Multi-time quantitative single-pulse impact device and method for charging

Abstract

The invention relates to a charging multi-time quantitative monopulse impact device and method, and belongs to the technical field of safe ammunition. According to the invention, accurate and quantitative multi-time single-pulse impact can be carried out on the charge test piece, and uncontrollable multi-time loading caused by a stress wave propagation effect in previous multi-time impact is effectively avoided. Besides, through a programmable controller, various sensors and electrical equipment, automatic repeated impact on charging is achieved, and errors and safety risks caused by manual operation are avoided. According to the invention, multiple impact tests are carried out on the charge test piece, the damage accumulation evolution process when the charge is subjected to multiple constant-amplitude or specific load spectrum impact loading can be obtained, the damage can be quantitatively described due to the controllability of the loaded load, and a more accurate damage accumulation model can be further established; and a powerful support is provided for the stability design of the charge of the warhead.

Description

Technical Field

[0001] This invention belongs to the field of safe ammunition technology, specifically relating to a device and method for multiple quantitative single-pulse impact of propellant. Background Technology

[0002] When an anti-tank warhead penetrates a multi-layered, spaced target, the warhead charge is subjected to multiple impacts. Under impact loads, microcracks and micropores nucleate, grow, aggregate, and eventually fracture within the charge. This damage degrades the mechanical properties of the charge and causes material failure. It also significantly influences the formation of "hot spots," altering the charge's sensitivity, combustion, and detonation properties. Under repeated impacts, damage accumulates, altering parameters such as the impact initiation threshold, detonation velocity, and critical initiation diameter. This can lead to accidental ignition or deviations, affecting the warhead's destructive effect. Therefore, studying the damage characteristics and damage accumulation models of charges under repeated impact loading is crucial for ensuring the stability of the charge and for the high-precision design of anti-tank warheads.

[0003] Existing methods for multiple impact tests of propellant charges, such as Figure 1 As shown in (Nie Shaoyun, Xue Pengyi, Dai Xiaogan. Safety evaluation method of simulated multi-layer target penetration process [J]. Journal of Explosives and Pyrotechnics, 2020, 43(5): 537-542.), this method uses an accelerated drop device to accelerate the test piece and impact a target with a certain structure. The device structure of this method includes 101-base, 102-mounting base, 103-buffer pad, 104-outer sleeve, 105-inner sleeve, 106-charge, and 107-punch.

[0004] This method involves designing multi-layered spaced steel targets and a propellant loading structure. The multi-layered steel targets are spaced at specific intervals to simulate the spacing between targets during warhead penetration. The propellant loading structure adopts an inner and outer sleeve design. The outer sleeve is made of high-strength steel, providing circumferential constraint to simulate the warhead shell, while the inner sleeve is made of polytetrafluoroethylene (PTFE) to simulate the propellant loading structure. During the experiment, the targets are released and fall, impacting the propellant loading structure. The propellant loading structure impacts the multi-layered steel targets sequentially, achieving multiple impact loading of the propellant. The experimental setup can achieve impact loading with different stress peak values ​​by changing the speed, and the stress amplitude gradually decreases with each impact.

[0005] Figure 1This method can simulate multiple impacts on the propellant structure, mimicking the scenario of multiple impacts on a propellant in reality. However, the results obtained by this method still have some limitations in studying the cumulative damage of propellants from multiple impacts. The structure designed by this method, for multiple impacts of the propellant, involves multiple loading processes with gradually decreasing stress peaks. Since the peak values ​​of each loading process are different and uncontrollable, it is impossible to accurately and quantitatively test the damage of the propellant under multiple impacts. That is, it is impossible to know the degree of damage to the propellant structure after a specific number of impacts under a specific load, or the degree of damage under a specific load spectrum. Furthermore, without accurate quantitative test results, it is impossible to form an accurate and reliable cumulative damage model for propellant from multiple impacts, making it difficult to meet the needs of efficient digital design of warhead propellants.

[0006] Testing propellant using a split Hopkinson bar is more conducive to achieving quantitatively accurate multiple loading. In contrast, traditional Hopkinson bars inevitably cause secondary or multiple loading of the specimen due to stress wave propagation and repeated reflections. The conventional Hopkinson bar single-pulse loading method requires a very small gap to be left between the flange, sleeve, and mass block before the test, making it difficult to operate and demanding extremely high precision, thus making it unsuitable for direct application in automated multiple impact testing devices. Summary of the Invention

[0007] (a) Technical problems to be solved

[0008] The technical problem to be solved by this invention is to design an accurate quantitative repetitive impact loading device that can be used for loading drugs, so as to overcome the defects of existing technologies that are difficult to quantitatively load constant or variable amplitude impacts, as well as the difficulties of automated single-pulse loading of Hopkinson bars.

