figure 3 A line graph showing the change in ballistic pressure inside the engine of a 56mm rocket; Figure 4 Line graph showing the effect of ambient temperature on the self-destruct delay time of rockets; Figure 5 A bar chart comparing the connection strength of different parts of a three-explosion self-destructing body; Figure 6 Line graph showing the relationship between rocket launch altitude and catalyst seeding amount. Detailed Implementation

[0020] 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.

[0021] 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.

[0022] 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.

[0023] Reference Figures 1 to 6 A multi-parameter measurement system for the assembly of a three-explosion self-destruct mechanism of a weather-modification rocket, comprising the following modules: The multi-dimensional positioning and measurement module measures the assembly positioning parameters of the three self-destructing bodies (head, middle, and tail self-destructing bodies) and the rocket engine casing. It is equipped with an adjustable positioning fixture adapted to the outer diameter of the 56mm caliber engine casing, with an outer diameter range of φ55.9mm~φ56.26mm. The fixture integrates laser displacement sensors and pressure sensors. Three sets of laser displacement sensors are arranged along the casing axis to measure the coaxiality between the self-destructing body and the casing axis. Pressure sensors are embedded in the self-destructing body assembly station to measure the contact pressure between the self-destructing body and the casing. It outputs coaxiality data and contact pressure data in real time. The allowable coaxiality deviation is ≤0.3mm, and the qualified contact pressure range is 50-80N. The multi-parameter measurement module for agent filling works in conjunction with the multi-dimensional positioning measurement module to comprehensively measure the agent filling parameters of the self-destructing explosive cartridge. It includes a weight measurement unit, a density measurement unit, and a defect detection unit. The weight measurement unit uses a high-precision weighing sensor with an accuracy of 0.01g to measure the weight of a single self-destructing explosive cartridge, with a weight deviation ≤2% of the design value. The density measurement unit measures the agent filling thickness using an ultrasonic thickness gauge and calculates the filling density based on the cartridge volume, with a density deviation controlled within ±3% of the design value. The defect detection unit uses a micro-focus X-ray flaw detector with a focal size of 5μm to detect internal voids and cracks in the explosive, capable of identifying defects ≥0.1mm. Connection strength dynamic measurement module, which measures the connection strength parameters between the three-explosion self-destruction bodies and between the self-destruction bodies and the housing. It includes a torque measurement unit, a tensile force measurement unit, and a vibration displacement measurement unit. The torque measurement unit applies a preset torque through a torque wrench. The accuracy of the torque wrench is ±1%, and the preset torque is 1.2 times the design value, which is used to measure the torque attenuation of the threaded connection, and the allowable attenuation ≤ 5%; the tensile force measurement unit applies an axial tensile force through a tensile testing machine to measure the tensile strength of the connection part, and the qualified value of the tensile strength ≥ 95% of the design value; the vibration displacement measurement unit uses an electromagnetic vibration table to simulate the launch vibration environment. The frequency range of the vibration table is 10 - 2000Hz. The displacement of the connection part is measured by a high-speed camera. The frame rate of the high-speed camera ≥ 1000fps, and the allowable displacement ≤ 0.2mm; Igniter performance parameter measurement module, which measures the key performance parameters of the igniter supporting the three-explosion self-destruction body. It includes a resistance measurement unit, a delay measurement unit, and an insurance reliability measurement unit. The resistance measurement unit uses a high-precision ohmmeter. The accuracy of the ohmmeter is ±0.01Ω, which is used to measure the resistance value of the igniter, and the resistance is maintained within the range of 0.55 - 1.0Ω; the delay measurement unit uses a timing recorder to record the delay time from the power-on of the igniter to ignition. The timing accuracy of the timing recorder ≤ 1μs, and the delay deviation ≤ 5% of the design value; the insurance reliability measurement unit simulates an accidental impact through a drop hammer impact testing machine. The impact force of the drop hammer impact testing machine is 500N, and the action time is 10ms, which is used to measure the locking state of the insurance mechanism. No accidental ignition is judged as qualified; Measurement data integration and analysis module, which is connected to the above measurement modules, receives and integrates multi-dimensional measurement data, and has a standard database for the assembly measurement of three-explosion self-destruction bodies built-in. It compares the real-time measurement data with the standard data, calculates the deviation rate of each parameter, generates a multi-parameter measurement report, marks the out-of-tolerance parameters and the out-of-tolerance amplitude in the report, and at the same time records the measurement process information. The measurement process information includes the measurement personnel, the measurement time, and the measurement equipment number, generates an immutable measurement log, and the log is encrypted and stored using a hash value. The encryption algorithm is SHA-256; System control and exception handling module, as the core coordination unit, is connected to the multi-dimensional positioning measurement module, the multi-parameter measurement module for propellant filling, the connection strength dynamic measurement module, the igniter performance parameter measurement module, and the measurement data integration and analysis module. It controls the measurement timing of each module, sets the measurement parameter thresholds, monitors the measurement data in real time. When a parameter out-of-tolerance is detected, it immediately stops the current measurement process and triggers an audible and visual alarm, displays the out-of-tolerance module and the out-of-tolerance parameters, supports restarting the measurement after manual adjustment, and at the same time has a function of monitoring the status of the measurement equipment, recording the equipment operation parameters. The equipment operation parameters include the sensor accuracy and the equipment working duration.

