CN102765488B - Ordinary-pressure thermal test system and method of manned spacecraft - Google Patents
Ordinary-pressure thermal test system and method of manned spacecraft Download PDFInfo
- Publication number
- CN102765488B CN102765488B CN201210270054.0A CN201210270054A CN102765488B CN 102765488 B CN102765488 B CN 102765488B CN 201210270054 A CN201210270054 A CN 201210270054A CN 102765488 B CN102765488 B CN 102765488B
- Authority
- CN
- China
- Prior art keywords
- manned spacecraft
- spacecraft
- vacuum
- tested
- thermal test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses an ordinary-pressure thermal test system of a manned spacecraft, and a method for performing ordinary-pressure thermal test by the system. The system comprises an inner insulating sealing chamber for setting the manned spacecraft, and a vacuum unit and a vacuum tank which are arranged outside, wherein the vacuum tank is used for providing a vacuum environment for inner part of the manned spacecraft; a control valve for controlling the vacuum unit to operate is arranged between the vacuum tank and a sealed cabin of the spacecraft; a refrigeration dehumidifier unit and a refrigerating unit are arranged outside the insulating sealing chamber; the refrigerating unit is connected with an immediate heat exchanger in the to-be-tested manned spacecraft by a liquid loop; and the liquid loop exchanges heat with the loop in the spacecraft in the insulating sealing chamber. The invention provides a new method in the ground thermal test of the large manned spacecraft, which can check performance of the whole space station assembly, has high safety and flexibility, reduces test expenses and improves thermal test level of the spacecraft in China.
Description
Technical field
The invention belongs to the ground level heat test field of manned spacecraft, be specifically related to a kind ofly under atmospheric pressure environment, carry out the system of the system-level thermal test of manned spacecraft and utilize this system to carry out the method tested.
Background technology
The test of manned spacecraft ground level heat needs ventilated environment in the thermal management ability to single cabin and fabricate block, cabin, let out the thermal behaviors such as multiple pressure temperature maintenance carries out performance test and acceptance, connect each other closely owing to also existing between the environmental control system of manned spacecraft and heat control system simultaneously, the performance of heat control system and environmental control system permanent co-action must be examined.In addition, space station is combined by many cabins section and is formed fabricate block, and inside, each cabin exists the transitive relation of complicated heat, air and steam, simultaneously, pernicious gas and pollutants etc. also intercouple, under fabricate block state, therefore must examine the performance of space station truly, fully when ground experiment.
Existing manned spacecraft thermal test all utilizes large space environmental simulation equipment simulating space vacuum, cold darkness environment, uses infrared cage or electric heating sheets Simulated Spacecraft Orbital heat flux border in-orbit.Adopting the method for subdivision simulation for ventilating between fabricate block cabin, utilizing the ventilation thermal boundary of test blower fan simulated target aircraft during airship thermal test, during target aircraft thermal test, adopting the ventilation thermal boundary of thermal control cludy simulation airship.Existing manned spacecraft environmental control system test is carried out separately, does not examine in thermal test.Environmental control system test is carried out under atmospheric pressure environment, adopts someone method that participates in for a long time, utilizes the real metabolic process of test personnel to change cabin atmosphere composition, and then examination environmental control system performance.
Existing manned spacecraft thermal test method can not be applied to the ultra-large type manned spacecraft ground level heat test of space station rank, and concrete restriction comprises: 1) size of space station fabricate block exceedes the available space of the existing maximum space environment simulator of China; 2) vacuum thermal test costly, and the test preparatory period is long; 3) performance of heat control system and environmental control system co-ordination can not be examined simultaneously.
Therefore, in order to meet the development demand of Chinese large-sized space station, the new mode carrying out the system-level thermal test of manned spacecraft under resting in atmospheric pressure environment has engineering significance.
Summary of the invention
In order to solve the problem, the present invention proposes a kind of manned spacecraft normal pressure thermal test system, this system is examined by the performance of normal pressure thermal test to whole space station fabricate block, safety and alerting ability high, to economize on resources and not by the dimensional restriction of vacuum vessel.
