CN108458823A - A kind of test system for testing positive pressure of shock wave decaying under low-temp low-pressure environment - Google Patents
A kind of test system for testing positive pressure of shock wave decaying under low-temp low-pressure environment Download PDFInfo
- Publication number
- CN108458823A CN108458823A CN201810172666.3A CN201810172666A CN108458823A CN 108458823 A CN108458823 A CN 108458823A CN 201810172666 A CN201810172666 A CN 201810172666A CN 108458823 A CN108458823 A CN 108458823A
- Authority
- CN
- China
- Prior art keywords
- shock wave
- pressure
- temperature
- test
- cabin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- 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
- G01L5/14—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring the force of explosions; for measuring the energy of projectiles
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention provides a kind of for testing the test system that positive pressure of shock wave is decayed under low-temp low-pressure environment, include nacelle with preset temperature and preset pressure, be installed on the shock wave of the nacelle end module occurs, the shock wave conversion module that module is connected occurs with the shock wave, and the test module that shock wave pressure changes is tested along the operational process of the nacelle length direction in shock wave；Promising its is set in nacelle and tests the temperature and pressure regulating mechanism that inner cavity provides preset temperature and preset pressure.The test system can adjust test temperature and test pressure in nacelle as needed, so that shock wave test can be tested under the temperature and pressure of setting, the temperature and pressure environment that operating mode therewith is provided and is matched can be tested for shock wave attenuation, to improve the result accuracy and accuracy of shock wave attenuation experiment.
Description
Technical field
The present invention relates to shock wave attenuation rule technical field of measurement and test, more particularly, to one kind for testing low-temp low-pressure ring
The test system that positive pressure of shock wave is decayed under border.
Background technology
Explosion time, surrounding medium are directly acted on by the explosion product of high temperature and pressure explosive in air, on contact circle
Detonation product at face is spread with high speed to surrounding, strong compression surrounding medium, the pressure density temperature in medium
There are phase step type raising, formation initial shock wave and constantly outside propagation, wherein shock wave wave surface pressure value and is undisturbed medium
The difference of initial pressure value be defined as the peak overpressure of shock wave, during shock wave is propagated outward, with away from the quick-fried heart
The increase of distance, peak overpressure are constantly decayed.Shock wave injures member as a kind of typical case, and peak overpressure is commonly used in weighing apparatus
The power of stroke wave and then quantitative analysis are to the situation of injuring of target, therefore the attenuation law of clear positive pressure of shock wave is for end
Point effect analysis is of great significance.It can be seen that the attenuation law of its superpressure and week from the generation of shock wave and propagation law
Initial pressure density and the temperature etc. for enclosing medium are closely related.Currently, semiempirical meter of the shock wave overpressure peak with range attenuation
Formula, such as Henrych formula, Backer formula are calculated, mainly for the data result under the experimental condition of standard atmospheric pressure point
Analysis obtains, it is difficult to be applied to the decaying for calculating shock wave overpressure peak under low-temp low-pressure environment.When ammunition is in high aerial explosion time,
The shock wave generated in air will be propagated under environment under low-temp low-pressure, and propagation law it is not immediately clear, therefore carry out
The test of positive pressure of shock wave attenuation law is very necessary under low-temp low-pressure environment.
Therefore it provides a kind of positive pressure of shock wave die-away test tests system, to be carried for the test of shock wave attenuation rule
For the temperature and pressure environment that operating mode therewith matches, to improve the result accuracy and accuracy of shock wave attenuation experiment,
Just become those skilled in the art's urgent problem to be solved.
Invention content
The object of the present invention is to provide a kind of for testing the experimental test that positive pressure of shock wave is decayed under low-temp low-pressure environment
System, to provide the temperature and pressure environment that operating mode therewith matches for the test of shock wave attenuation rule, to improve punching
Hit the result accuracy and accuracy of wave attenuation experiment.
In order to solve the above technical problem, the present invention provides one kind to decline for testing positive pressure of shock wave under low-temp low-pressure environment
The test system subtracted includes nacelle with preset temperature and preset pressure, is installed on the shock wave of the nacelle end
Module occurs, the shock wave conversion module that module is connected occurs with the shock wave, and in shock wave along the nacelle length
The test module of shock wave pressure variation is tested in the operational process in direction；Promising its is set in nacelle, inner cavity offer is provided
The temperature and pressure regulating mechanism of preset temperature and preset pressure.