[0024] This invention also includes a self-destruct performance correlation measurement module, which is connected to a multi-parameter measurement module for agent loading and a dynamic measurement module for connection strength. Based on the agent loading density and connection strength measurement data, it calculates the predicted maximum debris mass after self-destruction using a correlation formula, which is: in This is the predicted maximum mass of the debris after self-destruction. This refers to the total mass of the three self-destructing components and their corresponding shell parts. This is the performance correlation coefficient, with a value ranging from 0.85 to 0.95, determined based on the number of self-destructing medicine boxes. The actual filling density of the drug is obtained from the density measuring unit. To design standard densities for pharmaceutical preparations, The actual connection strength is obtained from the tensile force measurement unit. The standard value for connection strength is designed; the relationship between agent loading, connection strength and self-destruction debris mass is established through this formula, so as to realize the early measurement and prediction of self-destruction performance, with a predicted value ≤100g, and avoid rework caused by substandard self-destruction performance after assembly.

[0025] This invention also includes an environmental adaptability measurement module, which is connected to the system control and anomaly handling module. This module simulates the storage and use environment of rockets, measuring the impact of environmental factors on assembly parameters. Environmental conditions include temperature, humidity, and low pressure. The temperature range is -20℃ to 50℃, the humidity range is 30%RH to 90%RH, and the low pressure simulates an altitude of 5km. Environmental parameters are controlled through an environmental test chamber. Assembly parameters are measured before and after the test using various measurement modules. The parameter attenuation rate is calculated using an environmental impact measurement formula, which is: in The overall attenuation rate of assembly parameters. This refers to the measured mass of the reagent after environmental testing. This refers to the measured mass of the reagent before the experiment. This is the measured value of the connection strength after the test. The connection strength measurement value is the value measured before the test; ≤5% indicates that the impact of the environment on the assembly parameters meets the requirements. This module realizes the quantitative measurement of environmental adaptability and ensures the assembly stability of the rocket during its 3-year storage period.

[0026] In this invention, the laser displacement sensor of the multi-dimensional positioning measurement module adopts a two-dimensional scanning mode with a scanning frequency ≥1000Hz and a scanning accuracy ≤0.01mm. The measurement data is transmitted to the system control and anomaly handling module in real time via industrial Ethernet. When the coaxiality deviation exceeds 0.3mm, the system automatically controls the fine-tuning mechanism of the positioning fixture to make corrections. The fine-tuning mechanism has an adjustment accuracy of 0.005mm until the deviation meets the requirements. The pressure sensor adopts a piezoelectric structure with a range of 0-200N and a resolution of 0.1N. It outputs a fitting pressure curve in real time to observe the pressure change trend during the assembly process.

[0027] In this invention, the X-ray flaw detector of the reagent loading multi-parameter measurement module is equipped with an image recognition unit. It uses a deep learning model to identify defects in the flaw detection images. The model training sample includes more than 1,000 sets of reagent images with different defect types. The defect recognition accuracy is ≥98%. The recognition results automatically mark the defect location, size and type. The defect location accuracy is ±0.5mm. The defect types include cavities and cracks. The defect parameters are converted into quantitative data and stored in the measurement data integration and analysis module. The quantitative data includes cavity volume and crack length.

[0028] In this invention, the electromagnetic vibration table connected to the dynamic strength measurement module supports two modes: sinusoidal vibration and random vibration. Sinusoidal vibration is used to simulate the transient impact of launch, with a vibration frequency of 50Hz and an acceleration of 200m / s². 2 The duration was 0.5 s, and random vibration was used to simulate the flight process. The vibration frequency range was 10-2000 Hz, and the acceleration power spectral density was 0.01 g. 2 / Hz, the frame rate of the high-speed camera during vibration is adjustable, with an adjustment range of 500-2000fps. The displacement of the connection part is automatically calculated through image processing algorithm without manual intervention, and the measurement error is ≤0.02mm.

[0029] In this invention, the timing recorder of the ignition device performance parameter measurement module supports multi-channel synchronous measurement, up to 8 channels, and can simultaneously measure the delay time of multiple ignition devices. During measurement, the ignition device is connected through a special gold-plated test fixture with a contact resistance ≤0.01Ω to avoid interference from contact resistance on the measurement results. The drop hammer impact tester of the safety reliability measurement unit is equipped with an impact force sensor to monitor the actual impact force in real time during the impact process, ensuring that the impact parameters meet the simulation requirements. The allowable deviation of the impact parameters is 500N±50N.

[0030] In this invention, the standard database of the measurement data integration and analysis module contains the design parameters, measurement thresholds, and qualification standards for the 56mm caliber rocket triple self-destruct system. The database supports regular updates with a configurable update cycle, the default being once a month. Updates require administrator authorization and must be logged. The hash value of the measurement log is bound to the measurement report. Each log entry contains a unique hash value, which forms a chain with the hash value of the previous entry. Modifying any log entry will break the hash chain, ensuring the authenticity of the logs. Log storage uses a combination of local encryption and cloud backup, with the local encryption algorithm being AES-256.

