CN113701979B - Wide pulse high g value acceleration test system, test method and application - Google Patents
Wide pulse high g value acceleration test system, test method and application Download PDFInfo
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The test method is that the gas generated by the rapid combustion of the deflagration propellant pushes the projectile to generate an excitation acceleration pulse signal with the amplitude of 20000-150000 g and the pulse width of 1-5 ms in the short pipe cannon, and provides a test device and a test method for the calibration of the high-g value accelerometer and the impact resistance research of the missile-borne electronic instrument; the test device and the test method have advanced technical performance and can be applied to: traceability calibration of the high-g-value accelerometer, survival research of the missile-borne electronic instrument under the high-g-value impact environment and the like. The test device has the advantages that the acceleration of the projectile in the launching process can be accurately obtained, and the micro-damage recovery of the projectile under the high-speed flight condition is realized.
Description
Technical Field
The invention discloses a wide-pulse high-g-value acceleration test system and a method, belongs to the technical field of impact tests and calibration, and particularly relates to a wide-pulse high-g-value acceleration test system and a test method and application of the test method.
Background
In modern warfare, a plurality of military targets with important strategic values are transferred to the ground, and firm protective measures are adopted, so that the effects of advanced hard-breaking weapons such as penetration or drilling are more and more prominent, and the military targets are the subjects of competitive development of various military countries. For such penetration weapons, the selection of the timing of initiation by the intelligent fuze is critical to fully exploit the maximum destructive power of the weapon. Because key components such as a fuse and the like are subjected to high-amplitude acceleration overload with the duration of several milliseconds and the amplitude of several tens of thousands of g in the penetration process, the high overload can cause the failure of the fuse component and irrecoverable loss, a set of acceleration simulation equipment with wide pulse and high g value is urgently needed to check the working state and the viability of each component, discover the problems as soon as possible, and take measures to solve the problems, thereby improving the reliability of the component in a severe environment.
Typical impact acceleration simulation test devices mainly comprise Hopkinson rods, ma Xiete hammers, drop test stands, gas cannons and the like. The Hopkinson rod is widely used as a generating device of high-g-value excitation pulse, uses compressed air as a power source, generates different overload values through different air pressures, has the highest overload value of 200000g, has more convenient test on the overload value and structural performance, has simple and easy operation process, and has the defects that the pulse duration is short and the pulse width is only tens of microseconds when more than 100000 g. The Ma Xiete hammer impacts the anvil through the hammer head to generate impact acceleration, and simulates overload environmental force born by the fuze when the projectile impacts the target, and the amplitude of the acceleration pulse can reach 50000g at the moment, but the pulse width is only a few microseconds. The drop test bed is to install the tested piece on the test bed, lift the table to a certain height, make the test piece and the test bed drop freely on the elastic or plastic waveform generator, they receive an acceleration pulse of approximate half sine, the peak acceleration can reach 100000g, the duration is tens of microseconds. The gas gun uses high-pressure gas to push the projectile to accelerate along the gun barrel, collides with a module provided with an accelerometer, changes the material of a contact surface to generate signals with different amplitudes and durations, and the acceleration pulse amplitude generated by the gas gun device is generally 50000-150000 g, and the pulse duration is tens to hundreds of microseconds. The characteristics of these devices are that when the amplitude of the acceleration pulse is large, the pulse duration is difficult to reach the millisecond level, so for the acceleration with amplitude exceeding 100000g and pulse width reaching the millisecond level, no device can be realized at present.
The projectile breaks instantaneously at the moment of entry into still water at high velocity (> 1000 m/s). For complete and reliable recovery of the projectile, it is necessary to reduce the density of the water, i.e. the foam water. So far, various types of soft recovery methods exist, among which the most sophisticated is the sectional foam water recovery method, but the disadvantages are that the structure is complicated and the foam water with different densities is not easy to produce.
