CN104458475B - A kind of spacecraft thermal control unit product carries pressure cold shock testing method - Google Patents
A kind of spacecraft thermal control unit product carries pressure cold shock testing method Download PDFInfo
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- CN104458475B CN104458475B CN201410738223.8A CN201410738223A CN104458475B CN 104458475 B CN104458475 B CN 104458475B CN 201410738223 A CN201410738223 A CN 201410738223A CN 104458475 B CN104458475 B CN 104458475B
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- control unit
- temperature
- thermal control
- unit product
- shock
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- 238000012360 testing method Methods 0.000 title claims abstract description 42
- 230000035939 shock Effects 0.000 title claims abstract description 40
- 230000001351 cycling effect Effects 0.000 claims abstract description 6
- 239000001307 helium Substances 0.000 claims description 7
- 229910052734 helium Inorganic materials 0.000 claims description 7
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 7
- 238000010792 warming Methods 0.000 claims description 7
- 239000000203 mixture Substances 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 2
- 238000002474 experimental method Methods 0.000 claims description 2
- 230000006835 compression Effects 0.000 abstract description 10
- 238000007906 compression Methods 0.000 abstract description 10
- 238000000034 method Methods 0.000 abstract description 9
- 230000007613 environmental effect Effects 0.000 abstract description 6
- 238000004088 simulation Methods 0.000 abstract description 5
- 230000001154 acute effect Effects 0.000 abstract description 3
- 229910052756 noble gas Inorganic materials 0.000 abstract description 3
- 150000002835 noble gases Chemical class 0.000 abstract description 3
- 239000000126 substance Substances 0.000 abstract description 3
- 238000006243 chemical reaction Methods 0.000 abstract 1
- 230000000694 effects Effects 0.000 abstract 1
- 238000011156 evaluation Methods 0.000 abstract 1
- 238000003466 welding Methods 0.000 abstract 1
- 239000000047 product Substances 0.000 description 20
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 12
- 229910021529 ammonia Inorganic materials 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 3
- 229920006395 saturated elastomer Polymers 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000009863 impact test Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 230000001988 toxicity Effects 0.000 description 2
- 231100000419 toxicity Toxicity 0.000 description 2
- 239000006227 byproduct Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000006902 nitrogenation reaction Methods 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 239000006200 vaporizer Substances 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Landscapes
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
A kind of spacecraft thermal control unit product of the present invention carries pressure cold shock testing method.Fill including charge pressure conversion, noble gases, fill a mouthful seal welding, fill test effect evaluation procedure after quality examination, temperature cycling test and test.As thermal control unit interiors of products fills noble gases, therefore with the change of test temperature, thermal control unit interiors of products pressure also changes therewith, it is achieved that the requirement that temperature shock, compression shock are carried out simultaneously.Solve in actual space application, using high-purity ammon as two-phase working substance heat control system, the environmental testing project of the acute variation of space environmental simulation, the problem that temperature shock, compression shock are carried out simultaneously, ensure that type product test is met with working condition 100%, improve the testability of product.
Description
Technical field
The present invention belongs to spacecraft environmental test technology neck for spacecraft thermal control unit product thermal shock test
Domain.
Background technology
Two-phase fluid loop is new spacecraft Evolution of Thermal Control Technique, is to solve the high heat flow density device of military aerospace device
One of minority effective measures of heat dissipation problem.In actual space application, using high-purity ammon as two-phase working substance, due to space
, there is low temperature liquid working medium and enter the situation that high-temperature component rapidly heats up, gasifies in the acute variation of environment.Under due to different temperatures
Working medium saturated vapor pressure difference causes circuit assemblies experience temperature, compression shock change.
For this features, need to carry out the cold shock testing under load pressure condition on ground, while simulated pressure
Impact variation, to verify the adaptability of product space environment.At present, there is no thermal shock and compression shock to test at the same method
And measure, in conventional production, it is that the simulation for realizing the operating mode need to carry out filling for liquefied ammonia working medium by product actual working state
Dress, as liquefied ammonia has toxicity, during temperature and compression shock, such as going wrong to cause working medium to be revealed, process of the test
There is the hidden danger of safety, it is therefore desirable to provide effective test method.
Content of the invention
Present invention solves the technical problem that being：Overcome the deficiencies in the prior art, there is provided a kind of spacecraft thermal control unit is produced
Product carry pressure cold shock testing method, solve in actual space application, using high-purity ammon as two-phase working substance thermal control
System, the environmental testing project of the acute variation of space environmental simulation, the problem that temperature shock, compression shock are carried out simultaneously are protected
Demonstrate,prove type product test to meet with working condition 100%, improve the testability of product.
