CN112611271A - Cloud detonation capacity measuring method - Google Patents
Cloud detonation capacity measuring method Download PDFInfo
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- CN112611271A CN112611271A CN202011474035.0A CN202011474035A CN112611271A CN 112611271 A CN112611271 A CN 112611271A CN 202011474035 A CN202011474035 A CN 202011474035A CN 112611271 A CN112611271 A CN 112611271A
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Abstract
The application discloses a cloud detonation capability measuring method, which mainly utilizes a testing system composed of a visual cloud detonation tube, a pressure sensor, a temperature sensor, a pressure signal conditioner, a temperature signal conditioner, a data collector, a high-frequency signal line and the like to measure shock wave pressure and explosion temperature during cloud detonation, and can use a high-speed camera to carry out whole-course observation on a cloud detonation process, thereby realizing characterization and evaluation of cloud detonation performance. The method for measuring the cloud detonation capability is suitable for measuring the multi-phase cloud detonation capability, can provide technical support for evaluating the cloud detonation performance of the multi-phase fuel, and has the characteristics of visualization, flexible and convenient operation, low economic cost and the like.
Description
Technical Field
The application belongs to the technical field of cloud detonation performance testing, and relates to a cloud detonation performance measuring method which can be used for gas-liquid phase cloud detonation process observation and parameter measurement.
Background
Fuel Air Explosives (FAE) are a new explosive energy source, and have the characteristics of large damage area, high damage efficiency and the like, so that the fuel air explosives attract general attention and development of countries in the world. The fuel-air explosive is a heterogeneous explosive mixture which is composed of volatile liquid hydrocarbon or solid powder combustible as fuel and oxygen in the air as oxidant, when in use, under the action of primary fuze and center throwing explosive charge explosion, the fuel is thrown into the ambient air, the fuel is rapidly diffused and mixed with the air to form explosive cloud, and then the cloud is detonated by a secondary fuze to realize cloud detonation and generate explosive shock waves, fire balls and the like, thereby achieving the effect of killing a target in a large area.
At present, the detonation performance research of fuel air explosives mostly adopts a cloud detonation tube test or an actual explosive loading and throwing static explosion test without restriction. The cloud detonation tube test has the characteristics of more parameter measurement, low test cost, equipment reusability, capability of performing tests in a laboratory and the like, but generally in order to meet certain detonation pressure requirements, the detonation tube body is designed by steel tube processing, sometimes an organic glass window is designed on the detonation tube body, but in order to ensure the compressive strength of the cloud detonation tube, the area of the organic glass window is very small, the organic glass window can only be used for cloud and mist particle size measurement or explosion temperature measurement, and the cloud and mist detonation transfer process image observation cannot be performed. The actual explosive charging throwing static explosion test is generally carried out in an open explosion test field, and the whole process of fuel throwing, cloud and mist diffusion, cloud and mist detonation and the like can be shot and observed by high-speed photography, but the economic cost of the test is higher, the test workload is large, and the efficiency is lower.
Therefore, the test method is suitable for cloud and fog detonation, has the advantages of multiple parameter measurement, low test cost, simple and convenient operation and capability of overall process visual shooting observation, and can be used for measuring and evaluating the detonation capability of the novel high-energy fuel air explosive.
Disclosure of Invention
In order to overcome the defects and shortcomings of the prior art, the cloud detonation capability measuring method is economical, safe, simple and convenient to operate, reliable in performance and capable of achieving visual observation.
In order to realize the task, the invention adopts the following technical solution:
a cloud detonation capacity measuring method is characterized by comprising the following steps: the method comprises the steps of measuring shock wave pressure and explosion temperature parameters during cloud detonation by using a testing system consisting of a visual cloud detonation tube, a pressure sensor, a temperature sensor, a pressure signal conditioner, a temperature signal conditioner, a data collector, a high-frequency signal wire and the like, and observing the cloud detonation process by using a high-speed camera in the whole process, so as to measure and evaluate the cloud detonation capability, wherein the sensor in the cloud detonation tube is respectively connected with the signal conditioner through the signal wire, and the signal conditioner is connected with the data collector through the signal wire.
