CN110132836B - Multi-impact loading test device and method - Google Patents
Multi-impact loading test device and method Download PDFInfo
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- CN110132836B CN110132836B CN201910506011.XA CN201910506011A CN110132836B CN 110132836 B CN110132836 B CN 110132836B CN 201910506011 A CN201910506011 A CN 201910506011A CN 110132836 B CN110132836 B CN 110132836B
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Abstract
The application discloses many times striking loading test device and method, the rationale is that utilize the electromagnetism principle once to accelerate a plurality of shots, utilize time, the parameter variation course curve of sensor record shot striking explosive, the controller is according to measured data calculation control parameter, inhale the bottom through placing the pellet of accomplishing the striking task in proper order at the electro-magnet of target plate bottom, avoid the mutual interference that the shot kick-backed and caused, realize striking loading many times. The method has the advantages of strong universality, low cost and convenience in replacement of easily-damaged parts, can fill the blank of a device and a method for testing explosive impact ignition for many times in the penetration process, and can provide technical support for the development of penetration type anti-overload explosives.
Description
Technical Field
The application belongs to the technical field of explosive performance parameter experiments, and relates to a repeated impact loading test device and method, which are mainly used for researching the impact safety of explosives and can provide technical support for the development of overload-resistant explosives.
Background
The anti-overload explosive is a high-mechanical-property explosive designed for penetration-type ammunition, such as 155mm caliber shell charge, deep penetration missile and the like, and research shows that the stress on the explosive charge in the ammunition penetration process is usually not more than 1GPa, the value is far from reaching the impact detonation threshold value (about 7GPa) of the explosive, so that the ignition in the process of penetration of the explosive is generally classified into a non-impact ignition mechanism, the non-impact ignition mechanism of the explosive in the process of penetration is closely related to the motion state of the explosive in the process of penetration, and the numerical simulation result shows that for the condition of deep penetration, the explosive moves back and forth for multiple times in the shell, therefore, the non-impact ignition of the explosive can be the final result caused by repeated stimulation for many times, researchers mainly simulate the stress state of the explosive in the penetration process by using a drop hammer loading mode at present, and an explosive loading and launching safety simulation loading experimental method is established by using the license peaks based on a large drop hammer device; ginger Chinesbo et al tried to study the damage characteristics of explosives under multiple impact loads by using a double-diaphragm test, but limited by the test method, the existing test method has the following two defects:
(1) the large drop hammer can not simulate the condition of multiple times of loading, and only the equivalent simulation is carried out on the state of single loading, so that the existing test method can not meet the research requirement, and the technical blank exists;
(2) the double-diaphragm test is difficult to realize multiple times of non-impact loading, and is not suitable for researching the condition that the stress is lower than 1 GPa.
The overload-resistant explosive is a kind of explosive which is largely equipped in China, the overload-resistant safety is one of core indexes of the overload-resistant explosive, and currently, China has no test device and method which can carry out multiple non-impact loading, and can not accurately simulate the actual stress condition in the explosive penetration process, so that the research process of the overload-resistant explosive is hindered, and therefore, a multiple impact loading test device and method are urgently needed, and the domestic blank is filled.
Disclosure of Invention
Aiming at the defects or shortcomings of the existing testing device and method, the application provides a repeated impact loading testing device and method, which has the basic principle that a plurality of bullets are accelerated once by utilizing the electromagnetic principle, the bullets completing the impact task are sucked into the bottom in sequence through the electromagnets arranged at the bottom of the target plate, the mutual interference caused by the rebound of the bullets is avoided, and repeated impact loading is realized. The method has the advantages of strong universality, low cost and convenience in replacement of easily-damaged parts, can fill the blank of a method without a test device for non-impact ignition of explosives in the penetration process, and can provide technical support for the development of penetration type overload-resistant explosives.