Disclosure of Invention
The invention designs a wide-pulse high-g-value acceleration test system and a method, which are used for generating excitation acceleration pulse signals with the amplitude of 20000-150000 g and the pulse width of 1-5 ms in a short tube gun by pushing a projectile through high-pressure gas generated by rapid combustion of a deflagration propellant, so as to provide a test device and a test method for calibration of a high-g-value accelerometer and impact resistance research of an missile-borne electronic instrument; the test device and the test method have advanced technical performance and can be applied to: traceability calibration of the high-g-value accelerometer, survival research of the missile-borne electronic instrument under the high-g-value impact environment and the like.
In order to solve the existing calibration or experimental system: wide pulse excitation cannot be generated, but narrow pulses are easy to excite the natural frequency of the sensor to bring about larger calibration errors; system level calibration in the application environment cannot be performed; the invention provides a wide-pulse high-g-value acceleration test system and a method, which cannot be used for carrying out a simulation experiment on an airborne electronic instrument under an application environment.
The technical scheme of the invention comprises a wide pulse high g value acceleration test system and method and application of the method.
A wide pulse high g value acceleration simulation test system comprises: the device is characterized in that the wide pulse high g value acceleration pulse generator is a short tube gun and a simulated projectile; the projectile acceleration measuring instrument is a full light velocity interferometer; the soft elastomer recycling device is a multi-section type mixing recycling cabin.
The inner diameter of the short pipe gun is 125mm or 100mm, and the short pipe gun comprises a closed gas accelerating section and an exhaust accelerating section; the pipe cavity of the closed gas accelerating section is sealed, the length is 10cm, the pipe wall of the exhaust accelerating section is provided with a pressure relief hole, the length is 3m, and the purpose of the preset exhaust hole is to exhaust high-pressure gas generated by gunpowder combustion, reduce the acceleration amplitude of the falling edge of an acceleration pulse, reduce the speed of a projectile when entering a test cabin and reduce the recovery difficulty; the simulated projectile has a warhead with a 120-degree cone angle and is covered with a high-strength fiber material, a plane is arranged at the top of the warhead and used for pasting glass bead primary reflecting sheets, a missile-borne electronic instrument (including a calibrated accelerometer) is arranged in the simulated projectile, and the total mass of the projectile is 4-6 kg.
The projectile acceleration measuring instrument comprises a reflecting mirror which is positioned on the axis of the acceleration measuring section and forms an angle of 45 degrees with the axis, a reflecting sheet which is stuck on the surface of the head of the projectile and an ultra-high speed data acquisition analyzer besides the all-fiber velocity interferometer. The reflector is arranged in the speed measuring cabin through the bracket, light emitted by the laser (in the all-fiber speed interferometer) is deflected by 90 degrees and then enters the reflector at the head of the projectile, and the light returns to the interferometer after passing through the reflector and the reflector to interfere with the emitted light, and the ultra-high speed data acquisition analyzer acquires interference signals and calculates the acceleration of the projectile.
The soft elastomer recovery device comprises a multi-section type mixed speed reduction cabin composed of gas damping, liquid-gas mixed damping, liquid damping, a dispersion damping section and solid damping, wherein the gas damping is air, the liquid damping is water, the dispersion damping is a mixture of fine sand and sawdust, and the solid damping is a composite material composed of rubber and felt according to a layered structure. The gas damping section, the liquid-gas mixing damping section and the liquid damping section are provided with air inlet valves or water inlet valves; the dispersion damping section and the solid damping section are provided with semicircular pipe type hatches, so that the mixture and the composite material can be conveniently filled or the projectile can be conveniently taken out.
After passing through the speed measuring cabin, the projectile sequentially passes through the gas damping section, the liquid-gas mixed damping section, the liquid damping section and the dispersion damping section and finally stays in the solid damping section. The friction damping of the multi-section type hybrid deceleration cabin is sequentially increased from left to right, so that the minimum resistance of the projectile during high-speed invasion is ensured, the damping of the penetration is increased during low-speed penetration, the overload value of the missile-borne electronic instrument in the whole deceleration process is not more than 30000g, and the overload is recorded in a full range by the missile-borne acceleration tester arranged in the projectile. In the gas damping section, the density of the gas is changed by changing the pressure of the gas in the gas damping section, so that the friction resistance of the projectile in the section is changed; in the liquid-gas mixing damping section, the friction resistance of the projectile in the section can be changed by adjusting the density of cavitation water so as to adapt to the recovery of the projectiles with different firing speeds.