[0009] (2) Technical solution

[0010] To solve the above-mentioned technical problems, the present invention provides a device for multiple quantitative single-pulse impact of propellant, including a gas source 1, a gas charging solenoid valve 2, a cylinder 3, a pressure sensor 4, a launching solenoid valve 5, a vacuum pump 6, a vacuum pump solenoid valve 7, a gun barrel 8, an impact rod 9, a projectile sabot 10, a programmable controller 11, a position sensor 12, a servo motor 13, a push arm, a collar 15, a lead screw 16, an incident rod 17, a strain gauge, a propellant test piece 20, a constraint sleeve 21, and a transmission rod 22;

[0011] Gas source 1 is connected to cylinder 3, and the inflation process of cylinder 3 is controlled by inflation solenoid valve 2; pressure sensor 4 is installed on cylinder 3 to monitor the gas pressure value inside cylinder 3 in real time; barrel 8 is connected to cylinder 3 through firing solenoid valve 5, which is used to control the rapid deflation and firing process of cylinder 3; impact rod 9 slides inside barrel 8 through sabot 10, and the outer diameter of sabot 10 matches the inner diameter of barrel 8; position sensor 12 is arranged at the outlet of barrel 8 to monitor whether impact rod 9 has reached the outlet of barrel 8; after firing, impact rod 9 impacts incident rod 17 at a certain speed and generates an incident wave propagating to the right on incident rod 17, which propagates to the propellant charge in contact with the right end of incident rod 17. When test specimen 20 is loaded, part of the incident wave is reflected and propagates to the left on the incident rod 17, while the other part of the incident wave generates a transmitted wave that propagates to the right on the transmission rod 22 after loading the test specimen 20. There are three push arms, and corresponding lead screws 16 and servo motors 13 are also three. Each push arm and its corresponding lead screw 16 and servo motor 13 form a set of mechanical electric push arms, for a total of three sets. The push arm in each set of mechanical electric push arms is mounted on the corresponding lead screw 16, and the corresponding lead screw 16 is driven by the corresponding servo motor 13, which in turn drives the corresponding push arm to move. Each push arm does not contact the incident rod 17 or the transmission rod 22, and passes through a path with an inner diameter equal to the diameter of the incident rod 17 or the transmission rod 22.A ring with a diameter of 5 times or more is fitted onto the incident rod 17 and the transmission rod 22. The incident rod 17 and the transmission rod 22 move by pushing the ring 15 fixed to them. Three push arms, from left to right, can sequentially control the incident rod 17 to move to the right, the incident rod 17 to the left, and the transmission rod 22 to the left. The inner diameter of the constraint sleeve 21 matches the diameter of the incident rod 17 and the transmission rod 22, constraining the propellant sample 20 within the constraint sleeve 21. The vacuum pump 6 is connected to the bottom of the gun barrel 8 via a vacuum pump solenoid valve 7, creating a negative pressure inside the gun barrel 8. The impact rod 9 is recovered and returned to the bottom of the gun barrel 8 through the pressure difference. The inflation solenoid valve 2, pressure sensor 4, firing solenoid valve 5, vacuum pump solenoid valve 7, position sensor 12, and servo motor 13 are connected to the programmable controller 11 via wires. The programmable controller 11 uses... The device receives information from pressure sensor 4 and position sensor 12, and sends various on / off commands to control the operation of the inflation solenoid valve 2, firing solenoid valve 5, vacuum pump solenoid valve 7, and servo motor 13. There are two strain gauges: one on the incident rod 17, used to collect incident and reflected waves; the incident wave is the compression wave signal generated after the impact rod 9 strikes the incident rod 17, and the reflected wave is the waveform formed by the reflection of the incident wave at the contact surface between the incident rod 17 and the propellant sample 20; the other strain gauge 18 on the transmission rod 22 is used to collect transmitted waves, which are the waves that propagate from the incident wave through the propellant sample 20 to the transmission rod 22. When the device is arranged, the firing solenoid valve 5, gun barrel 8, sabot 10, collar 15, incident rod 17, propellant sample 20, constraint sleeve 21, and transmission rod 22 are arranged in a line on the same axis.

