CN108458823B - Test system for testing overpressure attenuation of shock wave in low-temperature and low-pressure environment - Google Patents
Test system for testing overpressure attenuation of shock wave in low-temperature and low-pressure environment Download PDFInfo
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- CN108458823B CN108458823B CN201810172666.3A CN201810172666A CN108458823B CN 108458823 B CN108458823 B CN 108458823B CN 201810172666 A CN201810172666 A CN 201810172666A CN 108458823 B CN108458823 B CN 108458823B
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- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
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Abstract
The invention provides a test system for testing overpressure attenuation of shock waves in a low-temperature and low-pressure environment, which comprises a cabin body with preset temperature and preset pressure, a shock wave generation module arranged at the end part of the cabin body, a shock wave conversion module communicated with the shock wave generation module, and a test module for testing pressure change of the shock waves in the running process of the shock waves along the length direction of the cabin body, wherein the shock wave generation module is used for generating shock waves; the cabin body is provided with a temperature and pressure adjusting mechanism for providing preset temperature and preset pressure for the test inner cavity of the cabin body. The test system can adjust the test temperature and the test pressure in the cabin body as required, so that the shock wave test can be performed at the set temperature and pressure, the temperature and pressure environment matched with the working condition of the shock wave attenuation test can be provided for the shock wave attenuation test, and the accuracy and the precision of the shock wave attenuation test result are improved.
Description
Technical Field
The invention relates to the technical field of shock wave attenuation rule testing, in particular to a test testing system for testing overpressure attenuation of shock waves in a low-temperature and low-pressure environment.
Background
When the explosive explodes in the air, the surrounding medium of the explosive is directly acted by high-temperature and high-pressure explosion products, the explosion products at the contact interface diffuse to the surroundings at a very high speed, the surrounding medium is compressed strongly, the pressure density and the temperature in the medium rise in a step-like manner, initial shock waves are formed and continuously spread outwards, wherein the difference value between the pressure value of the wave front of the shock waves and the initial pressure value of the undisturbed medium is defined as the overpressure peak value of the shock waves, and the overpressure peak value is attenuated continuously along with the increase of the distance from the detonation center in the process of the outward spread of the shock waves. The shock wave is taken as a typical damage element, and the overpressure peak value of the shock wave is usually used for measuring the power of the shock wave so as to quantitatively analyze the damage condition of a target, so that the clear attenuation rule of the overpressure of the shock wave has important significance for analyzing the end point effect. From the generation and propagation law of the shock wave, it can be seen that the attenuation law of the overpressure is closely related to the initial pressure density and temperature of the surrounding medium. At present, semi-empirical calculation formulas of the attenuation of the overpressure peak value of the shock wave along with the distance, such as a Henrych formula, a baker formula and the like, are mainly obtained by analyzing data results under the test condition of standard atmospheric pressure, and are difficult to be applied to the calculation of the attenuation of the overpressure peak value of the shock wave in the low-temperature and low-pressure environment. When ammunition explodes in high altitude, shock waves generated in the air propagate in the environment with low temperature and low pressure, and the propagation rule is not clear at present, so that the test of the overpressure attenuation rule of the shock waves in the environment with low temperature and low pressure is necessary.
Therefore, a shock wave overpressure attenuation test system is provided to provide a temperature and pressure environment matched with the working condition of the shock wave attenuation rule for the test of the shock wave attenuation rule, so that the accuracy and precision of the result of the shock wave attenuation test are improved, and the problem to be solved by the technical staff in the field is solved urgently.
Disclosure of Invention
The invention aims to provide a test system for testing the overpressure attenuation of shock waves in a low-temperature and low-pressure environment, so as to provide a temperature and pressure environment matched with the working condition of the test system for the attenuation rule of the shock waves, thereby improving the accuracy and precision of the result of the shock wave attenuation test.