According to the wide pulse high g value acceleration simulation test system, the technical characteristics are as follows:
(1) The wide-pulse high-g-value acceleration simulation test system is formed by pushing a projectile by high-pressure gas generated by rapid combustion of a deflagration propellant (such as a pistol propellant) to generate acceleration signals with the amplitude of 20000-150000 g and the pulse width of 1-5 ms.
(2) For a projectile of mass 4kg, a maximum amplitude acceleration pulse of 150000g, 1ms, may be generated, where the velocity of the projectile is 1000m/s; for a projectile of mass 6kg, a maximum pulse width acceleration pulse of 20000g, 5ms could be generated, at which time the velocity of the projectile is 600m/s.
(3) The system can generate excitation acceleration pulses with different pulse widths of 20000g, 60000g, 100000g and 150000g respectively so as to adapt to traceability calibration of the high-g-value acceleration sensor.
The high-g-value impact acceleration simulation test method is characterized in that a wide-pulse high-g-value acceleration simulation test system is adopted, excitation acceleration pulse signals with the amplitude of 20000-150000 g and the pulse width of 1-5 ms are generated by changing the type and the dosage of the propellant powder in the short-tube gun, and the acceleration signals are measured by using a full-light-ray velocity interferometer, a cooperative target reflector, a reflecting mirror and an ultra-high-speed data acquisition analyzer, so that the wide-pulse high-g-value acceleration simulation test method is formed.
The device is characterized in that the wide pulse high g value acceleration pulse generator is a short tube gun and a simulated projectile; the projectile acceleration measuring instrument is a full light velocity interferometer; the soft elastomer recycling device is a multi-section type mixing recycling cabin.
The application method of the wide pulse high g value acceleration simulation test method is technically characterized in that: the application method of the wide pulse high g value acceleration simulation test method comprises the following steps:
a. the traceability calibration of the high-g-value acceleration sensor under the wide pulse is realized by adopting a wide pulse high-g-value acceleration simulation test system;
b. the survival study of the missile-borne electronic instrument (arranged in a projectile instrument cabin) under the high-g-value impact environment is realized by adopting a wide-pulse high-g-value acceleration simulation test system.
The invention has the following advantages:
1. by changing the type and the dosage of the propellant powder, the test system can generate excitation acceleration pulses with different amplitude values and different pulse widths;
2. by varying the density of the cavitation water, the present test system is enabled to recover projectiles of different firing rates.
3. The invention adopts gases with different air pressures, namely different densities to replace the segmented foam water of the low-density section, and can monitor the air pressure by only one barometer, thereby having simple structure and convenient operation.
Drawings
FIG. 1 is a schematic diagram of a wide pulse high g value acceleration simulation test system;
FIG. 2 is a schematic view of a simulated projectile 6;
FIG. 3 is a schematic diagram of a configuration of a missile-borne acceleration tester;
in the drawings, 1 a firing mechanism, 2 a bore reinforcement, 3 a propellant charge, 4 a closed gas acceleration stage, 5 a missile-borne electronic instrument, 6 a simulated projectile, 7 a primary reflector, 8 an interference light path, 9 a pressure relief hole, 10 an exhaust acceleration stage, 11 a super high speed data acquisition analyzer, 12 a speed measurement cabin, 13 a reflector, 14 an all fiber speed interferometer, 15 a reflector bracket, 16 an air inlet valve A,17 a gas damping stage, 18 an air inlet valve B,19 a water inlet valve B,20 a liquid-gas mixing damping stage, 21 a water inlet valve A,22 a liquid damping stage, 23 a dispersion damping stage, 24 a solid damping stage, 25 a spring buffer, 26 a tail screw cap, 27 a projectile body, 28 a projectile body cabin, 29 a projectile head, 30 a shell, 31 a storage recording circuit, 32 a buffer member, 33 a high g value accelerometer.