The application provides a cloud detonation capability measuring method, which comprises the following steps:
the method comprises the following steps: fixing the temperature sensor and the pressure sensor on the corresponding interface of the detonation tube body through glass cement, ensuring the interface to be sealed firmly, adhering and sealing the interface without the sensor by using a sealing adhesive tape, and then placing the detonation tube body, the tube body bracket and the sensor bracket in an explosion field after the glass cement is cured for 24 hours;
step two: the pressure sensor, the temperature sensor, the signal conditioner and the data acquisition unit are connected through signal wires, and a test system is debugged to ensure that the pressure sensor, the temperature sensor, the signal conditioner and the data acquisition unit work normally;
step three: sticking a small quick-adhesion hook at the top part which is about 10cm away from the initiation port in the tube body of the detonation tube, then installing the detonator and the initiating explosive, firstly, firmly sticking the bottom of the detonator and the end face of the initiating explosive column by using an adhesive tape, then vertically hanging the detonator on the hook in the tube body by using a detonator leg wire, and enabling the initiating explosive column to be positioned at the center of the section of the tube body;
step four: penetrating out a detonator leg wire terminal from a center hole of the detonating end cover, connecting the detonator leg wire terminal with the detonating wire, sealing and fixing the detonating end cover and a center threading hole by using glass cement, and sealing and fixing a tail end cover of the belt plug by using the glass cement;
step five: uniformly adding the fuel to be detected through 4 fuel filling ports at the upper end of the detonation tube body, and then sealing the fuel filling ports by using sealing plugs;
step six: after the fuel to be tested and the air in the detonation tube body are uniformly mixed, starting a data collector, then detonating the detonator, and recording shock wave pressure data and explosion temperature data by the data collector.
According to the method for measuring the cloud and mist detonation capacity, a visual cloud and mist detonation tube in a test system used in the method comprises a detonation tube body, a sealing plug, a detonation end cover, a tail end cover, a tube body support, a pressure sensor support, a temperature sensor and a pressure sensor; wherein:
the detonation tube body is a circular tube body, the two ends of the detonation tube body are open, the length of the tube body is 1000mm, the outer diameter of the tube body is 200-208 mm, the inner diameter of the tube body is 184mm, the wall thickness is 8-12 mm, the material is organic glass, the tube body is provided with 7 pressure sensor interfaces, temperature sensor interfaces and fuel filling ports, the number of the pressure sensor interfaces is 7, the number of the interfaces is circular, the aperture is 21mm, the distance is 100mm, the interfaces are distributed on one side of the detonation tube body and are parallel to the axis of the tube body, the first interface is 200mm away from the front end of the detonation tube body, the number of the temperature sensor interfaces is 2, the interfaces are circular, the aperture is 13mm, the interfaces are distributed on the other side of the detonation tube body and are parallel to the axis of the tube body, the distance is 500mm and 700mm respectively away from the front end of the detonation tube body, the fuel filling ports are 4, the filling ports are circular, the aperture is 10mm, the, the first filling port is 200mm away from the front end of the tube body of the detonation tube;
the sealing plug is a silicon rubber sealing plug and is formed by an upper circular truncated cone and a lower circular truncated cone into a whole, the diameter of the upper circular truncated cone is 15mm, the thickness of the upper circular truncated cone is 10mm, the diameter of the lower circular truncated cone is 11mm, and the thickness of the lower circular truncated cone is 8 mm;
the detonation end cover is a circular disc with a central hole and is formed by an upper circular table and a lower circular table into a whole, the diameter of the upper circular table is 184mm, the thickness of the upper circular table is 10mm, the diameter of the lower circular table is 210mm, the thickness of the lower circular table is 10mm, the diameter of the central hole of the end cover is 2mm, and the material is 2A12 type aluminum;
the tail end cover is a disc with a plug in the center and is formed by an upper part and a lower part into a whole, the diameter of the upper round table is 184mm, the thickness of the upper round table is 10mm, the diameter of the lower round table is 210mm, the thickness of the lower round table is 10mm, an M12 threaded through hole is formed in the center of the end cover, the end cover is made of 2A12 type aluminum, the plug is an M12 screw, the length of the thread is 20mm, and the end cover is made;
the pipe body support is an adjustable lifting support made of steel, the upper end of the pipe body support is an 1/4 arc-shaped plate, the middle of the pipe body support is a cylindrical support rod with threads at one end, and the lower end of the pipe body support is a square support with a nut; the pressure sensor support is an adjustable lifting support made of steel, the upper end of the pressure sensor support is an 1/4 arc-shaped plate, the middle of the pressure sensor support is a cylindrical support rod with threads at one end, and the lower end of the pressure sensor support is a circular support with a nut; the temperature sensor support is an adjustable lifting support made of steel, the upper end of the temperature sensor support is a cylindrical support rod, the lower end of the temperature sensor support is a round support with a nut, one end of the support rod is provided with threads, and the other end of the support rod is provided with a square groove.
