CN104458475A - Pressure-loading cold and hot impact testing method of spacecraft hot-control single-machine product - Google Patents
Pressure-loading cold and hot impact testing method of spacecraft hot-control single-machine product Download PDFInfo
- Publication number
- CN104458475A CN104458475A CN201410738223.8A CN201410738223A CN104458475A CN 104458475 A CN104458475 A CN 104458475A CN 201410738223 A CN201410738223 A CN 201410738223A CN 104458475 A CN104458475 A CN 104458475A
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- Prior art keywords
- control unit
- temperature
- pressure
- unit product
- hot
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Links
- 238000000034 method Methods 0.000 title abstract description 12
- 238000009863 impact test Methods 0.000 title abstract 3
- 238000012360 testing method Methods 0.000 claims abstract description 41
- 230000035939 shock Effects 0.000 claims description 35
- 238000010792 warming Methods 0.000 claims description 8
- 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
- 230000001351 cycling effect Effects 0.000 claims description 5
- 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
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 abstract description 14
- 229910021529 ammonia Inorganic materials 0.000 abstract description 7
- 239000011261 inert gas Substances 0.000 abstract description 3
- 238000007789 sealing Methods 0.000 abstract 1
- 238000003466 welding Methods 0.000 abstract 1
- 239000000047 product Substances 0.000 description 20
- 230000006835 compression Effects 0.000 description 8
- 238000007906 compression Methods 0.000 description 8
- 230000007613 environmental effect Effects 0.000 description 4
- 229920006395 saturated elastomer Polymers 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000001154 acute effect Effects 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
- 238000005516 engineering process Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000010998 test method Methods 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
- 238000010586 diagram Methods 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
- 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
- 230000000630 rising effect Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Landscapes
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention provides a pressure-loading cold and hot impact testing method of a spacecraft hot-control single-machine product. The pressure-loading cold and hot impact testing method comprises the following steps: converting filling pressure; feeding inert gas; carrying out sealing welding on a feeding opening; and checking feeding quality, carrying out a temperature cycle test, and evaluating a testing effect after the test. The hot-control single-machine product is internally filled with the inert gas so that the pressure in the hot-control single-machine product is changed along the change of a testing temperature, and the requirements of carrying out temperature impact and pressure impact at the same time are realized. The problems that a hot-control system which takes high-purity ammonia as a two-phase working medium is used for simulating an environment testing project of violent changes of the space environment, and carrying out the temperature impact and the pressure impact at the same time in actual space application are solved; and the model product testing perfectly meets a working condition and the testability of the product is improved.
Description
Technical field
The present invention is used for spacecraft thermal control unit product thermal shock test, belongs to spacecraft environmental test technical field.
Background technology
Two-phase fluid loop is novel spacecraft Evolution of Thermal Control Technique, is one of minority effective measures solving military aerospace device high heat flow density device heat dissipation problem.In the application of the space of reality, adopt high-purity ammon as two-phase working substance, due to the acute variation of space environment, there is low temperature liquid working medium and enter the situation that high-temperature component heats up rapidly, gasifies.Because working medium saturated vapor pressure difference under different temperatures causes circuit assemblies need experience temperature, compression shock change.
For this features, need the cold shock testing under year pressure condition is carried out on ground, simultaneously simulated pressure impact variation, to verify the adaptability of product space environment.At present, there is no thermal shock and compression shock and test methods and measures simultaneously, in the past in production, for the simulation realizing this operating mode need carry out filling of liquefied ammonia working medium by product actual working state, because liquefied ammonia has toxicity, in temperature and compression shock process, will working medium be caused to reveal as gone wrong, there is the hidden danger of security in process of the test, therefore needs to provide effective test method.
Summary of the invention
The technical matters that the present invention solves is: overcome the deficiencies in the prior art, provide a kind of spacecraft thermal control unit product and carry pressure cold shock testing method, solve in the application of the space of reality, adopt high-purity ammon as the heat control system of two-phase working substance, the environmental testing project of the acute variation of space environmental simulation, the problem that temperature shock, compression shock carry out simultaneously, ensure that type product test meets with working condition 100%, improves the testability of product.