Before on-test, by temperature and pressure regulating mechanism by test inner cavity in temperature and pressure adjust to Conditions Matching
Required temperature and pressure, will then utilize shock wave that module occurs and generate super shock wave, detonation difference can be used as desired
The explosive of equivalent carries out shock wave generation, the shock loading generated for obtaining explosion；The shock wave that explosion generates enters impact
The unique one-dimensional plane wave of directional velocity is converted into after wave conversion module, then one-dimensional shock wave enters nacelle, and through shock wave
Superpressure test module tests peak overpressure of the shock wave wave surface by the test point, obtains shock wave wave surface and is passing through each survey
The attenuation law of peak overpressure when pilot provides to obtain pressure change and attenuation law for the attenuation analysis in later stage
Data supporting, to reach test purpose.
Optionally, the nacelle along the shock wave directional velocity successively include load chamber, test the speed cabin and buffering cabin, institute
State load chamber, the cabin of testing the speed is connected with the buffering cabin；
Module occurs for the shock wave and the shock wave conversion module is installed on the front end of the load chamber successively, described
Test module is installed on the cabin of testing the speed.
Optionally, the load chamber and the stitching portion in the cabin of testing the speed, the stitching portion in the test the speed cabin and the buffering cabin
It is mounted on sealing ring.
Optionally, the cabin of testing the speed includes the multiple secondary cabins being arranged in series, and each secondary cabin is connected, and described in adjacent two
It is provided with sealing ring between secondary cabin.
Optionally, the nacelle includes outer wall, inner layer wall and the interlayer cavity being folded between two layers of walls；The temperature and pressure
Regulating mechanism include adjust the first regulating mechanism of the interlayer cavity temperature and pressure, and adjust the experiment inner cavity temperature with
Second regulating mechanism of pressure.
Optionally, first regulating mechanism includes the first intake valve of the connection interlayer cavity and cryogen source, connects
Lead to the interlayer cavity and vacuum pump or the first air outlet valve of air, and monitors the interlayer cavity inner temperature and pressure in real time
The first temperature and pressure detection meter.
Optionally, second regulating mechanism includes the second intake valve of the connection experiment inner cavity and cryogen source, connects
The logical experiment inner cavity and vacuum pump or the second air outlet valve of air, and intracavitary temperature and pressure in the experiment is monitored in real time
The second temperature and pressure detection meter.
Optionally, it includes the bracket of explosive occurring for placing shock wave, and cover at institute that module, which occurs, for the shock wave
State the sealed shell of tank of bracket periphery.
Optionally, test module is at least three free fields being set in turn in along shock velocity direction in the nacelle
Superpressure tests sensor.
Optionally, the ultrasonic wave conversion module is the plane for the shock wave outlet that module occurs with the shock wave
Wave producer.
Description of the drawings
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, in being described below
Attached drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not making the creative labor
It puts, other drawings may also be obtained based on these drawings.
Fig. 1 is that the test system that positive pressure of shock wave is decayed under low-temp low-pressure environment provided by the present invention is a kind of specific
The structural schematic diagram of embodiment.
Reference sign：
1- nacelles
11- tests inner cavity 12- outer wall 13- inner layer wall 14- interlayer cavitys
101- load chambers
102- tests the speed cabin
103- buffers cabin
2- sealing rings
31- the first intake valve 32- the first air outlet valve the first temperature and pressure of 33- detection meter
41- the second intake valve 42- the second air outlet valve the second temperature and pressure of 43- detection meter
51- bracket 52- sealed shell of tank
6- free field superpressures test sensor
7- plane wave generators
8- holders
Specific implementation mode
Technical scheme of the present invention is clearly and completely described below in conjunction with attached drawing, it is clear that described implementation
Example is a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill
The every other embodiment that personnel are obtained without making creative work, shall fall within the protection scope of the present invention.
Referring to FIG. 1, Fig. 1 is the experimental test system that positive pressure of shock wave is decayed under low-temp low-pressure environment provided by the present invention
The structural schematic diagram of unified kind of specific implementation mode.
In a specific embodiment, the experiment that positive pressure of shock wave is decayed under low-temp low-pressure environment provided by the invention is surveyed
Test system includes the nacelle 1 with preset temperature and preset pressure, be installed on the nacelle end shock wave occur module, with
The shock wave conversion module that module is connected occurs for the shock wave, and in shock wave along the operation of the nacelle length direction
The test module of shock wave pressure variation is tested in journey；Be arranged in the nacelle it is promising its test inner cavity 11 provide preset temperature and
The temperature and pressure regulating mechanism of preset pressure.