[0031] In this invention, the system control and anomaly handling module adopts an industrial-grade PLC controller with a processing speed of ≥1μs / step. It is equipped with a 10.1-inch touchscreen human-machine interface, which displays the measurement data of each module, the working status of the equipment, and anomaly information in real time. The measurement data is presented in the form of numerical values ​​and curves. It supports both manual and automatic measurement modes. In automatic mode, each module starts measurement sequentially according to a preset process. In manual mode, a single module can be controlled independently. The system also has a data export function. Measurement reports and logs can be exported as PDF or Excel format. The exported files require password verification, and the password contains uppercase and lowercase letters, numbers, and special symbols.

[0032] This invention also includes a measurement equipment calibration module, which connects to all measurement equipment within the system. These devices include load cells, laser displacement sensors, torque wrenches, X-ray flaw detectors, and time-series recorders. The module periodically calibrates the measurement accuracy of the equipment, with the calibration cycle configured according to the equipment type. Load cells are calibrated quarterly, and laser displacement sensors are calibrated semi-annually. Calibration is performed using standard components, including standard weights, standard length gauge blocks, and standard resistors. Calibration data is automatically recorded to the measurement data integration and analysis module. When the equipment calibration error exceeds the allowable range (≤2%), the module issues a calibration warning and locks the equipment until calibration is complete, ensuring reliable measurement data.

[0033] The following two examples further illustrate the specific implementation of this system: Example 1: Assembly and Measurement of the Three-Destruction Self-Destruction Body of a 56mm Self-Destruct Rain-Enhancing and Hail-Suppressing Rocket This embodiment is applied to the assembly and testing of the three-explosion self-destruct body of a 56mm self-destructing rain-inducing and hail-suppressing rocket. The target product meets the technical requirements of outer diameter φ55.9mm~φ56.26mm, projectile length 889mm±3mm, and total weight 2.60kg±0.10kg. The three-explosion self-destruct body includes a head self-destruct body, a middle self-destruct body, and a tail self-destruct body. This system realizes integrated measurement of multiple parameters. The specific process is as follows.

[0034] I. Multi-dimensional positioning and measurement operation The 56mm rocket engine casing is fixed to an adjustable positioning fixture of a multi-dimensional positioning measurement module. The fixture is mechanically fine-tuned to fit the casing's outer diameter of φ56.1mm. Three sets of laser displacement sensors are arranged along the casing's axis, with a scanning frequency of 1200Hz and a scanning accuracy of 0.008mm, to collect real-time coaxiality data between the self-destructing device and the casing axis. A piezoelectric pressure sensor with a range of 0-200N and a resolution of 0.1N is embedded in the self-destructing device assembly station to monitor the contact pressure between the self-destructing device and the casing. When assembling the head self-destructing body, the laser sensor showed a coaxiality deviation of 0.22mm and the pressure sensor reading was 65N, both within the acceptable range. The allowable coaxiality value is ≤0.3mm, and the acceptable bonding pressure range is 50-80N. When assembling the middle self-destructing body, the coaxiality deviation increased to 0.35mm. The system controlled the tooling fine-tuning mechanism to correct it. The fine-tuning mechanism's adjustment accuracy was 0.005mm, and the deviation finally stabilized at 0.25mm. The bonding pressure was 62N, meeting the assembly requirements.

[0035] II. Measurement of reagent filling and connection strength Pharmaceutical Filling Measurement: The weight measurement unit of the multi-parameter pharmacy filling measurement module uses a weighing sensor with an accuracy of 0.01g to weigh the self-destructing powder box of the three-explosive self-destructing device. The self-destructing powder box is filled with a mixture of black powder and potassium borate nitrate. The head self-destructing powder box is designed to weigh 25g, and the actual measured weight is 24.8g, with a deviation of 0.8%; the middle powder box is designed to weigh 28g, and the actual measured weight is 28.2g, with a deviation of 0.7%; the tail powder box is designed to weigh 26g, and the actual measured weight is 25.9g, with a deviation of 0.4%. All deviations are ≤2% of the allowable deviation. The density measurement unit measures the pharmacy filling thickness using an ultrasonic thickness gauge and calculates the filling density based on the powder box volume. The head powder box has a volume of 50cm³. 3 The central medicine box has a volume of 55cm². 3 The volume of the medicine box at the tail is 52cm. 3 The calculated head density is 1.2 g / cm³. 3 The density of the middle part is 1.22 g / cm³. 3 Tail density 1.18 g / cm³ 3 All deviations were within ±3% of the design value. The defect detection unit activated the micro-focus X-ray flaw detector with a focal size of 5μm to scan the cartridge. No voids or cracks with a size ≥0.1mm were found, and the cartridge was determined to have no internal defects.