In order to achieve the above object, the following technical solutions are adopted in the present application: the utility model provides a multiple impact loading test device which characterized in that: the device comprises a guide rail negative electrode 1, an armature A2, a shot A3, an armature B4, a shot B5, a guide rail positive electrode 6, a laser velocimeter 7, an electromagnet 8, a barrier net 9, a strain gauge 10, a sample 11, a base 12, a sensor A13, a sensor B14, a sensor C15, a data line 16 and a controller 17, wherein the guide rail negative electrode 1 and the guide rail positive electrode 6 are made of conductive metal, the length of the guide rail negative electrode 1 and the length of the guide rail positive electrode 6 are 6-10 times of the distance between the guide rail negative electrode 1 and the guide rail positive electrode 6, so that the shot A3 and the shot B5 can obtain the optimal outlet speed, the shapes and the materials of the shot A3 and the shot B5 can be freely set according to research needs, the armature A2, the shot A3, the armature B4, the shot B5, the laser velocimeter 7, the electromagnet 8, the strain gauge 10 and the sample 11 are sequentially arranged on the same horizontal plane, the armature A2 and the armature B4 are made of concave metal, the armature A2 and the guide rail positive electrode 4 are positioned between the guide rail positive electrode 1 and the guide rail positive electrode 4, the armature A2 and the armature B4 are arranged in a front-back manner, the armature A2 and the armature B4 are in free contact with the guide rail cathode 1 and the guide rail anode 6, the projectile A3 is bonded on the outer surface of the armature A2 parallel to the cross section of the guide rail cathode 1, the projectile B5 is bonded on the outer surface of the armature B4 parallel to the cross section of the guide rail cathode 1, the laser velocimeter 7 is composed of a transmitting end and a receiving end, the transmitting end and the receiving end of the laser velocimeter 7 are respectively fixed at the tail ends of the guide rail cathode 1 and the guide rail anode 6, the electromagnet 8 and the barrier net 9 are fixed under the laser velocimeter 7, the barrier net 9 is made of nylon and used for recovering the projectiles, the barrier net 9 is positioned above the electromagnet 8, the distance between the barrier net 9 and the electromagnet 8 is equal to the distance between the guide rail cathode 1 and the guide rail anode 6, and the base 12 is fixed, the base 12 is of a reinforced concrete structure, two end faces of the base 12 perpendicular to the moving direction of the shot B5 are respectively provided with a groove, three through holes are distributed at equal intervals along the cross section between the two grooves of the base 12, the sensor A13, the sensor B14 and the sensor C15 are respectively installed on the three through holes, the sensitive surfaces of the sensor A13, the sensor B14 and the sensor C15 are tightly attached to the sample 11, the type of the sensor can be freely set according to research requirements, the groove on one side, close to the shot B5, of the base 12 is integrally of a cylindrical boss structure, the groove on one side, close to the shot B5, of the base 12 is filled with the sample 11, the strain gauge 10 is attached to the center position of the free surface of the sample 11, the strain gauge 10 is located on the central axis of the shot A3, the armature B and the shot B5, one end of the data line 16 is connected with the strain gauge 10, the sensor A13 and the sensor B15, A sensor B14 and a sensor C15, wherein the other end of the data line 16 is connected with the controller 17;
the method for measuring by using the device comprises the following steps:
step one, controlling the ambient temperature to be not more than 30 ℃ and the relative air humidity to be not more than 50%;
step two, sequentially placing the armature A2, the shot A3, the armature B4 and the shot B5 in place, filling the concave pit of the base 12 with the sample 11, and waiting for the electromagnet 8 to prepare;
and step three, switching on a strong pulse power supply, wherein pulse current flows out of the guide rail cathode 1 to return to the pulse power supply cathode through the guide rail anode 6, the armature A2 and the armature B4, and the formula F is 0.5L*I2Calculating thrust, where F is the thrust experienced by armature A2 and armature B4, L*The electric induction gradient is adopted, the current intensity is I, the armature A2 and the armature B4 are accelerated under the action of thrust, and meanwhile, the armature A2 and the armature B4 respectively drive the projectile A3 and the projectile B5 to sequentially accelerate;
step four, recording the initial time t when the sensor A13, the sensor B14 and the sensor C15 receive the signalsa、tb、tcThe starting time t of the electromagnet 8 is max (t)a,tb,tc) The electromagnet 8 accurately controls the switching time, the shot B5 which arrives and finishes impact firstly is quickly sucked into the bottom of the base 12 in the rebounding stage, the shot A3 and the shot B5 impact the sample 11 in sequence, and multiple impact tests without interference of a plurality of shots are realized.