Before on-test, by temperature and pressure regulating mechanism by test inner cavity in temperature and pressure adjust to Conditions Matching
Required temperature and pressure, then will utilize shock wave occur module generate shock wave, can as desired use detonation difference work as
The explosive of amount carries out shock wave generation, the shock loading generated for obtaining explosion；The shock wave that explosion generates enters shock wave
The unique one-dimensional plane wave of directional velocity is converted into after conversion module, then one-dimensional shock wave enters nacelle 1, and super through shock wave
It presses test module to test peak overpressure of the shock wave wave surface by the test point, obtains shock wave wave surface and passing through each test
The attenuation law of peak overpressure when point provides number to obtain velocity variations and attenuation law for the attenuation analysis in later stage
According to support, to reach test purpose.
Specifically, it includes the bracket 51 of explosive occurring for placing ultrasound, and cover at institute that module, which occurs, for above-mentioned shock wave
State the sealed shell of tank 52 of bracket periphery；Wherein, sealed shell of tank 52 ensures that explosion safety, bracket 51 are used for building confined space
In placement support explosive.
Above-mentioned test module is to be set in turn at least three free fields in the nacelle along shock velocity direction to surpass
Pressure test sensor 6；It is by sensing station and bent using sensor detection current pressure when shock wave is moved along nacelle
Line.
The direction dispersion for the shock wave that explosion generates, in order to which shock wave is converted to the single wave in direction, enables its movement side
To always along the length direction of nacelle, above-mentioned ultrasonic wave conversion module is the ultrasonic wave outlet that module occurs with the shock wave
The plane wave generator of connection.
The test system can adjust test temperature and test pressure in nacelle 1 as needed so that shock wave tests energy
It is enough to be tested under the temperature and pressure of setting, can be punching compared with the existing equipment that can only be tested at normal atmospheric pressure
It hits wave attenuation test and the temperature and pressure environment that operating mode matches therewith is provided, to improve the result of shock wave attenuation experiment
Accuracy and accuracy.
Specifically, above-mentioned nacelle 1 along it is described experiment fragmentation directional velocity successively include load chamber 101, test the speed 102 and of cabin
Cabin 103 is buffered, the load chamber 101, the cabin 102 of testing the speed are connected with the buffering cabin 103；Wherein, the shock wave
Module occurs and the shock wave conversion module is installed on the front end of the load chamber successively, the test module is installed on described
It tests the speed cabin.Each function cabin is split structure, installs and builds convenient for additional structure, can be with if certain part is damaged
It replaces respectively, repair and maintenance cost are relatively low.
It, can be in institute in order to avoid gas leakage occurs between adjacent nacelle 1 since experiment needs to carry out under pressurize environment
State load chamber 101 and the cabin 102 of testing the speed stitching portion, it is described test the speed cabin 102 and it is described buffering cabin 103 stitching portion be respectively mounted
There is sealing ring 2.
According to the needs of test distance, the cabin 102 of testing the speed may include the multiple secondary cabins being arranged in series, each secondary cabin phase
Connection, and it is provided with sealing ring 2 between the adjacent two secondary cabin.In this way, being individually present between each pair cabin, in each pair cabin respectively
Free field superpressure is installed by holder 8 and tests sensor 6, the secondary cabin number in cabin 102 of testing the speed can be increased or decreased according to actual demand
The use scope of system is tested in amount, expanding test, and the quantity by increasing secondary cabin makes test system can be applied to compared with high initial speed
The velocity attenuation of shock wave is tested.
The above-mentioned form that can select double wall, i.e. nacelle 1 include outer wall 12, inner layer wall 13 and be folded in two layers of walls it
Between interlayer cavity 14；At this point, the temperature and pressure regulating mechanism includes adjusting the first of 14 temperature and pressure of interlayer cavity to adjust
Mechanism is saved, and adjusts the second regulating mechanism of experiment 11 temperature and pressure of inner cavity；In this way, the second regulating mechanism Adjustment Tests
The temperature and pressure of inner cavity 11, the first regulating mechanism adjust the temperature and pressure of interlayer cavity 14, to pass through interlayer cavity 14
Setting realize heat preservation and pressurize, for test inner cavity 11 temperature and pressure value preserving protection is provided, further improve experiment essence
Degree and accuracy.