[0036] Connection strength measurement: The torque measurement unit of the connection strength dynamic measurement module uses a torque wrench with an accuracy of ±1% to apply a preset torque to the threaded connection between the three self-destructing bodies. The design value is 25 N·m, and the preset torque is 1.2 times the design value, specifically 30 N·m. The measured torque attenuation is 1.2 N·m, with an attenuation rate of 4%, and an allowable value of ≤5%. The tensile force measurement unit applies axial tensile force to the connection between the self-destructing body and the shell using a tensile testing machine, measuring a tensile strength of 4800 N. The design value is 5000 N, and the qualified value is ≥95% of the design value. The specific value of 95% of the design value is 4750 N. 4800 N ≥ 4750 N meets the requirements. The vibration displacement measurement unit uses an electromagnetic vibration table to simulate the launch vibration environment, initially running in sinusoidal vibration mode with a vibration frequency of 50 Hz and an acceleration of 200 m / s². 2 The duration is 0.5s, simulating transient impact; then it runs in random vibration mode with a vibration frequency of 10-2000Hz and an acceleration power spectral density of 0.01g. 2 / Hz, simulating flight process, high-speed camera frame rate set to 1500fps, recording the displacement of the connection part, maximum value 0.15mm, allowable displacement ≤0.2mm.

[0037] III. Measurement of Ignition Device Performance and Self-Destruct Effectiveness Ignition device performance measurement: The resistance measurement unit of the ignition device performance parameter measurement module uses an ohmmeter with an accuracy of ±0.01Ω to test the resistance of the self-destructing double-safety ignition device. The reading is 0.75Ω, which is within the acceptable range of 0.55~1.0Ω. The delay measurement unit records the delay time from power-on to ignition of the ignition device using a timing recorder. The timing recorder has a timing accuracy of 0.8μs, and the average of 3 measurements is 0.85s, while the design value is 0.8s, with a deviation of 6.25%. After adjusting the ignition device wiring, the deviation is reduced to 4.5%, which is within the allowable value of ≤5%. The safety reliability measurement unit simulates accidental impact using a drop hammer impact tester. The drop hammer impact tester has an impact force of 500N and an action time of 10ms. After the impact, the ignition device circuit status is checked using a multimeter, which shows that the safety mechanism is locked and there is no accidental ignition.

[0038] Self-destruct effectiveness correlation measurement: Based on agent loading density and bonding strength data, the predicted maximum debris mass after self-destruction is calculated using a self-destruct effectiveness correlation formula. The formula is as follows: .in This is the predicted maximum mass of the debris after self-destruction. The total mass of the three self-destructing components and their corresponding shell parts is taken as 0.8 kg; The efficiency correlation coefficient is set to 0.9 and is determined based on the number of self-destructing medicine boxes. In this embodiment, the number of self-destructing medicine boxes is 3. The actual filling density of the drug, obtained by the density measuring unit, is taken as 1.2 g / cm³.3 ; The standard density for the pharmaceutical preparation is set at 1.2 g / cm³. 3 ; The actual connection strength is obtained from the tensile force measurement unit and is taken as 4800N; The standard value for connection strength is 5000N. Substituting this into the calculation yields... =0.8×(1-0.9×1×0.96)=0.8×(1-0.864)=0.8×0.136=0.1088kg=108.8g, close to the 100g threshold. Upon inspection, it was found that the drug density in the tail compartment was slightly low. After adding 0.2g of drug, the calculation was recalculated. Adjusted to 1.21 g / cm³ 3 Substituting into =0.8×(1-0.9×1.008×0.96)=0.8×(1-0.873)=0.8×0.127=0.1016kg=101.6g, after further adding 0.1g of medicine, Adjusted to 1.22 g / cm³ 3 Calculated =0.8×(1-0.9×1.017×0.96)=0.8×(1-0.881)=0.8×0.119=0.0952kg=95.2g, which meets the requirements.

[0039] IV. Environmental Adaptability and Data Integration The environmental adaptability measurement module simulated a -20℃ low-temperature environment in an environmental test chamber. After 48 hours of continuous placement, the drug filling mass and connection strength were remeasured: Head drug box mass 24.7g, pre-test mass 24.8g; Middle drug box mass 28.1g, pre-test mass 28.2g; Tail drug box mass 25.8g, pre-test mass 25.9g; Connection strength 4750N, pre-test connection strength 4800N. The parameter decay rate was calculated using the environmental impact formula, which is: .in The overall attenuation rate of assembly parameters. The measured value of the drug filling mass after environmental testing was selected as 28.1g for the middle medicine box. The measured value of the drug filling mass before the experiment was selected as 28.2g for the middle medicine box; The measured value of the connection strength after the test is 4750 N; The measured connection strength value before the test is 4800 N. Substituting this value into the calculation yields... =1-(28.1×4750) / (28.2×4800)=1-(133475) / (135360)=1-0.986=0.014=1.4%, ≤5% allowable attenuation rate. The measurement data integration and analysis module compares all parameters with the standard database, which contains the design parameters, measurement thresholds, and qualification standards for the 56mm caliber rocket triple self-destruct body. After comparison, a measurement report is generated, marking all parameters as qualified, and a hash-encrypted measurement log is generated. The encryption algorithm is SHA-256. The log records the measurement personnel, measurement time, and equipment number.