Compared with the prior art, the invention has the following advantages:
(1) multiple times of non-interference loading on the sample is realized in one test;
(2) the simulation of the stress of the explosive in the non-impact ignition process in the explosive penetration process is realized, and the domestic blank is filled.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
FIG. 1 is a cross-sectional view of the test apparatus, 1-negative rail, 2-armature A, 3-projectile A, 4-armature B, 5-projectile B, 6-positive rail, 7-laser velocimeter, 8-electromagnet, 9-barrier, 10-strain gage, 11-sample, 12-base, 13-sensor A, 14-sensor B, 15-sensor C, 16-data line, and 17-controller.
Detailed Description
The invention will be further described in detail with reference to the following drawings and examples, which are not intended to limit the invention:
example 1
In the embodiment, a multi-impact loading test device is designed to perform two impact ignition tests on explosive B, wherein the impact interval time of two projectiles is 200ms, and the impact speed of the projectiles is 100 m/s.
The utility model provides a multiple impact loading test device which characterized in that: the device comprises a guide rail negative electrode 1, an armature A2, a shot A3, an armature B4, a shot B5, a guide rail positive electrode 6, a laser velocimeter 7, an electromagnet 8, a barrier net 9, a strain gauge 10, a sample 11, a base 12, a temperature sensor A13, a pressure sensor B14, a particle velocity sensor C15, a data line 16 and a controller 17, wherein the guide rail negative electrode 1 and the guide rail positive electrode 6 are made of conductive metal, the guide rail negative electrode 1 and the guide rail positive electrode 6 are 6-10 times as long as the distance between the guide rail negative electrode 1 and the guide rail positive electrode 6, so that the shot A3 and the shot B5 can obtain the optimal discharge speed, the shot A3 and the shot B5 are cylinders made of industrial pure iron, the armature A7378, the shot A3, the armature B4, the shot B5, the laser velocimeter 7, the electromagnet 8, the strain gauge 10 and the sample 11 are sequentially arranged on the same horizontal plane, the armature A2 and the armature B4 are made of concave metal, and the armature 4 are positioned between the guide rail positive electrode 1 and the armature B386, the armature A2 and the armature B4 are arranged in a front-back manner, the armature A2 and the armature B4 are in free contact with the guide rail cathode 1 and the guide rail anode 6, the projectile A3 is bonded on the outer surface of the armature A2 parallel to the cross section of the guide rail cathode 1, the projectile B5 is bonded on the outer surface of the armature B4 parallel to the cross section of the guide rail cathode 1, the laser velocimeter 7 is composed of a transmitting end and a receiving end, the transmitting end and the receiving end of the laser velocimeter 7 are respectively fixed at the tail ends of the guide rail cathode 1 and the guide rail anode 6, the electromagnet 8 and the barrier net 9 are fixed under the laser velocimeter 7, the barrier net 9 is made of nylon and used for recovering the projectiles, the barrier net 9 is positioned above the electromagnet 8, the distance between the barrier net 9 and the electromagnet 8 is equal to the distance between the guide rail cathode 1 and the guide rail anode 6, and the base 12 is fixed, the base 12 is of a reinforced concrete structure, two end faces of the base 12 perpendicular to the moving direction of the shot B5 are respectively provided with a groove, three through holes are distributed at equal intervals along the cross section between the two grooves of the base 12, the sensor A13, the sensor B14 and the sensor C15 are respectively installed on the three through holes, the sensitive faces of the sensor A13, the sensor B14 and the sensor C15 are tightly attached to the sample 11, the groove on one side, close to the shot B5, of the base 12 is integrally of a cylindrical boss structure, the sample 11 is filled in the groove on one side, close to the shot B5, of the base 12, the maximum thickness of the sample 11 is 0.55m, the strain gauge 10 is adhered to the center position of the free surface of the sample 11, the strain gauge 10 is located on the central axis of the shot A3, the armature B and the shot B5, one end of the data line 16 is connected with the strain gauge 10, the temperature sensor A13, the pressure sensor B14, the sample B3878, the data line 16 and the shot B5, A particle velocity sensor C15, the other end of the data line 16 is connected to the controller 17;