Specifically, first regulating mechanism includes the first intake valve of the connection interlayer cavity 14 and cryogen source
31, it is connected to the interlayer cavity 14 and vacuum pump or the first air outlet valve 32 of air, and monitors the interlayer cavity 14 in real time
The first temperature and pressure detection meter 33 of interior temperature and pressure.After the completion of test system is built, first by 31 He of the first intake valve
First air outlet valve 32 opens simultaneously, and the gaseous refrigerant in cryogen source enters interlayer cavity 14 through the first intake valve 31, and with
After air in cavity carries out heat exchange, it is discharged through the first air outlet valve 32, at the same time, 33 monitoring in real time of the first temperature and pressure detection meter
Temperature and pressure in interlayer cavity 14 waits for that 14 inside of interlayer cavity is thoroughly cooled to prediction numerical value, closes the first air outlet valve 32
With the first intake valve 31, the heat preservation operation of test system is completed.Above-mentioned cryogen source can be compressed nitrogen tank, make at this time
Cryogen is nitrogen.
Above-mentioned second regulating mechanism include the connection experiment inner cavity 11 with the second intake valve 41 of cryogen source, be connected to institute
Experiment inner cavity 11 and vacuum pump or the second air outlet valve 42 of air are stated, and monitors temperature and pressure in the experiment inner cavity 11 in real time
The second temperature and pressure detection meter 43 of power.It is initial in experiment, the second air outlet valve 42 is first turned on, will be tested by the second intake valve 41
Inner cavity 11 is connected with cryogen source, and filling refrigerant (such as nitrogen) at the same time passes through second into experiment inner cavity 11
Temperature change is closed until being thoroughly cooled to prediction numerical value in experiment inner cavity 11 in 43 monitoring test inner cavities 11 of temperature and pressure detection meter
Second air outlet valve 42 and the second intake valve 41 complete the cooling operation inside sealed compartment.Then, the second air outlet valve 42 is connected to
Vacuum pump prepares to extract gas in sealed compartment, opens vacuum pump, and meter 43 monitoring test inner cavity, 11 internal pressure is detected by the second temperature and pressure
Power and temperature change extract gas in cabin until default value, closes the second air outlet valve 42, and the decompression completed in sealed compartment is grasped
Make.
It should be understood that the i.e. detectable temperature that above-mentioned temperature and pressure detection meter can be integrated form can detect pressure simultaneously again
Device, or seperated pressure gauge and thermometer.
In conclusion module occurs for shock wave provided by the present invention can use the explosive for the different equivalents that detonate as desired
Shock wave generation is carried out, the shock loading generated for obtaining explosion includes mainly two parts：For building confined air
Between, ensure the sealed shell of tank of explosion safety, and the bracket for explosive.Shock wave conversion module provided by the present invention
Shock wave for generating explosion is converted into one-dimensional plane wave, includes mainly following two parts：For realizing one-dimensional impact
The plane wave generator 7 of wave conversion, and for creating environment under low pressure and keeping the double-layer seal cabin of temperature in cabin.Institute of the present invention
The positive pressure of shock wave test module of offer obtains shock wave for testing peak overpressure of the shock wave wave surface by the test point
The attenuation law of wave surface peak overpressure when by each test point.It include mainly part following six：Free field peak overpressure
Test system, for testing peak overpressure of the shock wave wave surface by test point；Double-layer seal cabin, for creating low-voltage ring
Border is additionally operable to keep temperature in cabin；Outer layer heat-insulation system, by intake valve to double-layer seal cabin interlayer filling nitrogen, while according to
Interlayer internal temperature and pressure are adjusted by air outlet valve according to monitoring result, are sealed compartment to dynamic regulation interlayer internal temperature
Internal environment is kept the temperature；External temperature and pressure display unit establish two objects for monitoring interlayer internal temperature and pressure condition
The Real-time Feedback of reason amount combines actual demand to adjust the numerical value of two physical quantitys accordingly；Internal temperature and control pressurer system, are used for
Sealed compartment internal pressure and temperature are adjusted, environmental pressure and temperature that test needs are obtained；Internal temperature and pressure display unit are used
In monitoring sealed compartment internal temperature and pressure condition, pressure and temperature in real-time adjusting cabin accordingly.
Below taking above-mentioned embodiment as an example, build process and the experiment of test system provided by the present invention are sketched
Process.