Detailed Description
Non-limiting examples of the invention are as follows:
examples: wide pulse high g value acceleration test system and method and application of test method
The embodiment is three parts, namely a wide pulse high g value acceleration test system; secondly, a wide pulse high g value acceleration simulation test method; thirdly, an application method of the wide pulse high g value acceleration test method.
1. Wide pulse high g value acceleration simulation test system
FIG. 1 shows a wide pulse high g value acceleration test system, comprising: high g value acceleration pulse generator, projectile acceleration measuring instrument and projectile soft recovery device.
The high-g-value acceleration pulse generator pushes the projectile by high-pressure gas generated by quick combustion of explosive propellant powder in a short pipe gun, generates acceleration signals with the amplitude of 20000-150000 g and the pulse width of 1-5 ms, forms a wide-pulse high-g-value acceleration simulation test system, and can realize micro damage recovery of the projectile.
The inner diameter of the short pipe gun adopted in the embodiment is 125mm, and the short pipe gun consists of a closed gas accelerating section 4 and an exhaust accelerating section 10; the lumen of the closed gas accelerating section 4 is sealed, and the length is 10cm; the length of the exhaust accelerating section 10 is 3m, the pipe wall of the exhaust accelerating section 10 is provided with a pressure relief hole 9 for discharging high-pressure gas generated by gunpowder combustion, reducing the acceleration amplitude of the falling edge of the acceleration pulse and reducing the speed of the simulated projectile 6 when entering the acceleration test cabin 12.
The inside of the closed gas accelerating section 4 is provided with a propellant powder 3 and a simulated projectile 6, a missile-borne electronic instrument 5 is arranged in the simulated projectile 6, and the head of the simulated projectile 6 is stuck with an original reflection sheet 7.
An acceleration test cabin 12 is provided in front of the exhaust acceleration section 10. A reflecting mirror 13 is arranged in the lumen of the speed measuring cabin 12, and the reflecting mirror 13 is arranged on the axis of the speed measuring cabin 12 through a bracket 15 and forms an angle of 45 degrees with the axis.
The projectile acceleration measuring instrument adopted in the example comprises an all-fiber speed interferometer 14, an ultra-high-speed data acquisition analyzer 11, a reflecting mirror 13 which is positioned on the axis of an acceleration test cabin and forms an angle of 45 degrees with the axis, a primary reflecting sheet 7 adhered to the surface of the head of the projectile, and the ultra-high-speed data acquisition analyzer 11.
As shown in fig. 2, in the simulated projectile 6 adopted in this example, the warhead 29 is 120 ° cone angle and covered with high-strength fiber material, the top of the warhead is provided with a plane for adhering the glass bead primary reflecting sheet 7, the instrument cabin of the projectile 6 is internally provided with a missile-borne electronic instrument 5, a calibrated high g value accelerometer 33 is arranged in the instrument cabin, and the total mass of the projectile is 4-6 kg.
As shown in fig. 3, the missile-borne electronic apparatus 5 includes a missile-borne acceleration tester, a penetration bullet fuze, and inertial navigation combinations on various types of bullets.
When the sensor is calibrated, the invention only uses the missile-borne acceleration tester for providing comparison signals.
The missile-borne acceleration tester comprises a tester shell 30, a storage recording unit 31, a buffer member 32 and a high-g-value accelerometer 33. The inner cavity of the missile-borne acceleration tester is provided with a storage recording unit 31, a buffer member 32 and a high-g value accelerometer 33.
The storage recording unit 31 comprises an analog adapting circuit, an analog-to-digital conversion circuit, a storage circuit and a logic control circuit, the signals of the high-g-value accelerometer 33 are sent to the analog adapting circuit and then to the analog-to-digital conversion circuit, the signals are digitized and stored in the storage circuit, and the working time sequence of the whole system is coordinated by the logic control circuit.
The cushioning member 32 employed in this example is a high g value acceleration cushioning device disclosed in chinese patent No. 202010078769.0.
The projectile acceleration measuring instrument is positioned outside the projectile and utilizes the laser interference principle; the missile-borne acceleration tester is arranged inside the projectile.
And comparing the measurement result of the projectile acceleration measuring instrument with the measurement result of the missile-borne acceleration measuring instrument to form calibration.