[0012] Preferably, the incident rod 17 is made of a low elastic modulus material.

[0013] Preferably, the incident rod 17 is made of nylon material.

[0014] Preferably, the transmission rod 22 is a metal rod or a metal tube.

[0015] Preferably, the device further includes a protective box 19, and the ends of the constraint sleeve 21, the charge test piece 20, and the incident rod 17 and the transmission rod 22 that are in contact with the charge test piece 20 are all located inside the protective box 19.

[0016] The present invention also provides a method for multiple quantitative single-pulse impact of drug delivery based on the aforementioned device.

[0017] Preferably, it includes the following steps:

[0018] (1) The programmable controller 11 controls the inflation solenoid valve 2 to open, and the air source 1 inflates the cylinder 3. When the output value of the pressure sensor 4 reaches the preset air pressure value, the programmable controller 11 controls the inflation solenoid valve 2 to close.

[0019] (2) The programmable controller 11 controls the launch solenoid valve 5 to open, the gas in the cylinder 3 is released rapidly, and the gas pushes the impact rod 9 to accelerate in the barrel 8.

[0020] (3) When the position sensor 12 senses that the impact rod 9 has reached the barrel muzzle, the programmable controller 11 controls the firing solenoid valve 5 to close and controls the vacuum pump solenoid valve 7 to open. A negative pressure is generated at the bottom of the barrel 8. The impact rod 9 is pushed back to the bottom of the barrel 8 under the action of the pressure difference. After a preset delay time, the programmable controller 11 controls the vacuum pump solenoid valve 7 to close.

[0021] (4) After the impact rod 9 impacts the incident rod 17, a compression wave is generated. The compression wave propagates backward and the waveform signal is collected by the strain gauge on the incident rod 17.

[0022] (5) When the compression wave reaches the charge specimen 20, it achieves a single impact loading on the charge specimen 20. The strain gauge on the transmission rod 22 collects the transmission wave signal and obtains the specimen load through processing.

[0023] (6) After an impact loading is completed, the three sets of mechanical electric push arms adjust the incident rod 17 and the transmission rod 22 to return to their initial positions, wherein the servo motor 13 operates under the control of the programmable controller 11;

[0024] (7) After the impact rod 9, the incident rod 17 and the transmission rod 22 return to their initial positions, repeat the above operation to achieve multiple impact loading.

[0025] (III) Beneficial Effects

[0026] This invention presents a device and method for multiple quantitative single-pulse impacts on propellant charges. This allows for precise and quantitative multiple single-pulse impacts on propellant test specimens, effectively avoiding the uncontrollable multiple loading caused by stress wave propagation effects in previous multiple impact methods. Furthermore, this invention achieves automated multiple impacts on the propellant charge through a programmable controller, various sensors, and electrical equipment, avoiding errors and safety risks associated with human operation. By conducting multiple impact tests on propellant test specimens using this invention, the cumulative damage evolution process of the propellant charge under multiple constant amplitude or specific load spectrum impacts can be obtained. The controllable loading load allows for quantitative description of the damage, further enabling the establishment of a more accurate damage accumulation model, providing strong support for the stability design of warhead propellants. Attached Figure Description

[0027] Figure 1 The schematic diagram of the multiple impact test method for explosive charges (Nie Shaoyun, Xue Pengyi, Dai Xiaogan. Safety evaluation method of explosive charge in simulated multi-layer target penetration process [J]. Journal of Explosives and Pyrotechnics, 2020, 43(5):537-542.);

[0028] Figure 2This is a schematic diagram of the multiple quantitative single-pulse impact test device for the propellant loading of the present invention;

[0029] Figure 3 The image shows the stress wave propagation XT diagram in the incident rod and the transmission rod of this invention.

[0030] Figure 4 This is a flowchart illustrating the implementation of the device of the present invention.

[0031] Among them, 101-base, 102-mounting base, 103-buffer pad, 104-outer sleeve, 105-inner sleeve, 106-charge, 107-punch;

[0032] 1-Gas source, 2-Inflation solenoid valve, 3-Cylinder, 4-Pressure sensor, 5-Launch solenoid valve, 6-Vacuum pump, 7-Vacuum pump solenoid valve, 8-Barrel, 9-Impact rod, 10-Ship sabot, 11-Programmable controller, 12-Position sensor, 13-Servo motor, 14-Push arm, 15-Lasso, 16-Lead screw, 17-Incident rod, 18-Strain gauge, 19-Protective box, 20-Pressure charge specimen, 21-Constraint sleeve, 22-Transmission rod. Detailed Implementation

[0033] To make the objectives, contents, and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples.