Technical scheme of the present invention is: a kind of spacecraft thermal control unit product carries pressure cold shock testing method, and step is as follows:
1) test in forward direction thermal control unit to be measured product and be filled with helium, described in be filled with helium pressure be
t in formula
0for ambient temperature, unit is K; P
0for required charge pressure, unit is Pa; T
1for thermal shock test maximum temperature, unit is K; P
1for thermal shock test top 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, prepare to carry out cold shock testing;
3) from room temperature, treat calorimetric control unit product and carry out warming temperature;
4) when thermal control unit product temperature to be measured reaches T
1time, keep Current Temperatures more than 0.5 hour;
5) after high temperature has kept, from baking box, take out thermal control unit product to be measured, and put into mixture of ice and water, until thermal control unit product temperature to be measured is down to 0 °, and keep Current Temperatures more than 0.5 hour;
6) after low temperature has kept, thermal control unit product to be measured is put into baking box, treat calorimetric control unit product and carry out warming temperature, namely complete a complete heat shock cycling;
7) step 3 is repeated)-step 6), until after heat shock cycling number of times meets task requirement of experiment, thermal control unit product to be measured is taken out in chamber, and carries out leak rate detection.
Described T
0be chosen for 20 °.
Step 3) in treat the rate of heat addition that calorimetric control unit product carries out warming temperature be 1.5 DEG C/s ~ 4 DEG C/s.
Step 6) in treat the rate of heat addition that calorimetric control unit product carries out warming temperature be 1.5 DEG C/s ~ 4 DEG C/s.
The present invention compared with prior art tool has the following advantages:.The present invention adopts the method filling inert gas, Simulated Spacecraft thermal control unit interiors of products fills the work characteristics of ammonia working medium, evade and filled ammonia working medium when carrying out temperature shock test, pipe breakage, the risk that toxicity working medium is revealed, meet the testing requirements of temperature shock with compression shock simultaneously, solve the type product test difficult problem that temperature shock, compression shock in the past carry out respectively.Can realize the internal pressure conditions consistent with compression shock top pressure operating mode by the calculating filling gaseous tension, because charge pressure is controlled, the method can realize the impulse test simulation of different operating pressure condition.
Accompanying drawing explanation
Fig. 1 is process flow diagram of the present invention.
Embodiment
For two-phase fluid loop temperature, compression shock test, process of the test is as follows:
1. according to caloric impact temperature T
1=265 DEG C, surge pressure and 265 DEG C of ammonia saturated vapor pressures correspond to P
1=5MPa, ambient temperature T
0=20 DEG C, calculating charge pressure is 2.72MPa;
2. tackling evaporator assemblies and be filled with the helium suitable with ammonia saturated vapour pressure when 265 DEG C, i.e. 2.72Mpa, whether revealing for weighing thermal shock test process weld seam.
3. the test assembly through acceptance inspeciton is put into high-temperature baking case;
4., from room temperature (Normal Environmental Temperature), the temperature of test assembly heats up by Cooling rate requirement, and it is 1.5 DEG C that Cooling rate can choose the rate of heat addition/s ~ 4 DEG C/s;
5. after temperature reaches the temperature permissible variation lower limit of test high temperature, start temperature and keep, temperature continues rising 2 DEG C and keeps stable in temperature permissible variation, and temperature hold-time is not less than 0.5h;
6. after high temperature has kept, from baking box, take out assembly, put into rapidly mixture of ice and water (quantity of ice obtains and is enough not more than 2 DEG C for being cooled to by testpieces).Process of the test uses liquid nitrogen and refrigeration for refrigerator.
7. be down to the permissible variation higher limit of the cryogenic temperature of testing requirements at assembly temperature, start temperature and keep, temperature hold-time is not less than 0.5h;
8., after low temperature has kept, assembly to be put into baking oven and heats up, it is 1.5 DEG C that heating rate can choose the rate of heat addition/s ~ 4 DEG C/s.