[0040] V. Data Representation and Interpretation Table 1: Comparison of Measurement Indicators for the Triple Destruction Self-Destruct Body Assembly of 56mm Rockets

[0041] Table 1 shows that traditional single-device measurement has significant shortcomings: the coaxiality deviation of the self-destructing device is 0.45mm, exceeding the acceptable threshold, which can easily lead to imbalance in the self-destructing device's positioning and affect the uniform release of energy during self-destruction; the internal defect identification rate of the agent is only 82%, which may miss internal voids or cracks, leading to the risk of premature detonation; the connection strength measurement error is ±3.5%, making it difficult to accurately judge the reliability of the connection; the ignition delay measurement accuracy is ±0.05s, and excessive deviation can easily lead to disordered self-destruction timing; the self-destruction effectiveness prediction accuracy is 65%, often resulting in rework after assembly and increasing production costs. This system, through the collaborative work of multiple modules, controls the coaxiality deviation of the self-destructing device within the acceptable range of 0.25mm, increases the agent defect identification rate to 99%, reduces the connection strength measurement error to ±0.08%, optimizes the ignition delay measurement accuracy to ±0.01s, and achieves a self-destruction effectiveness prediction accuracy of 98%, effectively preventing unqualified products from entering subsequent processes. At the same time, the system reduces manual operation, shortening the assembly and measurement time of a single rocket from the traditional 40 minutes to 15 minutes, significantly improving production efficiency and meeting the needs of large-scale production.

[0042] Example 2: Assembly and Measurement of the Triple Destruction Body of a 44mm Rain-Enhancing and Hail-Suppressing Rocket This embodiment is applied to the assembly and testing of the three-explosion self-destruct body of a 44mm rain-inducing and hail-suppressing rocket. The target product has a diameter of 44mm, a length of 750mm, and a total weight of 1.3kg. The three-explosion self-destruct body is adapted to the engine casing structure. After self-destruction, the weight of the debris is required to be ≤100g. The system achieves full parameter measurement, and the process is as follows.

[0043] I. Positioning and Drug Filling Measurement A 44mm engine housing is fixed to an adjustable positioning fixture of a multi-dimensional positioning measurement module. The fixture is adapted to the 44mm outer diameter of the housing via a mechanical structure. Three sets of laser displacement sensors are arranged along the housing axis, with a scanning frequency of 1000Hz and a scanning accuracy of 0.01mm. The sensors collect real-time coaxiality data between the self-destructing head and the housing axis, with a measured value of 0.28mm, and an acceptable allowable value of ≤0.3mm. A piezoelectric pressure sensor embedded in the self-destructing head assembly station has a range of 0-200N and a resolution of 0.1N, and measures a contact pressure of 58N, which is within the acceptable range of 50-80N. During the chemical filling measurement, the weight measurement unit used a weighing sensor with an accuracy of 0.01g to weigh the self-destructing explosive cartridges of the three-explosive self-destruct device: the head cartridge was designed to weigh 20g, and the actual measured weight was 19.9g, a deviation of 0.5%; the middle cartridge was designed to weigh 22g, and the actual measured weight was 22.1g, a deviation of 0.45%; the tail cartridge was designed to weigh 21g, and the actual measured weight was 20.9g, a deviation of 0.48%. All deviations were ≤2% of the allowable value. The density measurement unit measured the chemical filling thickness using an ultrasonic thickness gauge and calculated the filling density based on the cartridge volume. The head cartridge volume was 42cm³. 3 The central medicine box has a volume of 45cm. 3 The volume of the medicine box at the tail is 43cm. 3 The calculated average density of the drug is 1.15 g / cm³. 3 The standard density is 1.17 g / cm³. 3 The deviation was 1.2%, within the allowable range of ≤±3%. The defect detection unit activated the micro-focus X-ray flaw detector with a focal size of 5μm to scan the cartridge. No defects ≥0.1mm were found, indicating that the filling quality of the reagent was qualified.

[0044] II. Connection Strength and Ignition Device Measurement In the connection strength measurement, the torque measurement unit used a torque wrench with an accuracy of ±1% to apply a preset torque to the threaded connection between the three self-destructing bodies. The design value was 18.3 N·m, and the preset torque was 1.2 times the design value, specifically 22 N·m. The measured torque attenuation was 0.9 N·m, with an attenuation rate of 4.1%, which is ≤5% of the allowable value. The tensile force measurement unit applied axial tensile force to the connection between the self-destructing body and the shell using a tensile testing machine, measuring a tensile strength of 3800 N. The design value was 3900 N, and the pass value requirement was ≥95% of the design value. The specific value of 95% of the design value is 3705 N. 3800 N ≥ 3705 N, which meets the requirement. The vibration displacement measurement unit used an electromagnetic vibration table to simulate the launch vibration environment. It first operated in a sinusoidal vibration mode with a vibration frequency of 45 Hz and an acceleration of 180 m / s². 2 The duration is 0.5s; then it runs in random vibration mode with a vibration frequency of 10-1800Hz and an acceleration power spectral density of 0.01g. 2 / Hz, the high-speed camera frame rate was set to 1200fps, recording the displacement of the connection parts, with a maximum value of 0.18mm and an allowable displacement of ≤0.2mm. In the ignition performance measurement, the resistance measurement unit used an ohmmeter with an accuracy of ±0.01Ω to test the resistance of the self-destructing double-safety ignition device, with a reading of 0.65Ω, within the acceptable range of 0.55-1.0Ω. The delay measurement unit recorded the delay time using a timing recorder with a timing accuracy of 0.9μs; the average of three measurements was 0.9s, the design value was 0.85s, and the deviation was 5.9%. After adjusting the ignition device terminals, the deviation decreased to 4.8%, within the allowable value of ≤5%. The fuse reliability measurement unit simulated an accidental impact using a drop hammer impact tester with an impact force of 500N and an action time of 10ms. After the impact, a multimeter test showed that the fuse mechanism was locked normally, and there was no accidental ignition.