[0034] This invention designs an accurate, quantitative, and repetitive impact loading device for warheads, used to test the damage characteristics of warhead charges after multiple impact loadings. It can achieve multiple impact loadings with constant or variable amplitude load spectra, ensuring controllable loading waveforms and accurately determining the degree of damage and damage accumulation process of the charge under specific pulses at a specific number of times. This invention overcomes the shortcomings of existing technologies in quantitatively loading constant or variable amplitude impacts, as well as the difficulties in automated single-pulse loading with a Hopkinson bar. This invention can provide technical support for the study and modeling of damage behavior in warheads.

[0035] This invention, based on a split Hopkinson pressure bar, establishes an automated repetitive impact loading device for propellant charges, capable of quantitative multiple impacts with constant and variable amplitudes. The split Hopkinson pressure bar is chosen as the prototype due to its advantages, such as easily controllable waveform and real-time load monitoring. The device structure designed in this invention includes: 1. Gas source; 2. Inflating solenoid valve; 3. Cylinder; 4. Pressure sensor; 5. Launching solenoid valve (large-diameter launching solenoid valve); 6. Vacuum pump; 7. Vacuum pump solenoid valve; 8. Gun barrel; 9. Impact rod; 10. Projectile sabot; 11. Programmable controller; 12. Position sensor; 13. Servo motor; 14. Push arm; 15. Collar; 16. Lead screw; 17. Incident rod; 18. Strain gauge; 19. Protective box; 20. Propellant test piece; 21. Constraint sleeve; and 22. Transmission rod.Air source 1 is connected to cylinder 3, and the inflation process of cylinder 3 is controlled by inflation solenoid valve 2; pressure sensor 4 is installed on cylinder 3 to monitor the air pressure value inside cylinder 3 in real time; barrel 8 is connected to cylinder 3 through firing solenoid valve 5, which is used to control the rapid deflation and firing process of cylinder 3; impact rod 9 slides inside barrel 8 through sabot 10, and the outer diameter of sabot 10 is tightly fitted with the inner diameter of barrel 8; position sensor 12 is arranged at the outlet of barrel 8 to monitor whether impact rod 9 has reached the outlet of barrel 8; after firing, impact rod 9 impacts incident rod 17 at a certain speed and generates an incident wave propagating to the right on incident rod 17, the incident wave propagating to the point of contact with the right end of incident rod 17. When the test specimen 20 (the charge to be tested) is loaded, the test specimen 20 is subjected to a load. Part of the incident wave is reflected and propagates to the left on the incident rod 17, while the other part of the incident wave generates a transmitted wave that propagates to the right on the transmission rod 22 after loading the test specimen 20. The push arm 14 is mounted on the lead screw 16 and is driven by the servo motor 13, which in turn drives the push arm 14 to move. There are three push arms 14, and three corresponding lead screws 16 and servo motors 13. Each push arm 14 and its corresponding lead screw 16 and servo motor 13 form a set of mechanical-electric push arms, for a total of three sets. Each push arm 14 does not contact the incident rod 17 or the transmission rod 22, and passes through a path with an inner diameter equal to the diameter of the incident rod 17 and the transmission rod 22. A ring with a diameter of 5 times or more is fitted onto the incident rod 17 and the transmission rod 22. The incident rod 17 and the transmission rod 22 are moved by pushing the ring 15 fixed to them. Three push arms 14, from left to right, can control the incident rod 17 to move to the right, the incident rod 17 to the left, and the transmission rod 22 to the left, respectively. The constraint sleeve 21, the propellant sample 20, and the ends of the incident rod 17 and the transmission rod 22 that contact the propellant sample 20 are all located inside the protective box 19. The inner diameter of the constraint sleeve 21 is tightly fitted with the diameter of the incident rod 17 and the transmission rod 22, constraining the propellant sample 20 within the constraint sleeve 21. The vacuum pump 6 is connected to the bottom of the gun barrel 8 via a vacuum pump solenoid valve 7. This creates a negative pressure inside the barrel 8, and the impact rod 9 is recovered and returned to the bottom of the barrel 8 through the pressure difference. The inflation solenoid valve 2, pressure sensor 4, firing solenoid valve 5, vacuum pump solenoid valve 7, position sensor 12, and servo motor 13 are connected to the programmable controller 11 through wires. The programmable controller 11 is used to receive information from the pressure sensor 4, position sensor 12, etc., and send various on / off commands to control the operation of the inflation solenoid valve 2, firing solenoid valve 5, vacuum pump solenoid valve 7, and servo motor 13. When the device is arranged, the firing solenoid valve 5, barrel 8, sabot 10, collar 15, incident rod 17, propellant test piece 20, constraint sleeve 21, and transmission rod 22 are arranged in a row on the same axis.The strain gauge 18 on the incident rod 17 is used to collect the incident wave and reflected wave on the incident rod 17. The incident wave is the compression wave signal generated after the impact rod 9 impacts the incident rod 17. The reflected wave is the waveform formed by the reflection of the incident wave at the contact surface between the incident rod 17 and the charge specimen 20. The strain gauge 18 on the transmission rod 22 is used to collect the transmitted wave on the transmission rod 22. The transmitted wave is the incident wave that propagates to the transmission rod 22 after passing through the charge specimen 20.