the method for measuring by using the device comprises the following steps:
step one, controlling the ambient temperature to be not more than 30 ℃ and the relative air humidity to be not more than 50%;
step two, sequentially placing the armature A2, the shot A3, the armature B4 and the shot B5 in place, filling the concave pit of the base 12 with the sample 11, and waiting for the electromagnet 8 to prepare;
and step three, switching on a strong pulse power supply, wherein pulse current flows out of the guide rail cathode 1 to return to the pulse power supply cathode through the guide rail anode 6, the armature A2 and the armature B4, and the formula F is 0.5L*I2Calculating thrust, where F is the thrust experienced by armature A2 and armature B4, L*The electric induction gradient is adopted, the current intensity is I, the armature A2 and the armature B4 are accelerated under the action of thrust, and meanwhile, the armature A2 and the armature B4 respectively drive the projectile A3 and the projectile B5 to sequentially accelerate;
step four, recording the initial time t when the temperature sensor A13, the pressure sensor B14 and the particle velocity sensor C15 receive the signalsa、tb、tcThe starting time t of the electromagnet 8 is max (t)a,tb,tc)＝tb1.2ms, the electromagnet 8 precisely controls the switching time, the shot B5 which arrives at first and finishes the impact is quickly sucked into the bottom of the base 12 at the rebounding stage, the shot A3 and the shot B5 sequentially impact the sample 11, and multiple impact tests without interference of a plurality of shots are realized.
Example 2
In the embodiment, a multi-impact loading test device is designed to perform two impact ignition tests on passivated RDX explosives, wherein the impact interval time of two shots is 10ms, and the impact speed of the shots is 180 m/s.
The utility model provides a multiple impact loading test device which characterized in that: the device comprises a guide rail negative electrode 1, an armature A2, a shot A3, an armature B4, a shot B5, a guide rail positive electrode 6, a laser velocimeter 7, an electromagnet 8, a barrier net 9, a strain gauge 10, a test sample 11, a base 12, a pressure sensor A13, a pressure sensor B14, a pressure sensor C15, a data line 16 and a controller 17, wherein the guide rail negative electrode 1 and the guide rail positive electrode 6 are made of conductive metal, the length of the guide rail negative electrode 1 and the length of the guide rail positive electrode 6 are 6-10 times of the distance between the guide rail negative electrode 1 and the guide rail positive electrode 6, so that the shot A3 and the shot B5 can obtain the optimal outlet speed, the shot A3 and the shot B5 are made of steel material cylinders, the armature A2, the shot A3, the armature B4, the shot B5, the laser velocimeter 7, the electromagnet 8, the strain gauge 10 and the test sample 11 are arranged in sequence on the same horizontal plane, the armature A2 and the armature B4 are made of concave conductive metal, the armature A2 and the guide rail positive electrode 4 are positioned between the guide rail positive electrode 6 and the guide rail positive electrode 6, the armature A2 and the armature B4 are arranged in a front-back manner, the armature A2 and the armature B4 are in free contact with the guide rail cathode 1 and the guide rail anode 6, the projectile A3 is bonded on the outer surface of the armature A2 parallel to the cross section of the guide rail cathode 1, the projectile B5 is bonded on the outer surface of the armature B4 parallel to the cross section of the guide rail cathode 1, the laser velocimeter 7 is composed of a transmitting end and a receiving end, the transmitting end and the receiving end of the laser velocimeter 7 are respectively fixed at the tail ends of the guide rail cathode 1 and the guide rail anode 6, the electromagnet 8 and the barrier net 9 are fixed under the laser velocimeter 7, the barrier net 9 is made of nylon and used for recovering the projectiles, the barrier net 9 is positioned above the electromagnet 8, the distance between the barrier net 9 and the electromagnet 8 is equal to the distance between the guide rail cathode 1 and the guide rail anode 6, and the base 12 is fixed, the base 12 is of a reinforced concrete structure, two end faces of the base 12 perpendicular to the moving direction of the shot B5 are respectively provided with a groove, three through holes are distributed between the two grooves of the base 12 at equal intervals along the cross section, the sensor A13, the sensor B14 and the sensor C15 are respectively installed on the three through holes, the sensitive faces of