[0045] III. Self-destruct effectiveness and environmental measurement In the self-destruct effectiveness correlation measurement, based on the agent loading density and bonding strength data, the predicted maximum debris mass after self-destruction is calculated using the self-destruct effectiveness correlation formula, which is as follows: .in The total mass of the three self-destructing bodies and their corresponding shell parts is taken as 0.6 kg; The efficiency correlation coefficient is set to 0.88, determined based on the number of three self-destructing medicine boxes. The actual packing density of the drug is taken as 1.15 g / cm³. 3 ; The standard density for the pharmaceutical preparation is set at 1.17 g / cm³. 3 ; The actual connection strength is set at 3800N; The standard value for connection strength is 3900N. Substituting this into the calculation yields... =0.6×(1-0.88×(1.15 / 1.17)×(3800 / 3900))=0.6×(1-0.88×0.983×0.974)=0.6×(1-0.847)=0.6×0.153=0.0918kg=91.8g, which meets the requirement of ≤100g. The environmental adaptability measurement module simulates a 50℃ high temperature and 90%RH humidity environment in an environmental test chamber. After 48 hours of continuous placement, the filling mass and connection strength of the reagent are remeasured: Head box mass 19.8g, 19.9g before the test; Middle box mass 22.0g, 22.1g before the test; Tail box mass 20.8g, 20.9g before the test; Connection strength 3720N, 3800N before the test. The parameter decay rate is calculated using the environmental impact formula, which is: .in The weight of the middle medicine box is 22.0g. The weight of the middle medicine box was 22.1g. The value is 3720N. Taking the value 3800N, substituting it into the calculation yields... =1-(22.0×3720) / (22.1×3800)=1-(81840) / (84000)=1-0.974=0.026=2.6%, ≤5% allowable attenuation rate.

[0046] IV. Data Representation and Interpretation Table 2: Comparison of Measurement Indicators for the Triple Destruction Body Assembly of 44mm Rockets

[0047] Table 2 shows that traditional single-device measurements have several shortcomings in the assembly of 44mm rockets: bonding pressure fluctuations of ±8N are too large, easily leading to uneven tightness in the assembly of the self-destructing component, affecting separation accuracy during self-destruction; propellant density measurement deviations of ±4.2% exceed the allowable range, potentially causing imbalance in self-destruction energy release and resulting in excessive debris; post-vibration connection displacement of 0.35mm exceeds the acceptable threshold, increasing the risk of self-destructing component detachment during flight; ignition device resistance measurement error of ±0.08Ω is too large, easily leading to abnormal ignition; and the post-environment performance retention rate is only 88%, which is insufficient to meet the reliability requirements for a 3-year storage period. This system, through high-precision sensors and multi-module collaboration, reduces bonding pressure fluctuations to ±1.5N, controls propellant density measurement deviations to ±1.2%, reduces post-vibration connection displacement to 0.18mm, optimizes ignition device resistance measurement error to ±0.02Ω, and improves post-environment performance retention rate to 97.4%, comprehensively ensuring assembly quality. Meanwhile, the system enables automatic data integration and traceability, avoiding errors in manual recording. The defect rate of 50 rockets per batch has been reduced from the traditional 12% to 1%, significantly reducing production costs and improving production efficiency.

[0048] Reference Figure 2 This figure visually demonstrates the stability of the self-destruction effect of the two types of rocket self-destruction bodies. The data shows that the weight of the debris from each batch of 44mm and 56mm rockets is controlled within the range of 88-98g, far below the technical requirement of ≤100g, and the weight fluctuation between different batches of the same caliber is small (maximum fluctuation of 7g for both 44mm and 56mm). This indicates that the segmented detonation design and integrated sealing structure adopted by the triple-explosive self-destruction body are highly effective, ensuring that the debris from different calibers and batches of rockets is lightweight after self-destruction, avoiding ground safety risks caused by excessive debris. It also demonstrates the consistency of the self-destruction structure in large-scale production, providing data support for the safety of weather modification operations.

[0049] Reference Figure 3This figure reflects the combustion stability and internal ballistic performance of the 56mm rocket engine's dual-base propellant. The data shows that within a 0.2-1.0s combustion cycle, the internal ballistic pressure remains consistently within the 5.4-5.5MPa range, closely matching the initial equilibrium pressure and the final equilibrium pressure (both 5.5MPa), with no significant fluctuations. This is attributed to the engine's use of a single-hole tubular dual-base propellant design, where internal and external combustion ensure uniform combustion rate. Combined with precise nozzle throat diameter adjustment, this effectively controls pressure changes during combustion. Stable internal ballistic pressure not only guarantees the rocket's launch velocity and flight stability but also provides a stable power foundation for sequential actions such as self-destruct separation and catalyst dispersal, preventing functional unit malfunctions due to pressure fluctuations.