[0036] In operation, the device of the present invention controls the actions of each component through a programmable controller 11, thereby achieving automated operation. (See reference) Figure 4 The specific implementation steps are as follows:

[0037] (1) The programmable controller 11 controls the inflation solenoid valve 2 to open, and the air source 1 inflates the cylinder 3. When the output value of the pressure sensor 4 reaches the preset air pressure value, the programmable controller 11 controls the inflation solenoid valve 2 to close.

[0038] (2) The programmable controller 11 controls the launch solenoid valve 5 to open, the gas in the cylinder 3 is released rapidly, and the gas pushes the impact rod 9 to accelerate in the barrel 8.

[0039] (3) When the position sensor 12 senses that the impact rod 9 has reached the barrel muzzle, the programmable controller 11 controls the firing solenoid valve 5 to close and controls the vacuum pump solenoid valve 7 to open. A negative pressure is generated at the bottom of the barrel 8. The impact rod 9 is pushed back to the bottom of the barrel 8 under the action of the pressure difference. After a preset delay time, the programmable controller 11 controls the vacuum pump solenoid valve 7 to close.

[0040] (4) After the impact rod 9 impacts the incident rod 17, a compression wave is generated. The compression wave propagates backward and the waveform signal is collected by the strain gauge 18 on the incident rod 17.

[0041] (5) When the compression wave reaches the charge specimen 20, it achieves a single impact loading on the charge. The strain gauge 18 on the transmission rod 22 collects the transmission wave signal, which can be processed to obtain the specimen load.

[0042] (6) After one impact loading is completed, the three sets of mechanical electric push arms (composed of servo motor 13, push arm 14, and lead screw 16) adjust the incident rod 17 and the transmission rod 22 to return to the initial position, wherein the servo motor 13 operates under the control of the programmable controller 11;

[0043] (7) After the impact rod 9, the incident rod 17 and the transmission rod 22 return to their initial positions, repeat the above operation to achieve multiple impact loading.

[0044] This invention modifies the traditional Hopkinson bar. The incident bar 17 is made of a low-modulus material (such as nylon), while the transmission bar 22 is made of a traditional metal bar or tube. This creates a significant difference in wave impedance between the incident bar 17 and the transmission bar 22, causing the incident bar 17 to rebound after a single impact load, thus avoiding secondary or multiple impacts on the specimen during traditional split Hopkinson bar tests. Due to the large difference in wave impedance and material modulus between the incident bar 17 and the transmission bar 22, their wave velocities differ significantly, with the wave velocity of the transmission bar 22 being approximately three times that of the incident bar 17. Therefore, the transmitted wave propagates back and forth multiple times within the bar before returning to the end in contact with the propellant-loaded specimen 20. Figure 3 As shown, the transmission rod 22 moves backward a certain distance before the end of the incident rod 17 that contacts the propellant sample 20 begins to move. Furthermore, due to the difference in wave impedance, the reflected wave on the incident rod 17 is primarily a compression wave. After one round trip, the reflected wave in the incident rod 17 will move in the opposite direction at the end that contacts the sample, i.e., it will rebound. In summary, the solution of this invention can achieve the separation of the incident rod 17 and the transmission rod 22 after one impact loading, preventing the propellant sample 20 from being subjected to uncontrollable secondary impact loading.