9. the temperature of assembly rises to room temperature and namely completes a complete heat shock cycling.
10., until cycle index meets testing requirements, afterwards assembly is taken out in chamber.
After 11. thermal shock tests complete, evaporator bank is carried out to the inspection of outward appearance, installation dimension and leak rate.
The content be not described in detail in instructions of the present invention belongs to professional and technical personnel in the field's known technology.
Claims (4)
1. spacecraft thermal control unit product carries a pressure cold shock testing method, it is characterized in that step is as follows:
1) test in forward direction thermal control unit to be measured product and be filled with helium, described in be filled with helium pressure be
t in formula
0for ambient temperature, unit is K; P
0for required charge pressure, unit is Pa; T
1for thermal shock test maximum temperature, unit is K; P
1for thermal shock test top 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, prepare to carry out cold shock testing;
3) from room temperature, treat calorimetric control unit product and carry out warming temperature;
4) when thermal control unit product temperature to be measured reaches T
1time, keep Current Temperatures more than 0.5 hour;
5) after high temperature has kept, from baking box, take out thermal control unit product to be measured, and put into mixture of ice and water, until thermal control unit product temperature to be measured is down to 0 °, and keep Current Temperatures more than 0.5 hour;
6) after low temperature has kept, thermal control unit product to be measured is put into baking box, treat calorimetric control unit product and carry out warming temperature, namely complete a complete heat shock cycling;
7) step 3 is repeated)-step 6), until after heat shock cycling number of times meets task requirement of experiment, thermal control unit product to be measured is taken out in chamber, and carries out leak rate detection.
2. a kind of spacecraft thermal control unit product according to claim 1 carries pressure cold shock testing method, it is characterized in that: described T
0be chosen for 20 °.
3. a kind of spacecraft thermal control unit product according to claim 1 carries pressure cold shock testing method, it is characterized in that: step 3) in treat the rate of heat addition that calorimetric control unit product carries out warming temperature 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, it is characterized in that: step 6) in treat the rate of heat addition that calorimetric control unit product carries out warming temperature be 1.5 DEG C/s ~ 4 DEG C/s.
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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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|---|---|---|---|
| CN201410738223.8A CN104458475B (en) | 2014-12-05 | 2014-12-05 | A kind of spacecraft thermal control unit product carries pressure cold shock testing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104458475A true CN104458475A (en) | 2015-03-25 |
| CN104458475B 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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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106908338A (en) * | 2017-03-14 | 2017-06-30 | 杭州电子科技大学 | The impact test platform of material is clashed into a kind of HTHP more |
| CN108469393A (en) * | 2018-02-02 | 2018-08-31 | 中山市积目科技有限公司 | A kind of cold shock testing equipment |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100031693A1 (en) * | 2006-11-30 | 2010-02-11 | Ulvac, Inc. | Refridgerating 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 |
| CN103318427B (en) * | 2013-06-25 | 2016-03-30 | 上海宇航系统工程研究所 | A kind of space environment simulation test system |
-
2014
- 2014-12-05 CN CN201410738223.8A patent/CN104458475B/en not_active Expired - Fee Related
Non-Patent Citations (2)
| Title |
|---|
| 苗建印 等: "航天器热传输技术研究进展", 《航天器工程》 * |
| 苗建印 等: "高效深低温热收集与热传输技术", 《航天器工程》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106908338A (en) * | 2017-03-14 | 2017-06-30 | 杭州电子科技大学 | The impact test platform of material is clashed into a kind of HTHP more |
| CN108469393A (en) * | 2018-02-02 | 2018-08-31 | 中山市积目科技有限公司 | A kind of cold shock testing equipment |
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| Publication number | Publication date |
|---|---|
| CN104458475B (en) | 2017-03-15 |
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Granted publication date: 20170315 |