The technical scheme is that：A kind of spacecraft thermal control unit product carries pressure cold shock testing method, and step is such as
Under：
1) be filled with helium into thermal control unit product to be measured before testing, described be filled with helium pressure beFormula
Middle T0For ambient temperature, unit is K；P0Charge pressure for needed for, unit are Pa；T1For thermal shock test maximum temperature, list
Position is K；P1For thermal shock test maximum pressure, unit is Pa；
2) the thermal control unit product to be measured of helium of substituting the bad for the good is put into high-temperature baking case, is ready for cold shock testing；
3) from the beginning of room temperature, treating calorimetric control unit product carries out warming temperature；
4) when thermal control unit product temperature to be measured reaches T1When, keep Current Temperatures more than 0.5 hour；
5), after the completion of high temperature keeps, thermal control unit product to be measured is taken out from baking box, and is put in mixture of ice and water, directly
0 ° is down to thermal control unit product temperature to be measured, and keeps Current Temperatures more than 0.5 hour；
6), after the completion of low temperature keeps, thermal control unit product to be measured is put in baking box, calorimetric control unit product is treated and is entered
Row warming temperature, that is, complete a complete heat shock cycling；
7) repeat step 3)-step 6), until after heat shock cycling number of times meets task requirement of experiment, by thermal control list to be measured
Machine product is taken out from proof box, and carries out leak rate detection.
The T0It is chosen for 20 °.
Step 3) in treat calorimetric control unit product carry out warming temperature the rate of heat addition be 1.5 DEG C/s～4 DEG C/s.
Step 6) in treat calorimetric control unit product carry out warming temperature the rate of heat addition be 1.5 DEG C/s～4 DEG C/s.
The present invention is had the advantage that compared with prior art：.Method of the present invention using noble gases are filled, simulation boat
Its device thermal control unit interiors of products fills the work characteristics of ammonia working medium, has evaded when filling ammonia working medium and carrying out temperature shock test,
Pipe breakage, the risk that toxicity working medium is revealed, while meet test requirements document of the temperature shock with compression shock, solve with
Toward the type product test difficult problem that temperature shock, compression shock are carried out respectively.Can be realized by filling the calculating of gas pressure
The internal pressure conditions consistent with compression shock maximum pressure operating mode, as charge pressure is controllable, the method can realize difference
The impact test simulation of operating pressure conditions.
Description of the drawings
Fig. 1 is flow chart of the present invention.
Specific embodiment
By taking two-phase fluid loop temperature, compression shock test as an example, process of the test is as follows：
1. according to caloric impact temperature T1=265 DEG C, surge corresponds to P with 265 DEG C of ammonia saturated vapor pressures1=5MPa, week
Enclose ambient temperature T0=20 DEG C, calculating charge pressure is 2.72MPa；
2. reply evaporator assemblies are filled with the helium suitable with ammonia saturated vapour pressure when 265 DEG C, i.e. 2.72Mpa, for weighing
Whether calorimetric impact test process weld seam is revealed.
3. the test assembly through acceptance inspeciton is put into high-temperature baking case；
4., from the beginning of room temperature (Normal Environmental Temperature), the temperature of test assembly heats up by Cooling rate requirement, Cooling rate
The rate of heat addition can be chosen for 1.5 DEG C/s～4 DEG C/s；
5. after temperature reaches the temperature tolerance lower limit of test high temperature, started temperature keeps, and temperature continues to raise 2 DEG C
And keeping stable in temperature tolerance, temperature hold-time is not less than 0.5h；
6., after the completion of high temperature keeps, component is taken out from baking box, be put in mixture of ice and water rapidly that (quantity of ice obtains foot
It is enough in and testpieces is cooled to no more than 2 DEG C).Process of the test is using liquid nitrogen and refrigeration for refrigerator.
7. the tolerance higher limit of the cryogenic temperature of test requirements document is down in assembly temperature, and started temperature keeps, temperature
Retention time is not less than 0.5h；
8. after the completion of low temperature keeps, component is put in baking oven and is heated up, heating rate can choose the rate of heat addition for 1.5 DEG C/s
～4 DEG C/s.
9. the temperature of component is warmed to room temperature and completes a complete heat shock cycling.
10., until cycle-index meets test requirements document, afterwards component is taken out from proof box.
After the completion of 11. thermal shock tests, outward appearance, installation dimension and leak rate are carried out to vaporizer group inspection.
The content not being described in detail in description of the invention belongs to professional and technical personnel in the field's known technology.