In order to solve the technical problems, the invention provides a test system for testing overpressure attenuation of shock waves in a low-temperature and low-pressure environment, which comprises a cabin body with preset temperature and preset pressure, a shock wave generation module arranged at the end part of the cabin body, a shock wave conversion module communicated with the shock wave generation module, and a test module for testing pressure change of the shock waves in the running process of the shock waves along the length direction of the cabin body, wherein the shock wave conversion module is used for converting the shock waves into the shock waves; the cabin body is provided with a temperature and pressure adjusting mechanism for providing preset temperature and preset pressure for the test inner cavity of the cabin body.
Before the test is started, the temperature and the pressure in the test inner cavity are adjusted to the required temperature and pressure matched with the working condition through the temperature and pressure adjusting mechanism, then the shock wave generating module is utilized to generate the super shock wave, and explosives with different equivalent weights can be detonated as required to generate the shock wave so as to obtain the shock load generated by explosion; the shock wave generated by explosion enters the shock wave conversion module and is converted into a one-dimensional plane wave with the unique speed direction, then the one-dimensional shock wave enters the cabin body, the overpressure peak value of the shock wave front passing through the test point is tested by the shock wave overpressure testing module, the attenuation rule of the overpressure peak value of the shock wave front passing through each test point is obtained, and therefore the pressure change and the attenuation rule are obtained, data support is provided for later attenuation condition analysis, and the test purpose is achieved.
Optionally, the cabin body sequentially comprises a loading cabin, a speed measuring cabin and a buffer cabin along the speed direction of the shock wave, and the loading cabin, the speed measuring cabin and the buffer cabin are communicated with each other;
the shock wave generation module and the shock wave conversion module are sequentially arranged at the front end of the loading cabin, and the test module is arranged in the speed measuring cabin.
Optionally, sealing rings are mounted at the splicing position of the loading cabin and the speed measuring cabin and the splicing position of the speed measuring cabin and the buffer cabin.
Optionally, the speed measuring cabin comprises a plurality of auxiliary cabins which are arranged in series, each auxiliary cabin is communicated with another auxiliary cabin, and a sealing ring is arranged between every two adjacent auxiliary cabins.
Optionally, the cabin comprises an outer wall, an inner wall and an interlayer cavity sandwiched between the two walls; the temperature and pressure adjusting mechanism comprises a first adjusting mechanism for adjusting the temperature and the pressure of the interlayer cavity and a second adjusting mechanism for adjusting the temperature and the pressure of the test inner cavity.
Optionally, the first adjusting mechanism includes a first air inlet valve communicating the interlayer cavity with a refrigerant source, a first air outlet valve communicating the interlayer cavity with a vacuum pump or atmosphere, and a first temperature and pressure detector monitoring temperature and pressure in the interlayer cavity in real time.
Optionally, the second adjusting mechanism includes a second air inlet valve communicating the test cavity with the refrigerant source, a second air outlet valve communicating the test cavity with the vacuum pump or the atmosphere, and a second temperature and pressure detector monitoring the temperature and pressure in the test cavity in real time.
Optionally, the shock wave generation module comprises a bracket for placing shock wave generation explosive and a sealing tank body covering the periphery of the bracket.
Optionally, the test module is at least three free field overpressure test sensors sequentially arranged in the cabin body along the speed direction of the shock wave.
Optionally, the ultrasonic conversion module is a plane wave generator communicated with the shock wave outlet of the shock wave generation module.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic structural diagram of an embodiment of a test system for shock wave overpressure attenuation in a low-temperature and low-pressure environment according to the present invention.
Description of reference numerals:
1-cabin body
11-experimental inner cavity 12-outer wall 13-inner wall 14-interlayer cavity
101-load chamber
102-speed measuring cabin
103-buffer cabin
2-sealing ring
31-first air inlet valve 32-first air outlet valve 33-first temperature and pressure detector
41-second air inlet valve 42-second air outlet valve 43-second temperature and pressure detector
51-bracket 52-sealed can body
6-free field overpressure test sensor
7-plane wave generator
8-bracket
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, fig. 1 is a schematic structural diagram of an embodiment of a test system for overpressure attenuation of shock waves in a low-temperature and low-pressure environment according to the present invention.