Build process：
First, shock wave generating system is set up, which occurs module, explosive and detonator by shock wave and form.When installation,
Bracket is installed in sealed shell of tank first, completes building for shock wave generating system；Then by plane wave generator and load
Cabin is fixed together, and completes building for shock wave converting system, and the system is linked together with sealed shell of tank.
Seal washer is installed between load chamber and cabin of testing the speed, and is fixed by bolt at two sealed compartment otic placodes to be connected to
Together.Then, the method for several cabins of testing the speed being sequentially connected by the above method, and being connected using cabin of testing the speed, will buffer cabin
It is installed to cabin end of testing the speed, completes the installation of test system main body.Finally, free field superpressure test sensor is installed to
On holder, and it is connected to oscillograph.
Then positive pressure of shock wave attenuation test system is built, starts free field superpressure and tests sensor, carry out examination triggering, adjust
It tries free field superpressure and tests sensor, complete building for positive pressure of shock wave test system.
Experiment process：
Before on-test, the first intake valve 31 is connect with compressed nitrogen gas tank first and opens the first air outlet valve 32, then
The filling nitrogen into the interlayer cavity 14 of test chamber, and the temperature inside interlayer cavity 14 is monitored by the first temperature and pressure force detector
And pressure changing, until the inside of interlayer cavity 14 is thoroughly cooled to default value, close the first air outlet valve 32 and first into
Air valve 31 completes the heat preservation operation of test system.
When on-test, the second air outlet valve 42 is first turned on, and the second intake valve 41 is connected to compressed nitrogen gas tank, to examination
11 inside filling nitrogen of inner cavity, and the temperature change of the experiment inner cavity 11 by the 43 monitoring sealing of the second temperature and pressure detection meter are tested, directly
It is thoroughly cooled to default value in experiment inner cavity 11, closes the second air outlet valve 42 and the second intake valve 41, to complete in experiment
The cooling of chamber 11 operates.Then, the second air outlet valve 42 is connected to vacuum pump, prepares to extract the gas in experiment inner cavity 11, opens
Vacuum pump is opened, the pressure and temperature change in 43 monitoring test inner cavities 11 of meter is detected by the second temperature and pressure, extracts experiment inner cavity 11
Interior gas is until preset pressure numerical value, closes the second air outlet valve 42, the reduced pressure operation in completion experiment inner cavity 11.
Explosive and detonator are installed on the bracket in sealed shell of tank, it is to be triggered to ensure that free field superpressure test sensor is in
State, and monitor pressure and temperature variations in sealed compartment and tested when in ideal numberical range.After the test,
According to the oscillogram of each sensor acquisition, shock wave overpressure peak at each measuring point is read, shock wave under the environmental condition is obtained
Peak overpressure with distance attenuation law.
Pressure and temperature in sealed compartment are adjusted, we can obtain varying environment condition, to test varying environment temperature
And the positive pressure of shock wave attenuation law under pressure condition.During experiment, the second regulating mechanism can detect in sealed compartment in real time
Portion's pressure and temperature variations, to ensure that environmental condition is in by adjusting the opening and closing of the second air outlet valve and the second intake valve
Desired quantity.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art within the scope of the invention can be to above-mentioned
Embodiment is changed, changes, replacing and modification.
Claims (10)
1. a kind of for testing the test system that positive pressure of shock wave is decayed under low-temp low-pressure environment, which is characterized in that including
Nacelle with preset temperature and preset pressure, the shock wave for being installed on the nacelle end occur module, with the shock wave
The shock wave conversion module that module is connected occurs, and punching is tested along the operational process of the nacelle length direction in shock wave
The test module of pressure of hammer wave variation；Promising its is set in nacelle and tests the temperature that inner cavity provides preset temperature and preset pressure
Press regulating mechanism.
2. it is according to claim 1 for testing the test system that positive pressure of shock wave is decayed under low-temp low-pressure environment,
It is characterized in that, the nacelle along the shock wave directional velocity successively include load chamber, test the speed cabin and buffering cabin, it is described plus
Carry cabin, the cabin of testing the speed is connected with the buffering cabin；
Module occurs for the shock wave and the shock wave conversion module is installed on the front end of the load chamber, the test successively
Module is installed on the cabin of testing the speed.