the sensor A13, the sensor B14 and the sensor C15 are tightly attached to the sample 11, the type of the sensor can be freely set according to research requirements, the groove on one side, close to the shot B5, of the base 12 is integrally of a cylindrical boss structure, the groove on one side, close to the shot B5, of the base 12 is filled with the sample 11, the maximum thickness of the sample 11 is 0.42m, the strain gauge 10 is attached to the center position of the free surface of the sample 11, the strain gauge 10 is located on the central axis of the shot A3, the armature B and the shot B5, one end of the data line 16 is connected with the strain gauge 10, the shot B3878, A pressure sensor A13, a pressure sensor B14 and a pressure sensor C15, wherein the other end of the data line 16 is connected with the controller 17;
the method for measuring by using the device comprises the following steps:
step one, controlling the ambient temperature to be not more than 30 ℃ and the relative air humidity to be not more than 50%;
step two, sequentially placing the armature A2, the shot A3, the armature B4 and the shot B5 in place, filling the concave pit of the base 12 with the sample 11, and waiting for the electromagnet 8 to prepare;
and step three, switching on a strong pulse power supply, wherein pulse current flows out of the guide rail cathode 1 to return to the pulse power supply cathode through the guide rail anode 6, the armature A2 and the armature B4, and the formula F is 0.5L*I2Calculate thrust, where F is the thrust experienced by armature A2 and armature B4, L*The electric induction gradient is adopted, the current intensity is I, the armature A2 and the armature B4 are accelerated under the action of thrust, and meanwhile, the armature A2 and the armature B4 respectively drive the projectile A3 and the projectile B5 to sequentially accelerate;
step four, recording the initial time t when the pressure sensor A13, the pressure sensor B14 and the pressure sensor C15 receive the signalsa、tb、tcStarting time t of electromagnet 8max(ta,tb,tc)＝tbThe electromagnet 8 accurately controls the switching time, the shot B5 which arrives at first and finishes the impact is quickly sucked into the bottom of the base 12 in the rebounding stage, the shot A3 and the shot B5 impact the sample 11 in sequence, and multiple impact tests without interference of a plurality of shots are realized.
Claims (1)
1. A multiple impact loading test device is characterized in that: the device comprises a guide rail negative electrode (1), an armature A (2), a shot A (3), an armature B (4), a shot B (5), a guide rail positive electrode (6), a laser velocimeter (7), an electromagnet (8), a blocking net (9), a strain gauge (10), a sample (11), a base (12), a sensor A (13), a sensor B (14), a sensor C (15), a data line (16) and a controller (17), wherein the guide rail negative electrode (1) and the guide rail positive electrode (6) are made of conductive metal, the lengths of the guide rail negative electrode (1) and the guide rail positive electrode (6) are 6-10 times of the distance between the guide rail negative electrode and the guide rail positive electrode, the armature A (2), the shot A (3), the armature B (4), the shot B (5), the laser velocimeter (7), the electromagnet (8), the strain gauge (10) and the sample (11) are sequentially arranged on the same horizontal plane, and the armature A (2) and the armature B (4) are made of concave conductive metal, the armature A (2) and the armature B (4) are positioned between the guide rail negative electrode (1) and the guide rail positive electrode (6), the armature A (2) and the armature B (4) are arranged in front and back, the armature A (2) and the armature B (4) are freely contacted with the guide rail negative electrode (1) and the guide rail positive electrode (6), the shot A (3) is adhered to the outer surface of the armature A (2) parallel to the cross section of the guide rail negative electrode (1), the shot B (5) is adhered to the outer surface of the armature B (4) parallel to the cross section of the guide rail negative electrode (1), the laser velocimeter (7) is composed of a transmitting end and a receiving end, the transmitting end and the receiving end of the laser velocimeter (7) are respectively fixed at the tail ends of the guide rail negative electrode (1) and the guide rail positive electrode (6), the electromagnet (8) and the barrier net (9) are fixed under the laser velocimeter (7), the blocking net (9) is made of nylon, the blocking net (9) is located above the electromagnet (8), the distance between the blocking net (9) and the electromagnet (8) is equal to the distance