In a specific embodiment, the test system for testing overpressure attenuation of shock waves in a low-temperature and low-pressure environment provided by the invention comprises a cabin body 1 with a preset temperature and a preset pressure, a shock wave generation module arranged at the end part of the cabin body, a shock wave conversion module communicated with the shock wave generation module, and a test module for testing pressure change of the shock waves in the running process of the shock waves along the length direction of the cabin body; the cabin body is provided with a temperature and pressure adjusting mechanism for providing preset temperature and preset pressure for the test inner cavity 11 of the cabin body.
Before the test is started, the temperature and the pressure in the test inner cavity are adjusted to the required temperature and pressure matched with the working condition through the temperature and pressure adjusting mechanism, then the shock wave generating module is utilized to generate shock waves, and explosives with different equivalent weights can be detonated as required to generate the shock waves for obtaining shock loads generated by explosion; the shock wave generated by explosion enters the shock wave conversion module and is converted into a one-dimensional plane wave with the unique speed direction, then the one-dimensional shock wave enters the cabin body 1, the overpressure peak value of the shock wave front passing through the test point is tested by the shock wave overpressure testing module, the attenuation rule of the overpressure peak value of the shock wave front passing through each test point is obtained, and therefore the speed change and the attenuation rule are obtained, data support is provided for later attenuation condition analysis, and the test purpose is achieved.
Specifically, the shock wave generation module comprises a bracket 51 for placing ultrasonic explosive, and a sealing tank 52 covering the periphery of the bracket; wherein, sealed tank 52 is used for constructing airtight space, guarantees explosion safety, and bracket 51 is used for placing the bearing explosive.
The testing modules are at least three free field overpressure testing sensors 6 which are sequentially arranged in the cabin body along the speed direction of the shock wave; when the shock wave moves along the cabin, the shock wave passes through the position of the sensor and detects the current pressure curve by using the sensor.
The direction of the shock wave generated by explosion is dispersed, and in order to convert the shock wave into a wave with a single direction, the motion direction of the shock wave is always along the length direction of the cabin body, and the ultrasonic conversion module is a plane wave generator communicated with an ultrasonic outlet of the shock wave generation module.
This test system can adjust the test temperature and the test pressure in the cabin body 1 as required for the shock wave test can be experimental under the temperature and the pressure of setting for compare with current equipment that can only test under standard atmospheric pressure, can provide the temperature and the pressure environment with it operating mode assorted for the shock wave attenuation test, thereby improved shock wave attenuation experimental result accuracy and accuracy.
Specifically, the cabin body 1 sequentially comprises a loading cabin 101, a speed measuring cabin 102 and a buffer cabin 103 along the speed direction of the test fragment, and the loading cabin 101, the speed measuring cabin 102 and the buffer cabin 103 are communicated with each other; the shock wave generation module and the shock wave conversion module are sequentially installed at the front end of the loading cabin, and the test module is installed in the speed measuring cabin. Each function cabin is split type structure, and the additional structure of being convenient for is installed and is built, if certain part takes place to damage, can also change respectively, and maintenance cost are lower.
Because the test needs to be carried out in a pressure-maintaining environment, in order to avoid gas leakage between adjacent capsule bodies 1, sealing rings 2 can be mounted at the splicing positions of the loading chamber 101 and the speed measuring chamber 102 and the splicing positions of the speed measuring chamber 102 and the buffer chamber 103.
According to the requirement of the test distance, the speed measuring cabin 102 may include a plurality of auxiliary cabins arranged in series, each of the auxiliary cabins is communicated, and a sealing ring 2 is arranged between two adjacent auxiliary cabins. Therefore, the auxiliary cabins independently exist, the free field overpressure test sensors 6 are installed in each auxiliary cabin through the supports 8, the number of the auxiliary cabins of the speed measuring cabin 102 can be increased or decreased according to actual requirements, the application range of the test system is expanded, and the test system can be applied to speed attenuation tests of high initial speed shock waves by increasing the number of the auxiliary cabins.