Claims (4)
1. a kind of spacecraft thermal control unit product carries pressure cold shock testing method, it is characterised in that step is as follows：
1) be filled with helium into thermal control unit product to be measured before testing, described be filled with helium pressure beT in formula0For
Ambient temperature, unit are K；P0Charge pressure for needed for, unit are Pa；T1For thermal shock test maximum temperature, unit is K；
P1For thermal shock test maximum pressure, unit is Pa；
2) the thermal control unit product to be measured of helium of substituting the bad for the good is put into high-temperature baking case, is ready for cold shock testing；
3) from the beginning of room temperature, treating calorimetric control unit product carries out warming temperature；
4) when thermal control unit product temperature to be measured reaches T1When, keep Current Temperatures more than 0.5 hour；
5) after the completion of high temperature keeps, thermal control unit product to be measured is taken out from baking box, and is put in mixture of ice and water, until treating
Calorimetric control unit product temperature is down to 0 DEG C, and keeps Current Temperatures more than 0.5 hour；
6), after the completion of low temperature keeps, thermal control unit product to be measured is put in baking box, calorimetric control unit product is treated and is risen
Temperature operation, that is, complete a complete heat shock cycling；
7) repeat step 3)-step 6), until after heat shock cycling number of times meets task requirement of experiment, thermal control unit to be measured is produced
Product are taken out from proof box, and carry out leak rate detection.
2. a kind of spacecraft thermal control unit product according to claim 1 carries pressure cold shock testing method, and its feature exists
In：The T0It is chosen for 293K.
3. a kind of spacecraft thermal control unit product according to claim 1 carries pressure cold shock testing method, and its feature exists
In：Step 3) in treat calorimetric control unit product carry out warming temperature the rate of heat addition be 1.5 DEG C/s～4 DEG C/s.
4. a kind of spacecraft thermal control unit product according to claim 1 carries pressure cold shock testing method, and its feature exists
In：Step 6) in treat calorimetric control unit product carry out warming temperature the rate of heat addition be 1.5 DEG C/s～4 DEG C/s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410738223.8A CN104458475B (en) | 2014-12-05 | 2014-12-05 | A kind of spacecraft thermal control unit product carries pressure cold shock testing method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410738223.8A CN104458475B (en) | 2014-12-05 | 2014-12-05 | A kind of spacecraft thermal control unit product carries pressure cold shock testing method |
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| Publication Number | Publication Date |
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| CN104458475A CN104458475A (en) | 2015-03-25 |
| CN104458475B true CN104458475B (en) | 2017-03-15 |
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| CN201410738223.8A Expired - Fee Related CN104458475B (en) | 2014-12-05 | 2014-12-05 | A kind of spacecraft thermal control unit product carries pressure cold shock testing method |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106908338B (en) * | 2017-03-14 | 2019-04-23 | 杭州电子科技大学 | A kind of high temperature and pressure hits the impact test platform of material more |
| CN108469393B (en) * | 2018-02-02 | 2021-04-06 | 中山市积目科技有限公司 | Cold and hot shock test equipment |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201107192Y (en) * | 2007-10-31 | 2008-08-27 | 辉煌水暖集团有限公司 | Product cold and heat cycle test apparatus |
| EP2090850A1 (en) * | 2006-11-30 | 2009-08-19 | Ulvac, Inc. | Refrigerating machine |
| CN201348569Y (en) * | 2008-12-29 | 2009-11-18 | 北京卫星环境工程研究所 | Space ship environment simulation test device utilizing mixed work substance refrigerating technology |
| CN103318427A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航系统工程研究所 | Space environment simulation testing system |
-
2014
- 2014-12-05 CN CN201410738223.8A patent/CN104458475B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2090850A1 (en) * | 2006-11-30 | 2009-08-19 | Ulvac, Inc. | Refrigerating machine |
| CN201107192Y (en) * | 2007-10-31 | 2008-08-27 | 辉煌水暖集团有限公司 | Product cold and heat cycle test apparatus |
| CN201348569Y (en) * | 2008-12-29 | 2009-11-18 | 北京卫星环境工程研究所 | Space ship environment simulation test device utilizing mixed work substance refrigerating technology |
| CN103318427A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航系统工程研究所 | Space environment simulation testing system |
Non-Patent Citations (2)
| Title |
|---|
| 航天器热传输技术研究进展;苗建印 等;《航天器工程》;20100331;第19卷(第2期);第106－112页 * |
| 高效深低温热收集与热传输技术;苗建印 等;《航天器工程》;20050930;第14卷(第3期);第40－45页 * |
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| CN104458475A (en) | 2015-03-25 |
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Granted publication date: 20170315 |