[0050] Reference Figure 4 This diagram illustrates the environmental adaptability of the rocket's self-destruct delay system. The document requires the self-destruct time to be controlled within the range of 24 ± 2.5 seconds. As the data shows, even with significant temperature variations ranging from -20℃ (extreme low temperature) to 50℃ (extreme high temperature), the self-destruct delay time consistently remains within the range of 23.9-25.8 seconds, fully meeting the technical requirements. Furthermore, the deviation from the 23.9 seconds at room temperature (25℃) is minimal (maximum deviation 1.9 seconds). This is due to the low hygroscopicity and high stability of the black powder and boron / potassium nitrate igniters used in the self-destruct delay ignition system. Combined with the heat insulation protection of the insulating tube and glass cloth structure, this effectively resists the impact of temperature changes on the burning rate of the delay agent, ensuring precise and controllable self-destruct sequence when the rocket operates in different regions and seasons, avoiding premature or delayed self-destruction due to delay anomalies.

[0051] Reference Figure 5 This diagram illustrates the connection reliability of the integrated, fully enclosed design of the triple-explosive self-destruct mechanism. Data shows that the tensile strength of each independent part (head, middle, and tail) and the joints (head-middle, middle-tail) of the self-destruct mechanism are all within the range of 3900-4200N, exhibiting balanced strength with no obvious weak points. This is attributed to the threaded + adhesive combination connection method used in the triple-explosive self-destruct mechanism. The threads ensure mechanical connection strength, while the adhesive fills gaps and enhances sealing. Simultaneously, the integrated structure reduces the risk of fire. Sufficient and balanced connection strength ensures that the self-destruct mechanism does not detach or loosen during rocket flight until the preset self-destruct sequence is triggered, preventing premature separation due to connection failure and further guaranteeing the rocket's flight stability and self-destruct reliability.

[0052] Reference Figure 6This figure reflects the synergy between rocket launch altitude and catalyst dispersal effect. The 56mm rocket has a maximum launch altitude of 7.5km, corresponding to a maximum catalyst dispersal amount of 180g (compliant with the document's technical specifications). The data shows that as the launch altitude increases from 4km to 7.5km, the catalyst dispersal amount exhibits a steady increasing trend, and the higher the launch altitude, the closer the dispersal amount is to the maximum value. This is directly related to the design advantages of the two-stage engine structure—after the first-stage engine overcomes low-altitude drag, the second-stage engine efficiently accelerates at mid-to-high altitudes, providing conditions for sufficient catalyst dispersal at higher cloud layers (areas requiring rain enhancement and hail suppression operations). Simultaneously, the orderly change in dispersal amount with launch altitude indicates that the combustion and dispersal function unit and the second-stage engine have precise timing control, dynamically adjusting the dispersal amount according to flight altitude to ensure efficient catalyst coverage at different altitudes, thus improving the effectiveness of weather modification operations.

[0053] 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 multi-parameter measurement system for a three-explosion self-destruct mechanism assembly of a weather-modification rocket, characterized in that, It includes the following modules: Multi-dimensional positioning measurement module, which measures the assembly positioning parameters of the three-explosion self-destruction body and the rocket engine casing, equipped with an adjustable positioning tooling suitable for engine casings with a caliber of φ55.9mm~φ56.26mm, integrating a laser displacement sensor and a pressure sensor, and outputting coaxiality data and fitting pressure data in real time; Pharmaceutical filling multi-parameter measurement module, which works in cooperation with the multi-dimensional positioning measurement module to comprehensively measure the pharmaceutical filling parameters of the self-destruction medicine box of the three-explosion self-destruction body, including a weight measurement unit, a density measurement unit, and a defect detection unit; Connection strength dynamic measurement module, which measures the connection strength parameters between the three-explosion self-destruction bodies and between the self-destruction body and the casing, including a torque measurement unit, a tensile force measurement unit, and a vibration displacement measurement unit; Igniter performance parameter measurement module, which measures the key performance parameters of the igniter supporting the three-explosion self-destruction body, including a resistance measurement unit, a delay measurement unit, and an insurance reliability measurement unit; Measurement data integration and analysis module, which is connected to the above-mentioned measurement modules, receives and integrates multi-dimensional measurement data, has a built-in standard database, compares the real-time data with the standard data, calculates the deviation rate, generates a multi-parameter measurement report and a tamper-proof hash value to encrypt and store the measurement log; System control and exception handling module, which serves as the core coordination unit, is connected to each measurement module and the data integration and analysis module, controls the measurement timing, monitors the data in real time, stops the process and triggers an alarm when the tolerance is exceeded, and at the same time monitors the status of the measurement equipment and records the operating parameters.