The double-wall form can be selected, that is, the cabin body 1 comprises an outer wall 12, an inner wall 13 and an interlayer cavity 14 clamped between the two walls; at this time, the temperature and pressure adjusting mechanism comprises a first adjusting mechanism for adjusting the temperature and the pressure of the interlayer cavity 14 and a second adjusting mechanism for adjusting the temperature and the pressure of the test inner cavity 11; like this, the temperature and the pressure of experimental inner chamber 11 of second adjustment mechanism adjustment, the temperature and the pressure of first adjustment mechanism adjustment intermediate layer cavity 14 to realize heat preservation and pressurize through setting up of intermediate layer cavity 14, protect for the temperature and the pressure value of experimental inner chamber 11 and provide the protection, further improved experimental precision and degree of accuracy.
Specifically, the first adjusting mechanism includes a first air inlet valve 31 communicating the interlayer cavity 14 with a refrigerant source, a first air outlet valve 32 communicating the interlayer cavity 14 with a vacuum pump or atmosphere, and a first temperature and pressure detector 33 monitoring the temperature and pressure in the interlayer cavity 14 in real time. After the test system is built, the first air inlet valve 31 and the first air outlet valve 32 are opened at the same time, gaseous refrigerants in a refrigerant source enter the interlayer cavity 14 through the first air inlet valve 31 and exchange heat with air in the cavity and then are discharged through the first air outlet valve 32, meanwhile, the first temperature and pressure detector 33 monitors the temperature and the pressure in the interlayer cavity 14 in real time, when the interior of the interlayer cavity 14 is completely cooled to a predicted value, the first air outlet valve 32 and the first air inlet valve 31 are closed, and the heat preservation operation of the test system is completed. The source of refrigerant may be a compressed nitrogen tank, in which case the refrigerant is nitrogen.
The second adjusting mechanism comprises a second air inlet valve 41 for communicating the test inner cavity 11 with a refrigerant source, a second air outlet valve 42 for communicating the test inner cavity 11 with a vacuum pump or atmosphere, and a second temperature and pressure detector 43 for monitoring the temperature and pressure in the test inner cavity 11 in real time. At the beginning of the test, the second air outlet valve 42 is firstly opened to communicate the test inner cavity 11 with the refrigerant source through the second air inlet valve 41, and the refrigerant (for example, nitrogen gas) is injected into the test inner cavity 11, meanwhile, the temperature change in the test inner cavity 11 is monitored through the second temperature and pressure detector 43 until the temperature in the test inner cavity 11 is completely reduced to a predicted value, the second air outlet valve 42 and the second air inlet valve 41 are closed, and the temperature reduction operation in the sealed cabin is completed. Then, connect second air outlet valve 42 to the vacuum pump, prepare to extract the gas in the sealed cabin, open the vacuum pump, monitor pressure and temperature change in experimental inner chamber 11 through second warm-pressing detector 43, extract the gas in the cabin until the preset numerical value, close second air outlet valve 42, accomplish the depressurization operation in the sealed cabin.
It should be understood that the above-mentioned thermo-pressure detector can be an integrated device capable of detecting both temperature and pressure, and can also be a pressure gauge and a thermometer which are separated.
In summary, the shock wave generation module provided by the present invention can generate shock waves by detonating explosives of different equivalent weights as required, and is used for obtaining shock loads generated by explosion, and the shock wave generation module mainly includes two parts: the explosive tank is used for constructing a sealed space and ensuring the safety of explosion, and the bracket is used for placing explosives. The shock wave conversion module provided by the invention is used for converting shock waves generated by explosion into one-dimensional plane waves, and mainly comprises the following two parts: a plane wave generator 7 for realizing one-dimensional shock wave conversion, and a double-layer sealed cabin for creating a low-pressure environment and maintaining the temperature in the cabin. The shock wave overpressure testing module provided by the invention is used for testing the overpressure peak value of the shock wave front passing through the test point, and obtaining the attenuation rule of the overpressure peak value when the shock wave front passes through each test point. The device mainly comprises the following six parts: the free field overpressure peak value testing system is used for testing an overpressure peak value of the shock wave front passing through the test point; the double-layer sealed cabin is used for creating a low-pressure environment and maintaining the temperature in the cabin; the outer-layer heat preservation system is used for injecting nitrogen into the interlayer of the double-layer sealed cabin through the air inlet valve, and adjusting the internal temperature and pressure of the interlayer through the air outlet valve according to the monitoring result, so that the internal temperature of the interlayer is dynamically adjusted, and heat preservation is performed on the internal environment of the sealed cabin; the external temperature and pressure display is used for monitoring the temperature and pressure conditions in the interlayer, establishing real-time feedback of the two physical quantities and adjusting the numerical values of the two physical quantities according to the actual requirements; the internal temperature and pressure control system is used for adjusting the internal pressure and temperature of the sealed cabin to obtain the environmental pressure and temperature required by the test; and the internal temperature and pressure display is used for monitoring the internal temperature and pressure conditions of the sealed cabin and accordingly adjusting the pressure and temperature in the cabin in real time.