[0045] Furthermore, an automatic control system comprised of a programmable logic controller (PLC) 11, a pressure sensor 4, a position sensor 12, an inflation solenoid valve 2, a launch solenoid valve 5, a vacuum pump solenoid valve 7, and three sets of servo motors 17 fully automates the multiple impact loading of the propellant test specimen, avoiding the safety risks associated with manual operation. Before the test, the PLC 11 presets the number of loading cycles and the inflation pressure of the cylinder 3. The inflation pressure corresponds to the launch speed of the impact rod 9, and this is calibrated before the test. Through programming, different loading amplitudes can be achieved for each cycle, enabling multiple impact loading with complex load spectra.

[0046] Based on the above principles, the operation flowchart of the device of the present invention can be derived from... Figure 4 express.

[0047] It can be seen that the present invention has the following characteristics:

[0048] 1. In this invention, through the design of material wave impedance matching, there is a significant difference in the elastic modulus and wave velocity of the incident rod and the transmission rod. By utilizing the wave impedance difference and the time difference of the sample end face displacement, the incident rod and the transmission rod can be separated after one impact loading, so that the propellant sample is no longer subjected to uncontrollable secondary impact loading, and finally a quantitative single-pulse impact on the propellant sample can be achieved.

[0049] 2. The control system, composed of programmable logic controllers, sensors, and electrical devices, enables the traditional Hopkinson pressure bar to operate automatically, achieving automatic multiple impact loading on the propellant test specimen and avoiding the safety risks caused by human operation.

[0050] 3. By pre-programming and setting the inflation pressure for each loading, multiple loadings with a specific and complex load spectrum can be applied to the propellant test specimen.

[0051] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A device for multiple quantitative single-pulse impact of a propellant, characterized in that, It includes a gas source (1), a gas charging solenoid valve (2), a cylinder (3), a pressure sensor (4), a firing solenoid valve (5), a vacuum pump (6), a vacuum pump solenoid valve (7), a gun barrel (8), an impact rod (9), a sabot (10), a programmable controller (11), a position sensor (12), a servo motor (13), a push arm, a collar (15), a lead screw (16), an incident rod (17), a strain gauge, a charge test piece (20), a constraint sleeve (21), and a transmission rod (22); The air source (1) is connected to the cylinder (3), and the air filling process of the cylinder (3) is controlled by the air filling solenoid valve (2); the pressure sensor (4) is installed on the cylinder (3) to monitor the air pressure value in the cylinder (3) in real time; the gun barrel (8) is connected to the cylinder (3) through the firing solenoid valve (5), which is used to control the process of rapid air release and firing of the cylinder (3); the impact rod (9) slides inside the gun barrel (8) through the sabot (10), and the outer diameter of the sabot (10) matches the inner diameter of the gun barrel (8); the position sensor (12) is arranged at the outlet of the gun barrel (8) to monitor whether the impact rod (9) reaches the outlet of the gun barrel (8); after firing, the impact rod (9) impacts the incident rod (17) at a certain speed and generates an incident wave propagating to the right on the incident rod (17), and the incident wave propagates to the incident rod (17) 7) When the right end of the test piece (20) is in contact with the test piece (20), the test piece (20) is loaded. Part of the incident wave is reflected and propagates to the left on the incident rod (17). The other part of the incident wave is loaded on the test piece (20) and generates a transmission wave that propagates to the right on the transmission rod (22). There are three push arms, and there are also three corresponding lead screws (16) and servo motors (13). Each push arm and its corresponding lead screw (16) and servo motor (13) form a set of mechanical electric push arms. There are three sets in total. The push arm in each set of mechanical electric push arms is installed on the corresponding lead screw (16). The corresponding lead screw (16) is driven by the corresponding servo motor (13) and the corresponding push arm is moved in translation. Each push arm does not contact the incident rod (17) and the transmission rod (22). The inner diameter is 1 of the diameter of the incident rod (17) and the transmission rod (22).A ring of more than 5 times the diameter is fitted onto the incident rod (17) and the transmission rod (22). The incident rod (17) and the transmission rod (22) move by pushing the ring (15) fixed to them. Three push arms from left to right can sequentially control the incident rod (17) to move to the right, the incident rod (17) to the left, and the transmission rod (22) to the left. The inner diameter of the constraint sleeve (21) matches the diameter of the incident rod (17) and the transmission rod (22), allowing the test charge to be loaded. The component (20) is constrained within the constraint sleeve (21); the vacuum pump (6) is connected to the bottom of the gun barrel (8) via the vacuum pump solenoid valve (7), causing a negative pressure to be generated inside the gun barrel (8), and the impact rod (9) is recovered and returned to the bottom of the gun barrel (8) through the pressure difference; the inflation solenoid valve (2), pressure sensor (4), firing solenoid valve (5), vacuum pump solenoid valve (7), position sensor (12), and servo motor (13) are respectively connected to the programmable controller (11) via wires. The programmable controller (11) is used to receive information from the pressure sensor (4) and position sensor (12), and send various on / off commands to control the operation of the inflation solenoid valve (2), firing solenoid valve (5), vacuum pump solenoid valve (7), and servo motor (13); there are two strain gauges. The strain gauge 18 on the incident rod (17) is used to collect the incident wave and reflected wave on the incident rod (17). The incident wave is the compression wave signal generated after the impact rod (9) hits the incident rod (17), and the reflected wave is the incident wave after the impact rod (9) hits the incident rod (17). The waveform formed by reflection from the contact surface of the test specimen (20) and the incident wave; the strain gauge 18 on the transmission rod (22) is used to collect the transmitted wave on the transmission rod (22), which is the transmitted wave that propagates from the incident wave through the test specimen (20) to the transmission rod (22); when the device is arranged, the firing solenoid valve (5), the gun barrel (8), the sabot (10), the collar (15), the incident rod (17), the test specimen (20), the constraint sleeve (21), and the transmission rod (22) are arranged in a row on the same axis.