between the guide rail cathode (1) and the guide rail anode (6), the base (12) is fixed on the ground, the base (12) is of a reinforced concrete structure, two end faces, perpendicular to the moving direction of the projectile B (5), of the base (12) are respectively provided with a groove, three through holes are distributed between the two grooves of the base (12) at equal intervals along the cross section, the sensor A (13), the sensor B (14) and the sensor C (15) are respectively installed on the three through holes, the sensitive surfaces of the sensor A (13), the sensor B (14) and the sensor C (15) are tightly attached to the sample (11), and the grooves on one side, close to the projectile B (5), of the base (12) are integrally of a cylindrical boss structure, the test sample (11) is filled in a groove on one side, close to the shot B (5), of the base (12), the strain gauge (10) is pasted at the center of the free surface of the test sample (11), the strain gauge (10) is located on the central axis of the shot A (3), the armature B and the shot B (5), one end of the data line (16) is connected with the strain gauge (10), the sensor A (13), the sensor B (14) and the sensor C (15), and the other end of the data line (16) is connected with the controller (17);
the method for measuring by using the device comprises the following steps:
step one, controlling the ambient temperature to be not more than 30 ℃ and the relative air humidity to be not more than 50%;
step two, sequentially arranging the armature A (2), the shot A (3), the armature B (4) and the shot B (5) in place, filling the concave pit of the base (12) with a sample (11), and waiting for preparation of the electromagnet (8);
step three, switching on a strong pulse power supply, wherein pulse current flows out of a guide rail cathode (1) and returns to a pulse power supply cathode through a guide rail anode (6), an armature A (2) and an armature B (4), and the formula F is 0.5L*I2Calculating thrust, where F is the thrust experienced by armature A (2) and armature B (4), and L*The electric induction gradient is adopted, I is the current intensity, the armature A (2) and the armature B (4) are accelerated under the action of thrust, and simultaneously the armature A (2) and the armature B (4) respectively drive the projectile A (3) and the projectile B (5) to sequentially accelerate;
step four, recording the initial time t of the sensors A (13), B (14) and C (15) for receiving signalsa、tb、tcThe starting time t of the electromagnet (8) is equal to max (t)a,tb,tc) The electromagnet (8) accurately controls the switching time, the shot B (5) which arrives at first and finishes the impact is quickly sucked into the bottom of the base (12) in the rebounding stage, and the shot A (3) and the shot B (5) are sequentially impactedAnd (3) hitting the test sample (11) to realize multiple impact tests of a plurality of bullets without interference.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101694446A (en) * | 2009-10-14 | 2010-04-14 | 上海大学 | Device used for impact test of steel ball at high speed |
| CN102297754A (en) * | 2011-05-20 | 2011-12-28 | 重庆大学 | Test apparatus for fatigue of spring under continuous impact of high pressure gas |
| CN103712764A (en) * | 2013-11-29 | 2014-04-09 | 上海卫星装备研究所 | Electromagnetic hammer |
| KR20150025753A (en) * | 2013-08-30 | 2015-03-11 | 주식회사 리얼게인 | A remote controllerable impact test apparatus and a impact test system including the same |
| CN106772083A (en) * | 2016-12-26 | 2017-05-31 | 吉林大学 | A kind of automobile-used flat impact experiment apparatus of lithium ion battery high speed water |
| CN206795597U (en) * | 2017-04-24 | 2017-12-26 | 重庆钢铁(集团)有限责任公司 | A kind of steel plate height measuring device |
-
2019
- 2019-06-12 CN CN201910506011.XA patent/CN110132836B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101694446A (en) * | 2009-10-14 | 2010-04-14 | 上海大学 | Device used for impact test of steel ball at high speed |
| CN102297754A (en) * | 2011-05-20 | 2011-12-28 | 重庆大学 | Test apparatus for fatigue of spring under continuous impact of high pressure gas |
| KR20150025753A (en) * | 2013-08-30 | 2015-03-11 | 주식회사 리얼게인 | A remote controllerable impact test apparatus and a impact test system including the same |
| CN103712764A (en) * | 2013-11-29 | 2014-04-09 | 上海卫星装备研究所 | Electromagnetic hammer |
| CN106772083A (en) * | 2016-12-26 | 2017-05-31 | 吉林大学 | A kind of automobile-used flat impact experiment apparatus of lithium ion battery high speed water |
| CN206795597U (en) * | 2017-04-24 | 2017-12-26 | 重庆钢铁(集团)有限责任公司 | A kind of steel plate height measuring device |
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