CN210180846U - Explosion-proof test device for test piece with shell of aircraft power cabin - Google Patents
Explosion-proof test device for test piece with shell of aircraft power cabin Download PDFInfo
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- CN210180846U CN210180846U CN201921074332.9U CN201921074332U CN210180846U CN 210180846 U CN210180846 U CN 210180846U CN 201921074332 U CN201921074332 U CN 201921074332U CN 210180846 U CN210180846 U CN 210180846U
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Abstract
The utility model provides an aircraft power compartment area shell test piece flame proof test device, including explosive atmosphere test case, the test piece, air intake system, exhaust system, a weighing sensor and a temperature sensor, the pipeline switch, the sampling chamber, the circulating air pump, be equipped with the test piece in the explosive atmosphere test case, the test piece top is equipped with air intake system and exhaust system respectively, the inside air inlet pipe way below of test piece is equipped with ignition, the inside temperature monitoring system that still is equipped with of test piece, explosive atmosphere test case right side is equipped with the sampling chamber, sampling chamber top and left side are respectively through pipeline and explosive atmosphere test case UNICOM. The utility model has the advantages that: the circulating gas pump is adopted to circulate combustible gas, a plurality of groups of data with temperature and pressure changes can be acquired simultaneously in one test, the accuracy of test data is guaranteed, meanwhile, for reducing the volume change of the test piece, the connecting line of the test piece is utilized to install the igniter, the drilling of the shell of the test piece is reduced, and the small change of the inner volume of the test piece is guaranteed.
Description
Technical Field
The utility model relates to a test device especially relates to an aircraft power compartment area shell test piece flame proof test device.
Background
In a power cabin of an aircraft or a ship, a combustible gas environment can be formed due to fuel volatilization, when combustible gas permeates into a sealed electric test piece shell, a possibly explosive environment is formed, and when electric elements generate sparks, the shell can be detonated. When the sealing of the shell is not good, the shell can spread to the whole power cabin to cause the damage of the aircraft, so that the capability of the equipment with the shell for isolating the flame generated inside the equipment and preventing the explosion from spreading to the outside is determined through an explosion-proof test.
At present, the number of manufacturers capable of carrying out explosive atmosphere explosion-proof tests in China is small, and combustible gas in the existing explosion-proof test device cannot be recycled, so that multiple groups of data of temperature and pressure changes cannot be obtained simultaneously in one test, the accuracy of test data cannot be guaranteed, and in addition, an igniter is usually additionally arranged in the existing explosion-proof test, a test piece shell needs to be drilled, and the volume change of a test piece is large.
Disclosure of Invention
According to the technical problem, the utility model provides an aircraft power compartment area shell test piece flame proof test device which is characterized in that includes explosive atmosphere test case, test piece, air intake system, exhaust system, temperature sensor, pipeline switch, sampling room, circulating air pump, be equipped with the test piece in the explosive atmosphere test case, the test piece top is equipped with air intake system and exhaust system respectively, air intake system comprises air intake pipeline and pipeline switch, air intake pipeline one end is drawn forth to the explosive atmosphere test case outside by explosive atmosphere test incasement portion, and the other end passes explosive atmosphere test case and test piece UNICOM, exhaust system comprises exhaust pipe, circulating air pump, pipeline switch, exhaust pipe one end is drawn forth to the explosive atmosphere test case outside by test piece inside and is connected with circulating air pump, the exhaust pipe other end stretches into the explosive atmosphere test case inside through circulating air pump, the pipeline switch is arranged on the air inlet pipeline and the exhaust pipeline, the igniter is arranged below the air inlet pipeline inside the test piece, the temperature monitoring system is further arranged inside the test piece, the sampling chamber is arranged on the right side of the explosive atmosphere test box, and the top and the left side of the sampling chamber are respectively communicated with the explosive atmosphere test box through the pipeline.
Further, the detonation device comprises a detonator and a direct current power supply, and the detonator is electrically connected with the direct current power supply through a line.
Furthermore, the temperature monitoring system comprises a temperature sensor and a temperature polling instrument, and the temperature sensor is electrically connected with the temperature polling instrument through a line.
Further, the depth of the exhaust pipeline extending into the test piece is at least one fourth of the height of the test piece.
The utility model has the advantages that: the utility model relates to an aircraft power compartment area shell test piece flame proof test device, found the method that utilizes explosive atmosphere test box to realize the flame proof through the device, the data of temperature and pressure variation among the corresponding flame proof test has been obtained, the circulating air pump has been adopted and has been carried out combustible gas circulation, can obtain multiunit temperature and pressure variation's data simultaneously in a test, the accurate nature of experimental data has been guaranteed, and simultaneously, for reducing the volume change of test piece, utilize the line of test piece self to install ignition, test piece shell drilling has been reduced, the less change of test piece internal volume has been guaranteed. The utility model discloses not only can verify the electrical equipment flame proof ability of taking the shell in the aircraft power compartment, also can verify simultaneously in the marine engine compartment, the flame proof ability of the electrical component that has the combustible gas place such as mine, along with people's attention to safety, more host computer factories attach importance to test piece performance, need accomplish the demand of this experiment and constantly increase, compensatied the not enough of equipment supply volume few, simple and crude on the existing market.
Drawings
FIG. 1 is a view of the main structure of the present invention;
FIG. 2 is a flow chart of the test of the present invention;
FIG. 3 is a chart of data records of temperature changes of the sample chamber and the test piece during pre-testing;
FIG. 4 is a chart of data records of temperature changes of the sampling chamber and the test piece during the formal test.
As shown in the figure, the device comprises an explosive atmosphere test box-1, a test piece-2, an air inlet pipeline-3, an exhaust pipeline-4, a temperature sensor-5, a detonator-6, a pipeline switch-7, a sampling chamber-8, a circulating air pump-9, a direct current power supply-10 and a temperature polling instrument-11.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings:
example 1:
the utility model relates to an aircraft power compartment area shell test piece flame proof test device, its characterized in that includes explosive atmosphere test case 1, test piece 2, air intake system, exhaust system, temperature monitoring system, pipeline switch 7, sampling chamber 8, circulating air pump 9, be equipped with test piece 2 in the explosive atmosphere test case 1, test piece 2 top is equipped with air intake system and exhaust system respectively, air intake system comprises air inlet pipe 3 and pipeline switch 7, air inlet pipe 3 one end is drawn forth to explosive atmosphere test case 1 outside by explosive atmosphere test case 1 inside, the other end passes explosive atmosphere test case 1 and test piece 2 UNICOM, exhaust system comprises exhaust pipe 4, circulating air pump 9, pipeline switch 7, exhaust pipe 4 one end is drawn forth to explosive atmosphere test case 1 outside by test piece 2 inside and is connected with circulating air pump 9, the exhaust line 4 extends into the test piece 2 to a depth of at least one quarter of the height of the test piece 2, the other end of the exhaust pipeline 4 extends into the explosive atmosphere test box 1 through a circulating air pump 9, the air inlet pipeline 3 and the exhaust pipeline 4 are both provided with a pipeline switch 7, an igniter is arranged below the air inlet pipeline 3 in the test piece 2 and comprises an igniter 6 and a direct current power supply 10, the detonator 6 is electrically connected with a direct current power supply 10 through a line, a temperature monitoring system is also arranged in the test piece 2, the temperature monitoring system also comprises a temperature sensor 5 and a temperature polling instrument 11, the temperature sensor 2 is electrically connected with the temperature polling instrument 11 through a line, the right side of the explosive atmosphere test box 1 is provided with a sampling chamber 8, and the top and the left side of the sampling chamber 8 are communicated with the explosive atmosphere test box 1 through pipelines respectively.
Example 2:
firstly, a test piece 2 is pre-tested, a test temperature curve is shown in fig. 3 after the test, temperature change in the graph can be known, the interior of the test piece 2 can be detonated smoothly, after the pre-test of the test piece 2 is successful, a formal test is carried out on the test piece 2, the formal test curve is shown in fig. 4, and obvious temperature change can be seen from the test curve, so that 5 times of explosion in the test piece 2 can be judged, meanwhile, after 5 times of explosion, the mixed gas of the explosive atmosphere test box 1 has flammability, after the test is finished, the explosion does not occur in the explosive atmosphere test box 1, the test piece 2 passes the examination, and the specific operation is as follows: utilize air intake system and exhaust system with the inside mist that lets in combustible gas and air of test piece 2, make the mist be full of inside test piece 2, the utility model discloses well combustible gas adopts normal ethane, then, utilize and install 6 ignitable gases at the inside detonator of test piece 2, recycle and install and monitor whether combustible gas is lighted at the inside temperature sensor 5 of test piece 2, if ignite, then test success once, five times are lighted in this test altogether, after the inside combustible gas of test piece 2 is lighted five times, do not detonate explosive atmosphere test box 1 in the combustible gas, then test piece 2 is through the examination, possess the flame that cuts off its inside emergence and the ability that the explosion is unlikely to spread to the outside.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications can be made without departing from the principle of the present invention, and these modifications should also be regarded as the protection scope of the present invention.
Claims (4)
1. An explosion-proof test device for a test piece with a shell of an aircraft power compartment is characterized by comprising an explosive atmosphere test box, the test piece, an air inlet system, an exhaust system, a temperature monitoring system, a pipeline switch, a sampling chamber and a circulating air pump, wherein the test piece is arranged in the explosive atmosphere test box, the top of the test piece is respectively provided with the air inlet system and the exhaust system, the air inlet system consists of an air inlet pipeline and the pipeline switch, one end of the air inlet pipeline is led out from the interior of the explosive atmosphere test box to the exterior of the explosive atmosphere test box, the other end of the air inlet pipeline penetrates through the explosive atmosphere test box to be communicated with the test piece, the exhaust system consists of an exhaust pipeline, the circulating air pump and the pipeline switch, one end of the exhaust pipeline is led out from the interior of the test piece to the exterior of the explosive atmosphere test box to be connected with the circulating air pump, and the, the pipeline switch is arranged on the air inlet pipeline and the exhaust pipeline, the igniter is arranged below the air inlet pipeline inside the test piece, the temperature monitoring system is further arranged inside the test piece, the sampling chamber is arranged on the right side of the explosive atmosphere test box, and the top and the left side of the sampling chamber are respectively communicated with the explosive atmosphere test box through the pipeline.
2. The explosion-proof test device for the test piece with the shell of the aircraft power compartment according to claim 1, wherein the detonation device further comprises a detonator and a direct-current power supply, and the detonator is electrically connected with the direct-current power supply through a line.
3. The explosion-proof test device for the test piece with the shell of the aircraft power compartment according to claim 1, wherein the temperature monitoring system further comprises a temperature sensor and a temperature patrol instrument, and the temperature sensor is electrically connected with the temperature patrol instrument through a line.
4. An explosion-proof test device for a test piece with a shell of an aircraft power cabin, according to claim 1, characterized in that the depth of the exhaust pipeline extending into the test piece is at least one fourth of the height of the test piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921074332.9U CN210180846U (en) | 2019-07-10 | 2019-07-10 | Explosion-proof test device for test piece with shell of aircraft power cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921074332.9U CN210180846U (en) | 2019-07-10 | 2019-07-10 | Explosion-proof test device for test piece with shell of aircraft power cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210180846U true CN210180846U (en) | 2020-03-24 |
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ID=69840524
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921074332.9U Active CN210180846U (en) | 2019-07-10 | 2019-07-10 | Explosion-proof test device for test piece with shell of aircraft power cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210180846U (en) |
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2019
- 2019-07-10 CN CN201921074332.9U patent/CN210180846U/en active Active
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