Compared with the prior art, the beneficial effects of this application are as follows:
(1) according to the method for measuring the detonation capability of the cloud and mist, the detonation tube body is made of organic glass, and during testing, a high-speed camera can be used for visually shooting and observing the whole process of the cloud and mist detonation;
(2) the cloud and mist detonation capacity measuring method has the advantages that the number of parameter measurements is large, the data acquisition is stable and reliable, the shock wave pressure measurement stability error can reach about 3%, the explosion temperature measurement stability error can reach about 1.5%, in addition, the test system is simple and convenient to install and operate, and the economic cost is low.
Drawings
FIG. 1 is a front view of a test system in the measurement method of the present application;
FIG. 2 is a side view of a test system constructed in the measurement method of the present application;
FIG. 3 is a front view of a visual cloud detonation tube structure of the present application;
FIG. 4 is a rear view of a visual cloud detonation tube structure of the present application;
FIG. 5 is a typical graph of propylene oxide detonation shock wave pressure;
FIG. 6 is a graph showing an exemplary explosion temperature profile for propylene oxide;
FIG. 7 is a high speed photographic image of the propylene oxide detonation process;
in the figure, 1-visual cloud and mist detonation tube, 1-1-detonation tube body, 1-2-sealing plug, 1-3-detonation end cover, 1-4-tail end cover, 1-5-tube body bracket, 1-6-pressure sensor bracket, 1-7-temperature sensor bracket, 2-pressure sensor, 3-temperature sensor, 4-pressure signal conditioner, 5-temperature signal conditioner, 6-data collector and 7-high-frequency signal line.
The invention is described in further detail below with reference to the drawings and preferred embodiments.
Detailed Description
The following are specific examples given by the inventors.
Example 1
Referring to fig. 1 to 5, the present embodiment provides an application example of the cloud detonation capability measurement method.
The testing system in the cloud and fog detonation capability measuring method provided by one embodiment of the application comprises a visual cloud and fog detonation tube body, a pressure sensor, a temperature sensor, a pressure signal conditioner, a temperature signal conditioner, a data collector, a signal transmission line and the like, wherein the tube body in the visual cloud and fog detonation tube body is a circular tube body, the two ends of the visual cloud and fog detonation tube body are open, the length of the tube body is 1000mm, the outer diameter of the tube body is 200mm, the inner diameter of the tube body is 184mm, the wall thickness of the tube body is 8mm, the material is organic glass, the tube body is provided with 7 pressure sensor interfaces, temperature sensor interfaces and fuel filling ports, the pressure sensor interfaces are circular, the aperture is 21mm, the distance is 100mm, the visual cloud and fog detonation tube body is distributed on one side of the detonation tube body and parallel to the axis of the tube body, the first interface is 200mm away from the front end of the detonation tube body, the temperature sensor interfaces are 2 in total, the interfaces are, the distance between the fuel filling ports and the front end of the detonation tube body is respectively 500mm and 700mm, the number of the fuel filling ports is 4, the filling ports are circular, the aperture is 10mm, the distance is 200mm, the fuel filling ports are distributed on the upper part of the detonation tube body and are parallel to the axis of the detonation tube body, and the distance between the first filling port and the front end of the detonation tube body is 200 mm; the sealing plug is a silicon rubber sealing plug and is formed by an upper round table and a lower round table into a whole, the diameter of the upper round table is 15mm, the thickness of the upper round table is 10mm, the diameter of the lower round table is 11mm, and the thickness of the lower round table is 8 mm; the detonating end cap is a circular disc with a central hole, and is formed by an upper circular table and a lower circular table into a whole, the diameter of the upper circular table is 184mm, the thickness of the upper circular table is 10mm, the diameter of the lower circular table is 210mm, the thickness of the lower circular table is 10mm, the diameter of the central hole of the end cap is 2mm, and the material is 2A12 type aluminum; the tail end cover is a disc with a plug in the center and is formed by an upper part and a lower part into a whole, the diameter of the upper round table is 184mm, the thickness of the upper round table is 10mm, the