Light emitted by a laser arranged in the all-fiber speed interferometer 14 is deflected by 90 degrees through a reflector and then enters the primary reflecting sheet 7 of the projectile head, returns to the interferometer after passing through the reflecting sheet 7 and the reflector 13, interferes with the emitted light, and the ultra-high speed data acquisition analyzer 11 acquires interference signals.
The elastomer soft recovery device adopted in the embodiment comprises a multi-section type mixed speed reduction cabin consisting of a gas damper 17, a liquid-gas mixed damper 20, a liquid damper 22, a dispersion damper 23 and a solid damper 24; the air inlet valve A16 is used for adjusting the pressure of air in the air damping buffer section, the air inlet valve B18 and the water inlet valve B19 are used for adjusting the density of cavitation water in the liquid-air mixing damping buffer section, and the water inlet valve A21 is used for filling the liquid damping buffer section 22 with water.
2. Wide pulse high g value acceleration simulation test method
The specific scheme of the wide pulse high g value acceleration simulation test method of this example is shown by combining fig. 1, 2 and 3. Fig. 1 shows a specific structure of a wide-pulse high-g-value acceleration test system used for implementing the wide-pulse high-g-value acceleration simulation test method, and fig. 2 and 3 show specific structures of a simulated projectile and a missile-borne acceleration tester used for implementing the wide-pulse high-g-value acceleration simulation test method, respectively.
The simulation test method for the wide pulse high g value acceleration comprises the following steps: the wide-pulse high-g-value acceleration simulation test system is adopted, the type and the dosage of the propellant powder 3 are changed through operating a short gun of the system to generate acceleration signals with the amplitude of 20000-150000 g and the pulse width of 1-5 ms, and the acceleration pulse signals are measured by using a full-light velocity interferometer 14, a cooperative target primary reflecting sheet 7, a reflecting mirror 13 and an ultra-high-speed data acquisition analyzer 11 to form the wide-pulse high-g-value acceleration simulation test method.
The simulation test system adopted by the test method of the wide pulse high g value acceleration simulation test in the example comprises a projectile acceleration measuring instrument, the speed obtained by simulating the projectile 6 is measured through an all-fiber speed interferometer 14, and the acceleration signal of the projectile can be obtained by differentiating the speed signal. By changing the type and the dosage of the propellant powder in the short tube gun, an excitation acceleration signal with the amplitude of 150000g, the pulse width of 1ms or the amplitude of 20000g and the pulse width of 5ms can be obtained for a simulated projectile with the mass of 4-6 kg. If the gun propellant is adopted as the propellant 3, the amplitude of the generated acceleration pulse can reach 150000g, and the pulse width is larger than 1ms.
3. Application method of wide pulse high g value acceleration simulation test method
The application method of the wide pulse high g value acceleration simulation test method of this example is specifically shown in fig. 1, 2 and 3 in combination. Fig. 1 shows a specific structure of a wide-pulse high-g-value acceleration test system used for implementing the wide-pulse high-g-value acceleration simulation test method, and fig. 2 and 3 show specific structures of a simulated projectile and a missile-borne acceleration tester used for implementing the wide-pulse high-g-value acceleration simulation test method, respectively.
The application method of this example is specifically as follows:
(1) The traceability calibration of the high-g-value accelerometer under the wide pulse is realized by adopting a wide pulse high-g-value acceleration simulation test system, namely, an original reflection sheet 7 is stuck to the head of a simulated projectile 6, an acceleration signal of the projectile 6 in the launching process is measured by adopting a full-light-ray velocity interferometer 11 and a reflection mirror 13 arranged in an acceleration measuring cabin, meanwhile, an output signal of a calibrated accelerometer 33 arranged in a projectile instrument cabin 28 is recorded by adopting a missile-borne acceleration tester of a missile-borne electronic instrument 5, and the two acceleration signals are compared, so that the traceability calibration of the high-g-value accelerometer 33 under the wide pulse is realized.
The measuring ranges of the high-g-value accelerometer 33 are 20000g, 60000g and 100000g respectively, and the high-g-value accelerometer comprises most of high-g-value acceleration sensors at home and abroad at present.