2. The multi-parameter measurement system for the assembly of a three-explosion self-destruct body of a weather modification rocket according to claim 1, characterized in that, It also includes a self-destruct effectiveness correlation measurement module, which is connected to the agent loading multi-parameter measurement module and the connection strength dynamic measurement module. This module calculates the predicted maximum debris mass after self-destruction using a correlation formula, which is: in This is the predicted maximum mass of the debris after self-destruction. This refers to the total mass of the three self-destructing components and their corresponding shell parts. The efficiency correlation coefficient, The actual filling density of the drug is obtained from the density measuring unit. To design standard densities for pharmaceutical preparations, The actual connection strength is obtained from the tensile force measurement unit. The standard value for connection strength is designed; the relationship between agent loading, connection strength and the mass of self-destructing debris is established through this formula.

3. The multi-parameter measurement system for the assembly of a three-stage self-destruct mechanism of a weather modification rocket according to claim 1, characterized in that, It also includes an environmental adaptability measurement module, which connects to the system control and anomaly handling module. This module simulates the storage and use environment of rockets, measures the impact of environmental factors on assembly parameters, controls environmental parameters through an environmental test chamber, and calculates the parameter attenuation rate using an environmental impact measurement formula. The formula is as follows: in The overall attenuation rate of assembly parameters. This refers to the measured mass of the reagent after environmental testing. This refers to the measured mass of the reagent before the experiment. This is the measured value of the connection strength after the test. The connection strength measurement value is the value measured before the test; ≤5%, indicating that the environmental impact on assembly parameters meets the requirements.

4. The multi-parameter measurement system for the assembly of a three-explosion self-destruct body of a weather modification rocket according to claim 1, characterized in that, The laser displacement sensor of the multi-dimensional positioning measurement module adopts a two-dimensional scanning mode, and the measurement data is transmitted to the system control and exception handling module in real time through the industrial Ethernet. When the coaxiality deviation exceeds 0.3mm, the system automatically controls the fine-tuning mechanism of the positioning tooling for correction until the deviation meets the requirements; the pressure sensor adopts a piezoelectric structure and outputs the fitting pressure curve in real time.

5. A multi-parameter measurement system for the assembly of a three-stage self-destruct mechanism of a weather modification rocket according to claim 1, characterized in that, The X-ray flaw detector of the pharmaceutical filling multi-parameter measurement module is equipped with an image recognition unit, which uses a deep learning model to identify defects in the flaw detection images. The model training samples include more than 1000 groups of pharmaceutical images of different defect types. The recognition results automatically mark the defect positions, sizes and types. The defect types include voids and cracks, and the defect parameters are converted into quantitative data and stored in the measurement data integration and analysis module. The quantitative data includes void volume and crack length.

6. The multi-parameter measurement system for the assembly of a three-explosion self-destruct body of a weather modification rocket according to claim 1, characterized in that, The electromagnetic vibration table of the connection strength dynamic measurement module supports two modes: sine vibration and random vibration. Sine vibration is used to simulate the transient impact during launch, and random vibration is used to simulate the flight process. The frame rate of the high-speed camera can be adjusted during the vibration process, and the displacement of the connection part is automatically calculated through the image processing algorithm.

7. A multi-parameter measurement system for the assembly of a three-stage self-destruct mechanism of a weather modification rocket according to claim 1, characterized in that, The timing recorder of the igniter performance parameter measurement module supports multi-channel synchronous measurement and can measure the delay times of multiple groups of igniters at the same time; when measuring, the igniters are connected through a special gold-plated test tooling; the drop hammer impact testing machine of the insurance reliability measurement unit is equipped with an impact force sensor to monitor the actual impact force during the impact process in real time.

8. A multi-parameter measurement system for the assembly of a three-stage self-destruct mechanism of a weather modification rocket according to claim 1, characterized in that, The standard database of the measurement data integration and analysis module contains the design parameters, measurement thresholds, and qualification standards for the 56mm caliber rocket triple self-destruct system. The database supports regular updates, which require administrator authorization and must be logged. The hash value of the measurement log is bound to the measurement report. Each log entry contains a unique hash value and forms a chain relationship with the hash value of the previous entry. Modifying any log entry will break the hash chain. Log storage uses a combination of local encryption and cloud backup.

9. A multi-parameter measurement system for the assembly of a three-stage self-destruct mechanism of a weather modification rocket according to claim 1, characterized in that, The system control and fault handling module adopts an industrial-grade PLC controller and is equipped with a 10.1-inch touch screen human-machine interface. The interface displays the measurement data of each module, the working status of the equipment, and fault information in real time. The measurement data is presented in numerical and curve form. In automatic mode, each module starts measurement in sequence according to the preset process. In manual mode, a certain module can be controlled independently. The system also has a data export function. Measurement reports and logs can be exported. Password verification is required for exported files.

10. A multi-parameter measurement system for the assembly of a three-explosion self-destruct body of a weather modification rocket according to claim 1, characterized in that, It also includes a measurement equipment calibration module, which connects to all measurement equipment in the system and periodically calibrates the measurement accuracy of the equipment. The calibration cycle is configured according to the equipment type. The calibration cycle for weighing sensors is once a quarter, and the calibration cycle for laser displacement sensors is once every six months. Calibration is performed using standard parts, including standard weights, standard length gauge blocks, and standard resistors. Calibration data is automatically recorded to the measurement data integration and analysis module. When the equipment calibration error exceeds the allowable range, the module issues a calibration warning and locks the equipment until calibration is completed.

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