In addition, present invention provides a kind of method utilizing this manned spacecraft normal pressure thermal test system to carry out normal pressure test, this normal pressure thermal test method is the key method that the large-scale manned spacecraft of development must capture and grasp.
To achieve these goals, present invention employs following technical scheme:
A kind of manned spacecraft normal pressure thermal test system, comprise inner for arranging the heat-insulating and sealing room of manned spacecraft to be tested, the vacuum reservoir that heat-insulating and sealing outdoor is provided with vacuum pump set and is communicated with vacuum pump set, vacuum reservoir is used for providing vacuum environment for manned spacecraft internal unit to be tested, the control cock controlling vacuum pump set and run is provided with between vacuum reservoir and space capsule, heat-insulating and sealing room is cube structure, six faces are made up of the heat insulation color steel of polyphenyl, polytetrafluoroethylmaterial material is adopted to support between spacecraft and ground, guarantee spacecraft and ground insulation.Heat-insulating and sealing outdoor is also provided with freeze drying unit and refrigerating unit for providing low temperature dry air for manned spacecraft to be tested, refrigerating unit is connected on the self-contained Intermediate Heat Exchanger of manned spacecraft to be tested by fluid loop, and fluid loop carries out interchange of heat with spacecraft inner looping by Intermediate Heat Exchanger in above-mentioned heat-insulating and sealing indoor.
Wherein, fluid loop is cooling media loop, and cooling media is such as water, glycol water.
Wherein, fluid loop enters the cold side input port temperature of Intermediate Heat Exchanger is between-5 DEG C ~ 15 DEG C.
Utilize said system to carry out a method for normal pressure thermal test, comprise the following steps:
1) freeze drying unit is by the space that is provided to after the cooling-dehumidifying air entered between heat-insulating and sealing room and the manned spacecraft to be tested of its inside, and the temperature of this low temperature dry air controls at 5 DEG C ~ 20 DEG C, and relative humidity controls below 15%;
2) refrigerating unit is connected on the Intermediate Heat Exchanger that carries of manned spacecraft to be tested inside by fluid loop, and controls fluid loop and enter the cold side input port temperature of Intermediate Heat Exchanger at-5 DEG C ~ 15 DEG C;
3) vacuum pump set is by vacuum reservoir for manned spacecraft internal unit to be tested provides vacuum environment, and the degree of vacuum in vacuum reservoir maintains 10
-3pa ~ 10
-2pa;
4) after setting above-mentioned condition, the thermal test of manned spacecraft normal pressure is carried out.
The invention solves the system-level thermal test of existing manned spacecraft to limit by space environment simulation equipment size, examine the problems such as insufficient, in the test of large-scale manned spacecraft ground level heat, brand-new mode is proposed, can examine the performance of whole space station fabricate block, safety and alerting ability are very high, reduce test cost, promote China's spacecraft thermal test level.
Accompanying drawing explanation
Fig. 1 is the structural representation of manned spacecraft normal pressure thermal test system of the present invention.
Fig. 2 is the diagram of circuit of manned spacecraft normal pressure thermal test method of the present invention.
Detailed description of the invention
What below introduce is detailed description of the invention as content of the present invention, further illustrates described content of the present invention below by detailed description of the invention.Certainly, describe the content that following detailed description is only example different aspect of the present invention, and should not be construed as the restriction scope of the invention.