(2) The reliability research under the high-g-value impact environment of the missile-borne electronic instrument is realized by adopting a wide-pulse high-g-value acceleration simulation test system, namely, a projectile provided with the checked missile-borne electronic instrument 5 is accelerated to the acceleration with preset amplitude and pulse width, the acceleration signal is recorded by adopting a full-light velocity interferometer 11, the projectile 6 is recovered by an projectile body soft recovery device, the missile-borne electronic instrument is taken out, and whether the function of a detector is normal is checked, so that the reliability of the electronic instrument under the preset acceleration condition is determined.
The missile-borne electronic instrument is mainly a hard target penetration fuse, particularly a penetration fuse of an aircraft carrier or a tank armor, can load a high g value environment up to 150000g, and can basically meet the examination requirement in the penetration fuse application environment.
Claims (2)
1. A wide pulse high g value acceleration simulation test system, comprising: the high-g-value acceleration pulse generator comprises a short tube gun and a simulated projectile, and the high-g-value acceleration pulse generator generates high-pressure gas to push the projectile by quick combustion of deflagration propellant powder in the short tube gun to generate excitation acceleration signals with the amplitude of 20000-150000 g and the pulse width of 1-5 ms; the short pipe gun comprises a closed gas accelerating section and an exhaust accelerating section; the pipe cavity of the closed gas accelerating section is airtight, and the pipe wall of the exhaust accelerating section is provided with a pressure relief hole; the simulated projectile is internally provided with a missile-borne electronic instrument, the warhead of the simulated projectile is 120-degree cone angle, and the top of the warhead is provided with a plane which is used for pasting the glass bead original reflection sheet; the projectile acceleration measuring instrument comprises a full light velocity interferometer, a reflecting mirror which is positioned on the axis of the acceleration measuring section and forms an angle of 45 degrees with the axis, and a reflecting sheet which is stuck on the surface of the head of the projectile; sticking an original reflection sheet on the head of the projectile, measuring acceleration signals of the projectile in the launching process by adopting a full-light velocity interferometer and by means of a reflector arranged in an acceleration measuring cabin, simultaneously recording output signals of a calibrated accelerometer arranged in the projectile by adopting a missile-borne electronic instrument, and comparing the two acceleration signals to realize traceability calibration of the accelerometer with high g value under wide pulse; the elastomer soft recovery device is a multi-section type mixing recovery cabin; the multistage type mixed recovery cabin sequentially comprises a gas damping section, a liquid-gas mixed damping section, a liquid damping section, a dispersion damping section and a solid damping section, after passing through the speed measuring cabin, a projectile sequentially passes through the gas damping section, the liquid-gas mixed damping section, the liquid damping section and the dispersion damping section and finally stays in the solid damping section, the friction damping of the multistage type mixed recovery cabin is sequentially increased from left to right, the minimum resistance of the projectile during high-speed invasion is ensured, the damping during low-speed running is increased, the overload value of the missile-borne electronic instrument in the whole deceleration process is not more than 30000g, the overload is recorded in a whole range by a projectile acceleration tester arranged in the projectile, and the density of the gas is changed by changing the pressure of the gas in the gas damping section, so that the friction resistance of the projectile in the section is changed; in the liquid-gas mixing damping section, the friction resistance of the projectile in the section is changed by adjusting the density of cavitation water so as to adapt to the recovery of the projectiles with different firing speeds.
2. The wide-pulse high-g-value acceleration simulation test system according to claim 1, wherein: reliability research applied to high g value impact environment of missile-borne electronic instrument: the projectile provided with the calibrated missile-borne electronic instrument is accelerated to the acceleration with preset amplitude and pulse width, the acceleration signal is recorded by adopting a full light velocity interferometer, the projectile is recovered by the projectile soft recovery device, the missile-borne electronic instrument is taken out, and whether the function of the missile-borne electronic instrument is normal or not is checked, so that the reliability of the missile-borne electronic instrument under the preset acceleration condition is determined.
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| CN114396838B (en) * | 2021-12-09 | 2022-08-30 | 北京理工大学 | High-energy impact loading test and testing device and method for large-mass test piece |
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