3. it is according to claim 2 for testing the test system that positive pressure of shock wave is decayed under low-temp low-pressure environment,
It is characterized in that, the load chamber and stitching portion, the stitching portion for testing the speed cabin and the buffering cabin in the cabin of testing the speed are pacified
Equipped with sealing ring.
4. it is according to claim 3 for testing the test system that positive pressure of shock wave is decayed under low-temp low-pressure environment,
It is characterized in that, the cabin of testing the speed includes the multiple secondary cabins being arranged in series, each secondary cabin is connected, and the adjacent two secondary cabin
Between be provided with sealing ring.
5. being used to test the experiment that positive pressure of shock wave is decayed under low-temp low-pressure environment according to claim 1-4 any one of them to survey
Test system, which is characterized in that the nacelle includes outer wall, inner layer wall and the interlayer cavity being folded between two layers of walls；It is described
Temperature and pressure regulating mechanism includes adjusting the first regulating mechanism of the interlayer cavity temperature and pressure, and adjust experiment inner cavity temperature
Second regulating mechanism of degree and pressure.
6. it is according to claim 5 for testing the test system that positive pressure of shock wave is decayed under low-temp low-pressure environment,
It is characterized in that, first regulating mechanism include the connection interlayer cavity with the first intake valve of cryogen source, be connected to institute
The first air outlet valve of interlayer cavity and vacuum pump or air is stated, and monitors the of the interlayer cavity inner temperature and pressure in real time
One temperature and pressure detection meter.
7. it is according to claim 6 for testing the test system that positive pressure of shock wave is decayed under low-temp low-pressure environment,
It is characterized in that, second regulating mechanism include the connection experiment inner cavity with the second intake valve of cryogen source, be connected to institute
The second air outlet valve of experiment inner cavity and vacuum pump or air is stated, and monitors the of intracavitary temperature and pressure in the experiment in real time
Two temperature and pressure detection meter.
8. being used to test the experiment that positive pressure of shock wave is decayed under low-temp low-pressure environment according to claim 1-4 any one of them to survey
Test system, which is characterized in that it includes the bracket of explosive occurring for placing shock wave, and cover at that module, which occurs, for the shock wave
The sealed shell of tank of the bracket periphery.
9. being used to test the experiment that positive pressure of shock wave is decayed under low-temp low-pressure environment according to claim 1-4 any one of them to survey
Test system, which is characterized in that test module be along shock velocity direction be set in turn in the nacelle at least three from
Sensor is tested by field superpressure.
10. being used to test the experiment that positive pressure of shock wave is decayed under low-temp low-pressure environment according to claim 1-4 any one of them
Test system, which is characterized in that the shock wave conversion module is the ultrasonic wave outlet that module occurs with the shock wave
Plane wave generator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810172666.3A CN108458823B (en) | 2018-03-01 | 2018-03-01 | Test system for testing overpressure attenuation of shock wave in low-temperature and low-pressure environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810172666.3A CN108458823B (en) | 2018-03-01 | 2018-03-01 | Test system for testing overpressure attenuation of shock wave in low-temperature and low-pressure environment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108458823A true CN108458823A (en) | 2018-08-28 |
| CN108458823B CN108458823B (en) | 2020-08-04 |
Family
ID=63219705
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810172666.3A Active CN108458823B (en) | 2018-03-01 | 2018-03-01 | Test system for testing overpressure attenuation of shock wave in low-temperature and low-pressure environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108458823B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110057530A (en) * | 2019-05-28 | 2019-07-26 | 中国人民解放军军事科学院国防工程研究院工程防护研究所 | A kind of assembled orifice structure incident blast surge test cabin |
| CN113063920A (en) * | 2021-03-18 | 2021-07-02 | 北京理工大学 | Small-size variable-cross-section rectangular detonation tube with wave rectifier and optical observation window |
| CN114184096A (en) * | 2021-04-28 | 2022-03-15 | 北京理工大学 | Test device and method for testing fragment speed attenuation rule in complex environment |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19741888C1 (en) * | 1997-09-23 | 1999-06-17 | Bundesrep Deutschland | Method of determining the impact pressure |