The following briefly describes the construction process and the testing process of the testing system provided by the present invention, taking the above specific embodiment as an example.
The building process comprises the following steps:
firstly, a shock wave generation system is erected, and the system consists of a shock wave generation module, explosive and a detonator. When the shock wave generating system is installed, the bracket is installed in the sealed tank body to complete the construction of the shock wave generating system; and then fixedly connecting the plane wave generator with the loading cabin to complete the construction of the shock wave conversion system, and connecting the system with the sealed tank body.
And a sealing gasket is arranged between the loading cabin and the speed measuring cabin and is fixed by bolts at lug plates of the two sealing cabins so as to be connected together. Then, the plurality of speed measuring cabins are connected in sequence through the method, and the buffer cabin is installed at the tail end of the speed measuring cabin by adopting a method of connecting the speed measuring cabins, so that the installation of the test testing system main body is completed. Finally, a free-field overpressure test sensor was mounted to the bracket and connected to an oscilloscope.
And then, building a shock wave overpressure attenuation test system, starting the free field overpressure test sensor, performing test triggering, debugging the free field overpressure test sensor, and completing building of the shock wave overpressure test system.
The test process comprises the following steps:
before the test starts, the first air inlet valve 31 is connected with the compressed nitrogen tank, the first air outlet valve 32 is opened, then nitrogen is injected into the interlayer cavity 14 of the test cabin, the temperature and pressure change conditions inside the interlayer cavity 14 are monitored through the first temperature and pressure detector until the temperature inside the interlayer cavity 14 is completely reduced to a preset value, the first air outlet valve 32 and the first air inlet valve 31 are closed, and the heat preservation operation of the test system is completed.
When the test starts, firstly, the second air outlet valve 42 is opened, the second air inlet valve 41 is connected to the compressed nitrogen tank, nitrogen is injected into the test inner cavity 11, the temperature change of the sealed test inner cavity 11 is monitored through the second warm-pressure detector 43 until the temperature in the test inner cavity 11 is completely reduced to a preset value, and the second air outlet valve 42 and the second air inlet valve 41 are closed to finish the cooling operation of the test inner cavity 11. Then, connect second air outlet valve 42 to the vacuum pump, prepare to extract the gas in experimental inner chamber 11, open the vacuum pump, monitor pressure and temperature variation in experimental inner chamber 11 through second warm-pressing detection meter 43, extract the gas in experimental inner chamber 11 until presetting pressure value, close second air outlet valve 42, accomplish the step-down operation in experimental inner chamber 11.
And explosive and a detonator are arranged on a bracket in the sealed tank body, so that the free field overpressure test sensor is ensured to be in a state to be triggered, the pressure and temperature change conditions in the sealed cabin are monitored, and a test is carried out when the pressure and temperature change conditions are within an ideal numerical range. After the test is finished, reading the overpressure peak value of the shock wave at each measuring point according to the oscillogram acquired by each sensor, and obtaining the attenuation rule of the overpressure peak value of the shock wave along with the distance under the environmental condition.
The pressure and the temperature in the sealed cabin are adjusted, different environmental conditions can be obtained, and therefore the impact wave overpressure attenuation law under different environmental temperatures and pressure conditions is tested. In the test process, the second adjusting mechanism can detect the internal pressure and temperature change condition of the sealed cabin in real time, so that the environmental conditions are ensured to be in ideal values by adjusting the opening and closing of the second air outlet valve and the second air inlet valve.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (9)
1. A test system for testing overpressure attenuation of shock waves in a low-temperature and low-pressure environment is characterized by comprising a cabin body with preset temperature and preset pressure, a shock wave generation module arranged at the end part of the cabin body, a shock wave conversion module communicated with the shock wave generation module, and a test module for testing pressure change of the shock waves in the running process of the shock waves along the length direction of the cabin body; the cabin body is provided with a temperature and pressure adjusting mechanism for providing preset temperature and preset pressure for a test inner cavity of the cabin body; the cabin body comprises an outer layer wall, an inner layer wall and an interlayer cavity clamped between the two layers of walls; the temperature and pressure adjusting mechanism comprises a first adjusting mechanism for adjusting the temperature and the pressure of the interlayer cavity and a second adjusting mechanism for adjusting the temperature and the pressure of the test inner cavity.
2. The system for testing the overpressure attenuation of shock waves in a low-temperature and low-pressure environment according to claim 1, wherein the cabin body sequentially comprises a loading cabin, a speed measuring cabin and a buffer cabin along the velocity direction of the shock waves, and the loading cabin, the speed measuring cabin and the buffer cabin are communicated with each other;
the shock wave generation module and the shock wave conversion module are sequentially arranged at the front end of the loading cabin, and the test module is arranged in the speed measuring cabin.
3. The system for testing the attenuation of the overpressure of the shock wave in the low-temperature and low-pressure environment as claimed in claim 2, wherein sealing rings are mounted at the joint of the loading cabin and the speed measuring cabin and the joint of the speed measuring cabin and the buffer cabin.
4. A test system for testing attenuation of overpressure of shock wave in low temperature and low pressure environment as claimed in claim 3, wherein said speed measuring chamber includes a plurality of sub-chambers connected in series, each of said sub-chambers is connected to each other, and a sealing ring is disposed between two adjacent sub-chambers.
5. A test system for testing the overpressure attenuation of shock wave in low-temperature and low-pressure environment according to any one of claims 1 to 4, wherein the first adjusting mechanism comprises a first air inlet valve for communicating the interlayer cavity with a refrigerant source, a first air outlet valve for communicating the interlayer cavity with a vacuum pump or the atmosphere, and a first temperature and pressure detector for monitoring the temperature and the pressure in the interlayer cavity in real time.
6. A test system for testing shock wave overpressure attenuation in low temperature and low pressure environment as claimed in claim 5, wherein said second adjusting mechanism includes a second air inlet valve communicating said test cavity with a refrigerant source, a second air outlet valve communicating said test cavity with a vacuum pump or atmosphere, and a second temperature and pressure detector for real time monitoring temperature and pressure in said test cavity.
7. A test system for testing the overpressure attenuation of shock waves in low-temperature and low-pressure environments according to any one of claims 1 to 4, wherein the shock wave generation module comprises a bracket for placing shock wave generation explosive, and a sealing tank body covering the periphery of the bracket.
8. A test system for testing the overpressure attenuation of shock waves in low-temperature and low-pressure environment according to any one of claims 1 to 4, wherein the test modules are at least three free-field overpressure test sensors sequentially arranged in the cabin body along the speed direction of the shock waves.
9. A test system for testing overpressure attenuation of shock waves in low-temperature and low-pressure environment according to any one of claims 1 to 4, wherein the shock wave conversion module is a plane wave generator communicated with an ultrasonic outlet of the shock wave generation module.
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| CN113063920B (en) * | 2021-03-18 | 2022-03-25 | 北京理工大学 | Small-size variable-cross-section rectangular detonation tube with wave rectifier and optical observation window |
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| CN106383142A (en) * | 2016-09-09 | 2017-02-08 | 西安近代化学研究所 | Device for testing explosion and propagation characteristics of explosives |
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