diameter of the lower round table is 210mm, the thickness of the lower round table is 10mm, an M12 threaded through hole is formed in the center of the end cover, the end cover is made of 2A12 type aluminum, the plug is an M12 screw, the length of the thread is 20mm, and the end cover is; the pipe body support is an adjustable lifting support made of steel, the upper end of the pipe body support is an 1/4 arc-shaped plate, the middle of the pipe body support is a cylindrical support rod with threads at one end, and the lower end of the pipe body support is a square support with a nut; the pressure sensor support is an adjustable lifting support made of steel, the upper end of the pressure sensor support is an 1/4 arc-shaped plate, the middle of the pressure sensor support is a cylindrical support rod with threads at one end, and the lower end of the pressure sensor support is a circular support with a nut; the temperature sensor support is an adjustable lifting support made of steel, the upper end of the temperature sensor support is a cylindrical support rod, the lower end of the temperature sensor support is a round support with a nut, one end of the support rod is provided with threads, and the other end of the support rod is provided with a square groove.
The number of pressure sensors in the test system is 4, the pressure sensors are respectively arranged at interfaces 1, 3, 5 and 7 of the detonation end, high-frequency dynamic pressure sensors of Kunmshan double-bridge CYG401 type are selected, and the measuring range is 6 MPa. The temperature sensors are 2 in number, are respectively arranged on 2 temperature sensor interfaces, and are armored thermocouples of WRKKJ-103-D type.
The testing system is used for measuring the detonation performance of the typical fuel propylene oxide gas with the volume fraction of 20 percent, the test is carried out for 3 times, and the test is specifically carried out according to the following steps:
the method comprises the following steps: fixing the pressure sensor and the temperature sensor on the corresponding interface of the detonation tube body through glass cement, ensuring the interface to be sealed firmly, adhering and sealing the interface without the sensor by using a sealing adhesive tape, and then placing the detonation tube body, the tube body bracket and the sensor bracket in an explosion field after the glass cement is cured for 24 hours;
step two: the pressure sensor, the temperature sensor, the signal conditioner and the data acquisition unit are connected through signal wires, and a test system is debugged to ensure that the pressure sensor, the temperature sensor, the signal conditioner and the data acquisition unit work normally;
step three: laying a high-speed camera, and debugging shooting parameters and a visual angle to enable a shooting scene to be aligned to the detonation tube;
step four: a small quick-adhesion hook is adhered to the top, which is about 10cm away from an initiation port, in a detonation tube body, then a detonator and initiating explosive are installed, the detonator is a No. 8 universal electric detonator, and the initiating explosive is a JH-14 explosive column with the diameter of phi 10mm multiplied by 10mm and does not have a detonator hole. Firstly, firmly bonding the bottom of a detonator with the end face of an initiating explosive column by using an adhesive tape, and then vertically hanging the detonator on a hook in a tube body by using a detonator leg wire, wherein the initiating explosive column is positioned at the center of the section of the tube body;
step five: penetrating out a detonator leg wire terminal from a center hole of the detonating end cover, connecting the detonator leg wire terminal with the detonating wire, sealing and fixing the detonating end cover and a center threading hole by using glass cement, and sealing and fixing a tail end cover of the belt plug by using the glass cement;
step six: according to the volume of the detonation tube body, theoretically calculating the mass of the required propylene oxide liquid to be 13.8g when the volume fraction of the propylene oxide gas accounts for 20%, then quickly and uniformly adding the weighed propylene oxide liquid from 4 fuel filling ports at the upper end of the detonation tube body by using a pipette, and then sealing the fuel filling ports by using a sealing plug;
step seven: and observing the volatilization condition of the epoxypropane liquid, starting a data collector and high-speed photography after the epoxypropane liquid is completely volatilized and is uniformly mixed with air in the detonation tube body, then detonating the detonator, recording shock wave pressure data and explosion temperature data by the data collector, and recording cloud detonation process images by the high-speed photography.