| CN104634578A (en) * | 2015-03-09 | 2015-05-20 | 北京动力机械研究所 | Total environment high-altitude test system and total environment high-altitude test method for aviation turbocharged internal combustion engine |
| 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 |
| CN107271635A (en) * | 2017-06-30 | 2017-10-20 | 中国石油天然气股份有限公司西部管道分公司 | A kind of method of testing of the three-dimensional Overpressure Field of open space large scale flammable vapor cloud explosion |
| CN206862215U (en) * | 2017-05-22 | 2018-01-09 | 中国工程物理研究院流体物理研究所 | A kind of general purpose type high accuracy planar impact wave producer |
-
2018
- 2018-03-01 CN CN201810172666.3A patent/CN108458823B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19741888C1 (en) * | 1997-09-23 | 1999-06-17 | Bundesrep Deutschland | Method of determining the impact pressure |
| CN104634578A (en) * | 2015-03-09 | 2015-05-20 | 北京动力机械研究所 | Total environment high-altitude test system and total environment high-altitude test method for aviation turbocharged internal combustion engine |
| 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 |
| CN206862215U (en) * | 2017-05-22 | 2018-01-09 | 中国工程物理研究院流体物理研究所 | A kind of general purpose type high accuracy planar impact wave producer |
| CN107271635A (en) * | 2017-06-30 | 2017-10-20 | 中国石油天然气股份有限公司西部管道分公司 | A kind of method of testing of the three-dimensional Overpressure Field of open space large scale flammable vapor cloud explosion |
Non-Patent Citations (1)
| Title |
|---|
| 张世文，龙建华，贾宏志，金山: "平面冲击波在有机玻璃中的衰减测试及数值模拟", 《兵工学报》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110057530A (en) * | 2019-05-28 | 2019-07-26 | 中国人民解放军军事科学院国防工程研究院工程防护研究所 | A kind of assembled orifice structure incident blast surge test cabin |
| CN110057530B (en) * | 2019-05-28 | 2024-07-23 | 中国人民解放军军事科学院国防工程研究院工程防护研究所 | Assembled orifice structure incident explosion shock wave test cabin |
| CN113063920A (en) * | 2021-03-18 | 2021-07-02 | 北京理工大学 | Small-size variable-cross-section rectangular detonation tube with wave rectifier and optical observation window |
| CN114184096A (en) * | 2021-04-28 | 2022-03-15 | 北京理工大学 | Test device and method for testing fragment speed attenuation rule in complex environment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108458823B (en) | 2020-08-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108458823A (en) | A kind of test system for testing positive pressure of shock wave decaying under low-temp low-pressure environment | |
| US10288058B2 (en) | Method and system for an instrumented piston assembly | |
| US10295433B2 (en) | Device for testing performance of pyro device using high-pressure air | |
| CN101726396A (en) | Device and method for detecting leak rate of O type rubber sealing ring used for spaceflight | |
| CN109991148A (en) | Carbon dioxide blasting impact dynamic monitoring tester and its test method | |
| CN111366263B (en) | High-temperature calibration equipment and method for TDLAS temperature measurement based on shock tube | |
| CN107966259A (en) | The impact of fiber-reinforced composite thin-wall member and hot composite test device | |
| Collen et al. | Commissioning of the t6 stalker tunnel | |
| CN110657966B (en) | Infrared seeker refrigeration test equipment | |
| CN108592714A (en) | A kind of experimental rig for testing Fragment Velocities decaying | |
| CN111896396B (en) | Rock dynamic mechanical property experimental device and experimental method thereof | |
| CN110308246B (en) | Outburst elimination technology for water injection of outburst coal seam and outburst elimination effect test method | |
| CN113124645A (en) | Air separation cooling method adopting wind power | |
| CN111157370A (en) | Vehicle body part low-temperature collision test environment box and test method thereof | |
| CN109855795A (en) | A kind of fission opposite opened high/low temperature experimental provision | |
| CN220018831U (en) | Air pressure control mechanism for leak test of cylinder body | |
| CN208751889U (en) | A kind of gas pressure loads pilot system of controllable temperature | |
| US3362215A (en) | Apparatus for testing seals for propellant actuated devices | |
| CN110095147A (en) | A kind of environmental test system and its working method of Multi-parameter coupling | |
| CN117783206B (en) | Test system and method for evaluating warm-pressing explosive function | |
| Sparr et al. | Adaptation of tactical cryocoolers for short duration space-flight missions | |
| CN116519218A (en) | Air pressure control mechanism for leak test of cylinder body | |
| RU2791575C1 (en) | Spherical device for researching compressibility of gases in the megabar pressure range | |
| CN115561083B (en) | Deep rock mass dynamic performance test system and method | |
| CN216695454U (en) | Air tightness detection device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |