CN109932140A - A kind of leakage system safety testing device for space flight low-temperature composite material component - Google Patents
A kind of leakage system safety testing device for space flight low-temperature composite material component Download PDFInfo
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- CN109932140A CN109932140A CN201910377941.XA CN201910377941A CN109932140A CN 109932140 A CN109932140 A CN 109932140A CN 201910377941 A CN201910377941 A CN 201910377941A CN 109932140 A CN109932140 A CN 109932140A
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- 239000002131 composite material Substances 0.000 title claims abstract description 73
- 238000009781 safety test method Methods 0.000 title claims abstract description 30
- 239000001307 helium Substances 0.000 claims abstract description 125
- 229910052734 helium Inorganic materials 0.000 claims abstract description 125
- 238000012360 testing method Methods 0.000 claims abstract description 63
- 239000007788 liquid Substances 0.000 claims abstract description 38
- 239000012528 membrane Substances 0.000 claims abstract description 15
- 238000010079 rubber tapping Methods 0.000 claims abstract description 7
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims abstract 25
- 239000007789 gas Substances 0.000 claims description 21
- 238000005086 pumping Methods 0.000 claims description 10
- 238000007789 sealing Methods 0.000 claims description 9
- 238000002347 injection Methods 0.000 claims description 8
- 239000007924 injection Substances 0.000 claims description 8
- 230000008878 coupling Effects 0.000 claims description 6
- 238000010168 coupling process Methods 0.000 claims description 6
- 238000005859 coupling reaction Methods 0.000 claims description 6
- 238000012544 monitoring process Methods 0.000 claims description 6
- 239000000565 sealant Substances 0.000 claims description 6
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 238000012790 confirmation Methods 0.000 claims description 2
- 238000001228 spectrum Methods 0.000 claims description 2
- 229910001209 Low-carbon steel Inorganic materials 0.000 claims 1
- 229910045601 alloy Inorganic materials 0.000 claims 1
- 239000000956 alloy Substances 0.000 claims 1
- 238000009423 ventilation Methods 0.000 claims 1
- 238000001514 detection method Methods 0.000 abstract description 14
- 238000012827 research and development Methods 0.000 abstract description 3
- MCWJHOCHKYKWMK-UHFFFAOYSA-N helium Chemical compound [He].[He] MCWJHOCHKYKWMK-UHFFFAOYSA-N 0.000 description 101
- 238000000034 method Methods 0.000 description 17
- 239000000463 material Substances 0.000 description 11
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- 229910001339 C alloy Inorganic materials 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000005494 condensation Effects 0.000 description 2
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- 229920006255 plastic film Polymers 0.000 description 2
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- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
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Abstract
The invention discloses a kind of leakage system safety testing devices for space flight low-temperature composite material component, including liquid helium bottle, vacuum pump, helium mass spectrometer leak detector, liquidometer, test tank and hermetically sealed can, breathable membrane is provided in test tank, the top cover of test tank is equipped with helium inlet A and exhaust outlet A, liquid helium bottle is connected with helium inlet A, vacuum pump is connected by vacuum line and helium mass spectrometer leak detector with test tank, the bottom plate of hermetically sealed can is equipped with step aperture, and composite element setting is tightly connected in step tapping and with hermetically sealed can；The helium inlet B and exhaust outlet B of hermetically sealed can pass through pipeline respectively and are connected with the helium inlet A of test tank and exhaust outlet A.Leakage system safety testing device of the invention can highly restore locating low temperature environment when composite element is on active service, and realize and carry out the leakage detection of low temperature to composite element；The present invention provides necessary detection device for the research and development for the composite system of resistance to extreme environment.
Description
Technical field
The present invention relates to the engineering device technique fields of detection material seepage property, particularly, are related to a kind of for space flight low temperature
The leakage system safety testing device of composite element.
Background technique
Space launch vehicle as can by the spaces device such as artificial satellite, space station, airship be sent into cosmic space it is important
Flight carrier is the important symbol of a National Airspace scientific and technological level.Future Spacecraft and the development trend of carrier rocket are tools
Standby high carrying capacity, while its manufacturing cost is utmostly reduced, such as inexpensive spacecraft, Reusable launch vehicles, list
Grade, which is entered the orbit, waits spacecrafts, this just needs for the transmitting total weight of spacecraft to be preferably minimized.In order to realize high delivery power, low cost boat
The development of its device it may first have to which solution is exactly the excessive problem of aircraft overall weight.Propellant tank is as carrier rocket
One of chief component, occupy very large space, be main loss of weight component.
The development of low-temperature composite material component is the key that carry out next-generation space exploration and creation New Launch one
Step.Currently, the aviation vehicle of mainstream attempts weight and production cost that complete machine is reduced using composite material in the world,
Systems in Certain Developed Countries is successfully applied among the manufacture of aerospace craft Cryogenic tank.Traditional low temp fuel tank is big
It is all to be prepared by metal material (such as high strength alumin ium alloy etc.) by welding procedure, but with the height of composite technology
Speed development and the gradually application in aerospace field, the especially composite system of cold cycling good mechanical performance
Constantly research and development, so that becoming the main direction of development of space launch vehicle lighting without liner full composite material Cryogenic tank.It is compound
Material has higher specific strength and specific modulus compared to metal material, while having both excellent anti-fatigue performance.Composite material
Cryogenic tank can be realized loss of weight target 20-40% lower than current aluminium alloy tank, and various advanced used by it
The assembly of components can be greatly reduced in moulding process, greatly enhance production efficiency, shorten the production cycle, reach
The purpose for reducing production cost is arrived.However, due to the cryogenic media (such as liquid oxygen, liquid hydrogen) held inside space launch vehicle tank
Small molecule characteristic, material internal is easily penetrated by the manufacturing defect of tank；Meanwhile in order to maintain the liquid of low temp fuel
State, generally there are the pressure of 0.2-0.3MPa in tank, huge pressure difference and long-term alternating hot and cold circulation of bearing inside and outside cabinet are answered
The complex working conditions such as power can make material internal generate micro-crack, and the continuous of micro-crack extends and be connected to and cryogenic media can be caused to leak
The problem of, it finally results in tank and fails and destroy.Therefore, normal, low temperature is carried out to composite element and sample before serving to seep
The test of leakage property is very necessary.
Currently, the domestic leakage test method of composite material generallyd use is the pressure difference based on GB/T 1038-2000
Method.The method is suitable for measuring the gas transit dose and gas transmission coefficient of plastic film and thin slice.Utilize plastic film or thin
Piece separates high and low pressure chamber, and the test gas of 0.1MPa is filled with into hyperbaric chamber, with vacuum pump by low pressure after sample is sealed
Air in room is extracted into close to zero.The indoor pressure increment of low pressure is measured using manometer, that is, can determine test gas by height
Pressure chamber is through films/sheets to low-pressure chamber using the time as the gas flow of function.The method can be used for penetrating for most of gas and measure
It is fixed, there is certain universality；But the transit dose of gas needs to carry out subsequent calculation processing, complex steps and can introduce error；
Meanwhile the method can only carry out the measurement of gas transit dose under room temperature, not be related to the test of fluid seepage under low temperature.
Those skilled in the art improves the infiltration for detecting material at normal temperature or low temperature to above-mentioned test method
Performance is leaked, such as discloses one kind application No. is the application for a patent for invention of CN201610810397.X and detects at normal temperature or low temperature
The method and apparatus of material seepage property, this method and device are based on pressure differential method and fluorescence method dual principle, in test sample
Upper surface covering fluoroscopic leak test liquid and the high pressure gas for being passed through specified pressure calculate sample according to the gas pressure change of lower surface
Gas transit dose, and by ultraviolet light sample lower surface observe fluorescence leakage situation, to determine leak location.In addition,
By be mixed with fluorescer and liquid nitrogen to obtain low temperature fluoroscopic leak test liquid, it can be achieved that under low temperature material seepage property detection.
But this method still need by gas pressure change calculate sample gas transit dose, complex steps and not intuitively；Together
When, the low temperature for being only simply covered on specimen surface using mixture prepared low temperature fluoroscopic leak test liquid, therefore obtaining leaks
Testing result also has deviation.
In addition, application No. is the patent applications of CN201811612392.1 to disclose a kind of ring network cabinet SF6 gas tank helium inspection system
System and method are applicable in and carry out dry type leak detection to 10kV ring network cabinet SF6 gas tank.The system includes the vacuum for placing examined workpiece
Case leakage detection apparatus, for vacuum box leak detection device and examined workpiece fill helium and recycle helium helium recyclable device, for pair
The helium mass spectrometer leak detector that examined workpiece is hunted leak and the PLC for controlling helium recyclable device and helium mass spectrometer leak detector.Though the system
So can judge at normal temperature whether examined workpiece is qualified using helium and helium mass spectrometer detector, but the system obviously cannot be used
In the leakage test of space flight low-temperature composite material component under cryogenic.
Therefore, it is necessary to be directed to seepage property and prevention of the space flight low-temperature composite material component under extremely low temperature for this field
Research is made in corrective measure.
Summary of the invention
The purpose of the present invention is to provide a kind of leakage system safety testing devices for space flight low-temperature composite material component, with solution
Material seepage property detection device certainly in the prior art can not highly restore locating low temperature environment when composite element is on active service
The problem of.
To achieve the above object, the present invention provides a kind of leakage test dresses for space flight low-temperature composite material component
It sets, the leakage system safety testing device is for detecting the seepage property of space flight low-temperature composite material component at low temperature, the leakage
System safety testing device includes liquid helium bottle, vacuum pump, helium mass spectrometer leak detector, liquidometer, test tank and for placing composite element
Hermetically sealed can, the test tank includes tank body and the top cover for sealing the tank body, be provided in the test tank it is ventilative every
Plate, the top cover are equipped with helium inlet A and exhaust outlet A, and the liquid helium bottle is connected by pipeline with the helium inlet A, institute
State vacuum pump and be connected with the helium mass spectrometer leak detector by vacuum line, the helium mass spectrometer leak detector pass through vacuum line with it is described
The vacuum pumping opening of tank body is connected, and the hermetically sealed can is arranged on the breathable membrane, and the bottom plate of the hermetically sealed can is equipped with platform
Rank aperture, the composite element setting are tightly connected in the step tapping and with the hermetically sealed can, the hermetically sealed can
Helium inlet B and exhaust outlet B pass through pipeline respectively and be connected with the helium inlet A of the test tank and exhaust outlet A, helium note
Entrance B and exhaust outlet B are arranged on the upper lid of the hermetically sealed can, and the upper Gai Shangyong of the hermetically sealed can is arranged in the liquidometer
In the height of the liquid helium in measurement injection hermetically sealed can.
Preferably, the leakage system safety testing device further includes that can be used to detect space flight low-temperature composite material component at normal temperature
Seepage property helium tank, pressure gauge and triple valve, triple valve setting the liquid helium bottle and the helium inlet A it
Between pipeline on, the helium tank is connected by pipeline with the helium inlet A, and the pressure gauge setting is on the hermetically sealed can
For monitoring the pressure of gas in hermetically sealed can constantly.
Preferably, the breathable membrane is the stainless steel plate with several ventholes, the breathable membrane level and height
Adjustably it is arranged in the test tank.
Preferably, the vacuum pumping opening is arranged on the side wall of the tank body, and the vacuum pumping opening is equipped with quick
Connector, the helium mass spectrometer leak detector are connected by vacuum line with the quick coupling.
Preferably, the step aperture includes the first aperture recessed down at the top of hermetically sealed can bottom plate and from the first aperture
Bottom surface downward through the sealing tank bottom the second aperture, the shape of first aperture and the composite element
Shape is adapted, and the supporting table for being used to support the composite element is formed between second aperture and the first aperture
Rank.
Preferably, the composite element is arranged on support level, the composite element by sealant with
The sealing tank bottom is tightly connected.
Preferably, the front of the tank body is equipped with for monitoring whether state and each instrument numerical value of confirmation in tank normally regard
Window.
Preferably, it is additionally provided on the top cover of the test tank convenient for opening the top cover handle of the test tank, the exhaust
The valve for adjusting capacity size is equipped at mouth A.
Preferably, the test tank and hermetically sealed can are made of low-carbon alloy steel.
Compared with the prior art, the invention has the following advantages:
(1), the leakage system safety testing device for space flight low-temperature composite material component of the invention, including liquid helium bottle, vacuum
Pump, helium mass spectrometer leak detector, liquidometer, test tank and hermetically sealed can are provided with breathable membrane in test tank, set on the top cover of test tank
There are helium inlet A and exhaust outlet A, liquid helium bottle is connected by pipeline with helium inlet A, and vacuum pump passes through vacuum line and helium mass spectrum
Leak detector is connected, and helium mass spectrometer leak detector is connected by vacuum line with the vacuum pumping opening of tank body, hermetically sealed can setting breathe freely every
On plate, the bottom plate of hermetically sealed can is equipped with step aperture, and composite element setting seals company in step tapping and with hermetically sealed can
It connects, the helium inlet B and exhaust outlet B of hermetically sealed can pass through pipeline respectively and be connected with the helium inlet A of test tank and exhaust outlet A, liquid
Position meter is arranged on hermetically sealed can for measuring the height of the liquid helium in injection hermetically sealed can.The present invention is for locating for composite element
The extreme service condition of complexity under issuable cryogenic media the problem of leaking, be based on GB/T1038-2000, devise one kind
The leakage system safety testing device that locating low temperature environment when composite element is on active service can highly be restored, is realized to composite element
Carry out the leakage detection of low temperature；The present invention can exclude environment, gas and vapor pair in material by introducing helium mass spectrometer leak detector
The influence of pressure differential method test result, accurate, the intuitive seepage property for reflecting testpieces under different condition are multiple for resistance to extreme environment
The research and development of condensation material system provide necessary detection device.
(2), the leakage system safety testing device for space flight low-temperature composite material component of the invention further includes helium tank, pressure
Power table and triple valve, triple valve are arranged on the pipeline between liquid helium bottle and helium inlet A, and helium tank passes through pipeline and test tank
Triple valve be connected, pressure gauge be arranged on composite element for the moment monitoring hermetically sealed can in gas pressure.The structure
Leakage system safety testing device so that of the invention is set, in addition to it can carry out the leakage detection of low temperature to composite element, moreover it is possible to
It is enough in and the leakage detection of room temperature is carried out to composite element.
(3), the leakage system safety testing device for space flight low-temperature composite material component of the invention, step aperture includes from close
At the top of sealed cans bottom plates the first aperture recessed down and from the bottom surface of the first aperture downward through the second aperture of sealing tank bottom,
The shape of first aperture is adapted with the shape of composite element, and is formed and be used to support between the second aperture and the first aperture
The support level of composite element.In the structure setting, composite element can be arbitrary shape；Composite element
Sealant is arranged in periphery, makes to seal between component and hermetically sealed can with composite material；Specifically, second on tank bottom is sealed
The size for being sized to be slightly smaller than composite element of aperture, in case composite element is fallen from tapping.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to figure, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the structural schematic diagram of embodiment 1 in the present invention；
Fig. 2 is the enlarged structure schematic diagram of hermetically sealed can in embodiment 1 in the present invention；
Fig. 3 is the structural schematic diagram of embodiment 2 in the present invention；
Fig. 4 is the enlarged structure schematic diagram of hermetically sealed can in embodiment 2 in the present invention；
Wherein, 1, liquid helium bottle, 2, vacuum pump, 3, vacuum line, 4, helium mass spectrometer leak detector, 5, quick coupling, 6, helium injection
Mouth A, 7, liquidometer, 8, top cover handle, 9, pressure gauge, 10, exhaust outlet A, 11, top cover, 12, form, 14, test tank, 15, helium
Bottle, 16, hermetically sealed can, 17, breathable membrane, 18, composite element, 19, sealant, 20, helium inlet B, 21, exhaust outlet B,
22, upper cover, 23, triple valve.
Specific embodiment
The embodiment of the present invention is described in detail below in conjunction with attached drawing, but the present invention can be limited according to claim
Fixed and covering multitude of different ways is implemented.
Embodiment 1
Referring to Fig. 1 and Fig. 2, a kind of leakage system safety testing device for space flight low-temperature composite material component of the invention, packet
Include liquid helium bottle 1, vacuum pump 2, helium mass spectrometer leak detector 4, liquidometer 7, test tank 14 and for placing the close of composite element 18
Sealed cans 16, test tank include tank body and the top cover 11 for sealed shell of tank, are provided with breathable membrane 17 in tank body, top cover is equipped with
Helium inlet A6 and exhaust outlet A10, liquid helium bottle are connected by pipeline with helium inlet A6, and vacuum pump passes through vacuum line 3 and helium
Mass-spectrometer leak detector is connected, and helium mass spectrometer leak detector is connected by vacuum line 3 with the vacuum pumping opening of tank body, and vacuum pump will be for that will survey
Space between examination tank and hermetically sealed can vacuumizes, and to exclude influence of the helium ingredient to test result in air, guarantees helium matter
The helium ingredient that spectrum leak detector detects all is by leaking in hermetically sealed can.Preferably, vacuum pumping opening is arranged in tank body
Side wall on, vacuum pumping opening is equipped with quick coupling 5, and helium mass spectrometer leak detector is connected by vacuum line 3 with quick coupling.
Hermetically sealed can is arranged on breathable membrane, and the bottom plate of hermetically sealed can 16 is equipped with step aperture；Composite element is set
It sets in step tapping and is tightly connected with hermetically sealed can.The helium inlet B20 and exhaust outlet B21 of hermetically sealed can pass through respectively pipeline with
The helium inlet A6 of test tank is connected with exhaust outlet A10, and helium inlet B and exhaust outlet B are arranged in the upper cover 22 of hermetically sealed can；
Liquidometer is arranged on the top cover 22 of hermetically sealed can for measuring the height of the liquid helium in injection hermetically sealed can.The present embodiment it is leakage
In test device, due to that can volatilize in liquid helium injection process, the pressure in hermetically sealed can be made to increase, thus be arranged in a device
Exhaust outlet A and exhaust outlet B keeps liquid helium in hermetically sealed can in certain height to be discharged the helium by volatilizing in liquid helium in time,
So that liquid helium keeps injection and volatilization and forms a dynamic equilibrium process.
In the present embodiment, step aperture include from recessed down and the first aperture of shape at the top of hermetically sealed can bottom plate and from
Second aperture of the bottom surface of first aperture downward through sealing tank bottom, the shape and the shape of composite element 18 of the first aperture
Shape is adapted, and the support level for being used to support composite element is formed between the second aperture and the first aperture.The structure is set
In setting, composite element can be arbitrary shape；Sealant is arranged in the periphery of composite element, makes component with composite material
It can be sealed between hermetically sealed can；Specifically, seal second aperture on tank bottom is sized to be slightly smaller than composite element
Size, in case composite element is fallen from tapping.Leakage under the low-temperature condition of missile propellant application, at sealant
It also can be ignored relative to the leakage at composite element.
In the present embodiment, breathable membrane is the stainless steel plate with several ventholes, and breathable membrane is horizontal and height can
Ground is adjusted to be arranged in test tank.Breathable membrane is used to support hermetically sealed can, and it is suitable in test tank that hermetically sealed can is smoothly placed in
Position, in order to operate and test；The gas permeability design of partition is to facilitate in vacuum pump work by down space on partition
It all vacuumizes, creates the overall vacuum environment in test tank.
In the present embodiment, the tank body front of test tank is equipped with for monitoring state in tank and whether confirming each instrument numerical value
Normal form 12.It is additionally provided on the top cover of test tank convenient for opening the top cover handle 8 of test tank, is equipped with and uses at exhaust outlet A10
In the valve for adjusting capacity size.
In a kind of specific embodiment, test tank and hermetically sealed can are made of low-carbon alloy steel.
It is seeped at low ambient temperatures using the leakage system safety testing device of the present embodiment is accidental to space flight low-temperature composite material
Leak performance test, test method specifically: composite element 18 to be tested is placed in bottom with step aperture first
In hermetically sealed can 16, hermetically sealed can is put on the breathable membrane 17 in test tank 14, by the helium inlet B and exhaust outlet on hermetically sealed can
B respectively with the helium inlet A6 in test tank is corresponding with exhaust outlet A10 is connected to, close the top cover 11 of test tank；Then by liquid helium
Bottle 1 is connected to the helium inlet A in test tank by pipeline；Vacuum pump and helium mass spectrometer leak detector are opened, is first excluded in air
Influence of the helium ingredient to test result vacuumizes the space between test tank and hermetically sealed can until helium mass spectrometer leak detector registration
When being zero or being steadily lower than some numerical value, the open state of vacuum pump and helium mass spectrometer leak detector is kept, test starts；Open liquid
Helium bottle valve, the small flow of control liquid helium, which injects in hermetically sealed can, to be pre-chilled, and reduces rapidly the temperature in hermetically sealed can, the liquid helium of volatilization can
It is discharged by exhaust outlet B and exhaust outlet A；Liquid helium injection rate, observation 7 registration of liquidometer variation are increased after a period of time；Observation is simultaneously
The variation of helium mass spectrometer leak detector registration is recorded, the seepage property of composite element at low ambient temperatures is obtained；After being completed, close
Liquid helium bottle valve, vacuum pump and helium mass spectrometer leak detector are closed, liquid helium volatilizees naturally in tank to be sealed.
Embodiment 2
Referring to Fig. 3 and Fig. 4, on the basis of above-described embodiment 1: the leakage system safety testing device of the present embodiment further includes that can use
In helium tank 15, pressure gauge 9 and the triple valve 23 of the seepage property of detection space flight low-temperature composite material component at normal temperature, threeway
Valve 23 is arranged on the pipeline between liquid helium bottle 1 and helium inlet A6, and helium tank is connected by pipeline with triple valve, and pressure gauge is set
It sets on hermetically sealed can, the pressure for gas in moment monitoring hermetically sealed can.The structure setting can be more by helium source by triple valve
Conveniently and safely switch between liquid helium bottle 1 and helium tank 15, so that the leakage system safety testing device of the present embodiment, removing can be to multiple
Condensation material component carries out other than the leakage detection of low temperature, additionally it is possible to for carrying out the leakage inspection of room temperature to low-temperature composite material component
It surveys.
On the basis of above-described embodiment 1, using the leakage system safety testing device of the present embodiment to space flight low-temperature composite material
Component carries out seepage property test under normal temperature environment method particularly includes: is operated first triple valve 23, makes helium tank 16 and survey
The helium inlet A tried on tank is connected to by pipeline；Vacuum pump and helium mass spectrometer leak detector are opened, the helium ingredient in air is first excluded
Influence to test result, vacuumizes the space between test tank and hermetically sealed can and helium mass spectrometer leak detector registration is zero or stablizes
When ground is lower than some numerical value, the open state of vacuum pump and helium mass spectrometer leak detector is kept, test starts；Open helium bottle valve to
Helium is injected in hermetically sealed can, when learning that sealing pressure inside the tank reaches certain value from pressure gauge 9, is closed the valve of helium tank, is stopped
Helium is only injected into hermetically sealed can, observes and records the numerical value of percolation ratio on helium mass spectrometer leak detector；After being completed, vacuum is closed
Pump and helium mass spectrometer leak detector open exhaust outlet A10, the helium in hermetically sealed can quickly be discharged.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (9)
1. a kind of leakage system safety testing device for space flight low-temperature composite material component, which is characterized in that the leakage test
For device for detecting the seepage property of space flight low-temperature composite material component at low temperature, the leakage system safety testing device includes liquid helium
Bottle (1), vacuum pump (2), helium mass spectrometer leak detector (4), liquidometer (7), test tank (14) and for placing composite element
(18) hermetically sealed can (16), the test tank include tank body and the top cover (11) for sealing the tank body, are set in the tank body
Be equipped with breathable membrane (17), the top cover is equipped with helium inlet A (6) and exhaust outlet A (10), the liquid helium bottle by pipeline and
The helium inlet A (6) is connected, and the vacuum pump is connected by vacuum line (3) with the helium mass spectrometer leak detector, the helium matter
Spectrum leak detector is connected by vacuum line (3) with the vacuum pumping opening of the tank body, and the hermetically sealed can (16) is arranged described
On air bound plate, the bottom plate of the hermetically sealed can is equipped with step aperture, and the composite element is arranged in the step tapping
And be tightly connected with the hermetically sealed can, the helium inlet B (20) and exhaust outlet B (21) of the hermetically sealed can pass through pipeline and institute respectively
The helium inlet A (6) for stating test tank is connected with exhaust outlet A (10), and the helium inlet B and exhaust outlet B are arranged at described close
In the upper cover (22) of sealed cans, the liquidometer is arranged in the upper cover (22) of the hermetically sealed can for measuring in injection hermetically sealed can
The height of liquid helium.
2. leakage system safety testing device according to claim 1, which is characterized in that the leakage system safety testing device further includes energy
For detecting the helium tank (15), pressure gauge (9) and triple valve of the seepage property of space flight low-temperature composite material component at normal temperature
(23), on the pipeline that the triple valve is arranged between the liquid helium bottle (1) and the helium inlet A (6), the helium tank is logical
Piping is connected with the helium inlet A (6), and the pressure gauge is arranged in the upper cover (22) of the hermetically sealed can supervises for the moment
Survey the pressure of gas in hermetically sealed can.
3. leakage system safety testing device according to claim 1, which is characterized in that the breathable membrane is with several ventilations
The stainless steel plate in hole, the breathable membrane is horizontal and height is adjustably arranged in the test tank.
4. leakage system safety testing device according to claim 1, which is characterized in that the vacuum pumping opening is arranged in the tank
On the side wall of body, the vacuum pumping opening be equipped with quick coupling (5), the helium mass spectrometer leak detector by vacuum line (3) with
The quick coupling is connected.
5. leakage system safety testing device according to claim 1, which is characterized in that the step aperture includes from hermetically sealed can bottom
At the top of plate the first aperture recessed down and from the bottom surface of the first aperture downward through the second aperture of the sealing tank bottom, institute
The shape for stating the first aperture is adapted with the shape of the composite element (18), and second aperture and the first aperture it
Between formed and be used to support the support level of the composite element.
6. leakage system safety testing device according to claim 5, which is characterized in that the composite element setting is supporting
On step, the composite element is tightly connected by sealant (19) and the sealing tank bottom.
7. leakage system safety testing device according to claim 1, which is characterized in that the front of the tank body is equipped with for monitoring
State and each whether normal form (12) of instrument numerical value of confirmation in tank.
8. leakage system safety testing device according to claim 1, which is characterized in that be additionally provided with just on the top cover of the test tank
The valve for adjusting capacity size is equipped at the top cover handle (8) for opening the test tank, the exhaust outlet A (10).
9. leakage system safety testing device according to claim 1, which is characterized in that the test tank and hermetically sealed can are by low-carbon
Steel alloy is made.
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| WO2020224632A1 (en) * | 2019-05-08 | 2020-11-12 | 中南大学 | Method for testing leakage performance of aerospace composite material member in low temperature environment |
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