Through data recording, parameters of detonation shock wave pressure P and explosion temperature T at the time of 20% of volume fraction of the tested propylene oxide gas are respectively obtained by a pressure sensor and a temperature sensor, test results are respectively shown in tables 1 and 2, a typical detonation shock wave pressure curve is shown in fig. 5, a typical explosion temperature curve is shown in fig. 6, and a high-speed photographic image is shown in fig. 7.
TABLE 1 propylene oxide detonation shock wave pressure data
TABLE 2 propylene oxide explosion temperature data
From the analysis of the shock wave pressure data in the table 1 above, it can be seen that the mean values of the shock wave pressures in the 3-time propylene oxide/air mixed gas detonation tests are relatively consistent, and are respectively 1.08MPa, 1.02MPa and 0.99MPa, the total mean value is 1.03MPa, the relative errors of the shock wave pressure values in each test are 4.7%, 1.0% and 3.5%, and the mean value is 3.1%. In addition, through the arrival time of the shock wave pressure and the distance between adjacent pressure sensors, the average detonation propagation speeds of the propylene oxide/air mixed gas in 3 times of tests are calculated and obtained and are 928m/s, 889m/s and 906m/s respectively, and the average value is 908 m/s. From the analysis of the explosion temperature data in Table 2, the explosion temperatures of the 3-time explosion tests of the propylene oxide/air mixed gas are 786 ℃, 817 ℃ and 815 ℃, respectively, the average value is 806 ℃, the relative errors are 2.5%, 1.4% and 1.1%, respectively, and the average value is 1.6%. FIG. 7 is a high speed photographic image of the experimental detonation process, with a clear view of the propylene oxide/air detonation propagation process. Through the data analysis of the shock wave pressure and the explosion temperature in the 3 times of tests and the high-speed photographic image of the detonation propagation process, the cloud detonation capability measuring method is suitable for measuring the detonation capability of the fuel-air explosive, and has high measurement stability, the shock wave pressure measurement stability error can reach about 3%, and the explosion temperature measurement stability error can reach about 1.5%.
Claims (1)
1. A cloud detonation capacity measuring method is characterized by comprising the following steps: the method comprises the steps that a testing system consisting of a visual cloud detonation tube (1), a pressure sensor (2), a temperature sensor (3), a pressure signal conditioner (4), a temperature signal conditioner (5), a data collector (6) and a high-frequency signal line (7) is utilized, the visual cloud detonation tube (1) comprises a detonation tube body (1-1), a sealing plug (1-2), a detonation end cover (1-3), a tail end cover (1-4), a tube body support (1-5), a pressure sensor support (1-6) and a temperature sensor support (1-7), the sensor is connected with the signal conditioner through the high-frequency signal line, and the signal conditioner is connected with the data collector through the high-frequency signal line;
the method comprises the following steps:
the method comprises the following steps: fixing the pressure sensor (2) and the temperature sensor (3) on the corresponding interface of the detonation tube body (1-1) through glass cement, ensuring the interface to be sealed firmly, bonding and sealing the interface without the sensor by using a sealing adhesive tape, and then placing the detonation tube body (1-1), the tube body support (1-5), the pressure sensor support (1-6) and the temperature sensor support (1-7) in an explosion field after the glass cement is cured for 24 hours;
step two: the pressure sensor (2), the temperature sensor (3), the pressure signal conditioner (4), the temperature signal conditioner (5) and the data acquisition unit (6) are connected through a high-frequency signal wire (7), and a test system is debugged to ensure that the pressure sensor, the temperature sensor, the pressure signal conditioner and the data acquisition unit work normally;
step three: sticking a small quick-adhesion hook at the top part which is about 10cm away from the initiation port in the detonation tube body (1-1), then installing a detonator and initiating explosive, firstly, firmly sticking the bottom of the detonator and the end face of the initiating explosive column by using an adhesive tape, then vertically hanging the detonator on the hook in the tube body by using a detonator leg wire, and enabling the initiating explosive column to be positioned at the center of the section of the tube body;
step four: enabling a detonator leg wire terminal to penetrate out of a center hole of the detonating end cover and be connected with the detonating wire, sealing and fixing the detonating end cover (1-3) and a center threading hole by using glass cement, and sealing and fixing a tail end cover (1-4) of the belt plug by using the glass cement;
step five: uniformly adding the fuel to be detected through 4 fuel filling ports at the upper end of the detonation tube body (1-1), and then sealing the fuel filling ports by using a sealing plug (1-2);
step six: after the fuel to be tested and the air in the detonation tube body are uniformly mixed, starting the data collector (6), then detonating the detonator, and recording shock wave pressure data and explosion temperature data by the data collector (6).
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| CN202011474035.0A CN112611271A (en) | 2020-12-14 | 2020-12-14 | Cloud detonation capacity measuring method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113341062A (en) * | 2021-07-14 | 2021-09-03 | 北京科技大学 | Pipeline system and method for directly observing detonation of atomized kerosene on combustible premixed gas |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101576521A (en) * | 2009-06-10 | 2009-11-11 | 西安科技大学 | Device for testing explosion, spreading and explosion suppression characteristics of inflammable gas and dust |
| KR20110130085A (en) * | 2010-05-27 | 2011-12-05 | 한국항공우주연구원 | Sensor mounting equipment for measuring the characteristics of flame with high temperature and high pressure |
| CN102930770A (en) * | 2012-10-12 | 2013-02-13 | 浙江工业大学 | Shock tube type combustible gas explosion experiment device |
| CN103412107A (en) * | 2013-05-24 | 2013-11-27 | 西安近代化学研究所 | Nonideal explosive work capacity measuring device |
| CN104634192A (en) * | 2015-01-09 | 2015-05-20 | 西安近代化学研究所 | Testing device for testing deflagration to detonation transition performance of propellant powder |
| CN105928425A (en) * | 2016-07-07 | 2016-09-07 | 宏大矿业有限公司 | Detonating speed measuring device and method of detonating fuse |
| CN107796645A (en) * | 2017-10-20 | 2018-03-13 | 安徽理工大学 | A kind of method of testing of cavity body structure to Gas Detonation wave absorption effect |
-
2020
- 2020-12-14 CN CN202011474035.0A patent/CN112611271A/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101576521A (en) * | 2009-06-10 | 2009-11-11 | 西安科技大学 | Device for testing explosion, spreading and explosion suppression characteristics of inflammable gas and dust |
| KR20110130085A (en) * | 2010-05-27 | 2011-12-05 | 한국항공우주연구원 | Sensor mounting equipment for measuring the characteristics of flame with high temperature and high pressure |
| CN102930770A (en) * | 2012-10-12 | 2013-02-13 | 浙江工业大学 | Shock tube type combustible gas explosion experiment device |
| CN103412107A (en) * | 2013-05-24 | 2013-11-27 | 西安近代化学研究所 | Nonideal explosive work capacity measuring device |
| CN104634192A (en) * | 2015-01-09 | 2015-05-20 | 西安近代化学研究所 | Testing device for testing deflagration to detonation transition performance of propellant powder |
| CN105928425A (en) * | 2016-07-07 | 2016-09-07 | 宏大矿业有限公司 | Detonating speed measuring device and method of detonating fuse |
| CN107796645A (en) * | 2017-10-20 | 2018-03-13 | 安徽理工大学 | A kind of method of testing of cavity body structure to Gas Detonation wave absorption effect |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113341062A (en) * | 2021-07-14 | 2021-09-03 | 北京科技大学 | Pipeline system and method for directly observing detonation of atomized kerosene on combustible premixed gas |
| CN113341062B (en) * | 2021-07-14 | 2022-09-13 | 北京科技大学 | Pipeline system and method for directly observing detonation of atomized kerosene on combustible premixed gas |
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