2. The apparatus as claimed in claim 1, characterized in that, The incident rod (17) is made of a low elastic modulus material.

3. The apparatus as described in claim 1, characterized in that, The incident rod (17) is made of nylon.

4. The apparatus as described in claim 3, characterized in that, The transmission rod (22) is made of metal rod or metal tube.

5. The apparatus as claimed in claim 1, characterized in that, The solenoid valve (5) is a large-diameter solenoid valve for launching.

6. The apparatus as claimed in claim 1, characterized in that, The device also includes a protective box 19, and the ends of the constraint sleeve (21), the charge test piece (20), and the incident rod (17) and the transmission rod (22) that are in contact with the charge test piece (20) are all located inside the protective box 19.

7. The apparatus as claimed in claim 1, characterized in that, The device can be used to test the damage characteristics of warhead charges after multiple impact loading.

8. A method for multiple quantitative single-pulse impact of a propellant, implemented using the apparatus described in any one of claims 1 to 7.

9. The method as described in claim 8, characterized in that, Includes the following steps: (1) The programmable controller (11) controls the inflation solenoid valve (2) to open, and the air source (1) inflates the cylinder (3). When the output value of the pressure sensor (4) reaches the preset air pressure value, the programmable controller (11) controls the inflation solenoid valve (2) to close. (2) The programmable controller (11) controls the launch solenoid valve (5) to open, the gas in the cylinder (3) is released quickly, and the gas pushes the impact rod (9) to accelerate in the barrel (8); (3) When the position sensor (12) senses that the impact rod (9) has reached the barrel muzzle, the programmable controller (11) controls the firing solenoid valve (5) to close and controls the vacuum pump solenoid valve (7) to open. A negative pressure is generated at the bottom of the barrel (8). The impact rod (9) is pushed back to the bottom of the barrel (8) under the action of the pressure difference. After a preset delay time, the programmable controller (11) controls the vacuum pump solenoid valve (7) to close. (4) After the impact rod (9) impacts the incident rod (17), a compression wave is generated. The compression wave propagates backward and the waveform signal is collected by the strain gauge on the incident rod (17). (5) When the compression wave reaches the charge test piece (20), it realizes the first impact loading on the charge test piece (20). The strain gauge on the transmission rod (22) collects the transmission wave signal and obtains the test piece load through processing. (6) After an impact loading is completed, the three sets of mechanical electric push arms adjust the incident rod (17) and the transmission rod (22) to return to their initial positions, wherein the servo motor (13) operates under the control of the programmable controller (11); (7) After the impact rod (9), the incident rod (17) and the transmission rod (22) return to their initial positions, repeat the above operation to achieve multiple impact loading.

10. The method as described in claim 9, characterized in that, Before the test, the programmable controller (11) presets the number of impact loadings and the air pressure of the cylinder (3).

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