As shown in Figure 1, manned spacecraft normal pressure thermal test system of the present invention, comprises the part compositions such as heat-insulating and sealing room, vacuum pump set, vacuum reservoir, control cock, freeze drying unit, refrigerating unit and fluid loop.Heat-insulating and sealing chamber interior is used for arranging manned spacecraft to be tested, and provides controlled local environment for manned spacecraft.Heat-insulating and sealing room is cube structure, and six faces are made up of polyurethane or the heat insulation color steel of polyphenyl.Adopt polytetrafluoroethylmaterial material to support between spacecraft and ground, guarantee spacecraft and ground insulation.The vacuum reservoir that heat-insulating and sealing outdoor is provided with vacuum pump set and is communicated with vacuum pump set, vacuum reservoir is used for the CO for manned spacecraft inside to be tested
2the environmental control equipments such as clean-up device, trace harmful gases cancellation element provide vacuum environment, meet the vacuum condition of needs during these equipment regeneration desorb.The control cock controlling vacuum pump set and run is provided with between vacuum reservoir and space capsule.Heat-insulating and sealing outdoor is also provided with freeze drying unit and refrigerating unit for providing low temperature dry air for manned spacecraft to be tested.Freeze drying unit by the space that is provided to after extraneous air cooling and dehumidifying between heat-insulating and sealing room and the manned spacecraft to be tested of its inside, for spacecraft provides the air ambient of low temperature drying.Refrigerating unit is connected on the self-contained Intermediate Heat Exchanger of manned spacecraft to be tested by fluid loop, and fluid loop carries out interchange of heat with spacecraft inner looping by Intermediate Heat Exchanger in above-mentioned heat-insulating and sealing indoor.Fluid loop is cooling media loop, and cooling media is such as water, glycol water.
In conjunction with above-mentioned hardware device, utilize test method of the present invention can carry out test according to manned spacecraft normal pressure thermal test basic procedure as shown in Figure 2.First utilize freeze drying unit, in heat-insulating and sealing indoor for manned spacecraft to be tested provides controlled air ambient, the temperature of low temperature dry air controls at 5 DEG C ~ 20 DEG C, and relative humidity controls below 15%.This environment can meet the simulation requirement of different measurement condition spacecraft thermal boundary, ensures that spacecraft low-temperature surface does not condense simultaneously.Second step opens refrigerating unit, is connected on the self-contained Intermediate Heat Exchanger of manned spacecraft to be tested by fluid loop, and fluid loop carries out interchange of heat with spacecraft inner looping by Intermediate Heat Exchanger in heat-insulating and sealing indoor.Refrigerating unit controls fluid loop and enters the cold side input port temperature of Intermediate Heat Exchanger between-5 DEG C ~ 15 DEG C, and this range of temperatures can simulate the performance of different measurement condition spacecraft low-temperature receiver.The device power-up of the 3rd step manned spacecraft inside to be tested, whole spacecraft arranges operation according to operating condition of test, until spacecraft temperature starts to test each equipment performance after stablizing.4th step opens vacuum pump set, makes the degree of vacuum in vacuum reservoir maintain 10
-3pa-10
-2pa.Work as CO
2when the environmental control equipments such as clean-up device, trace harmful gases cancellation element need to regenerate desorb, open control cock, for equipment provides required vacuum environment.Finally terminate test or enter next operating condition of test when test reaches when operating mode terminates requirement.
Test method of the present invention is applicable to single manned spacecraft cabin section, is also applicable to the fabricate block that multiple manned spacecraft cabins section is combined into.Experiment process of the present invention can arrange flexibly according to actual tests project, and the various hardware units in pilot system can be used singly or in combination for different tests project.
Although give detailed description and explanation to the specific embodiment of the present invention above; but what should indicate is; those skilled in the art can carry out various equivalence according to spirit of the present invention to above-mentioned embodiment and change and amendment; its function produced do not exceed that specification sheets and accompanying drawing contain spiritual time, all should within scope.
Claims (4)
1. a manned spacecraft normal pressure thermal test system, comprise inner for arranging the heat-insulating and sealing room of manned spacecraft to be tested, the vacuum reservoir that heat-insulating and sealing outdoor is provided with vacuum pump set and is communicated with vacuum pump set, vacuum reservoir is used for providing vacuum environment for manned spacecraft internal unit to be tested, the control cock controlling vacuum pump set and run is provided with between vacuum reservoir and space capsule, heat-insulating and sealing room is cube structure, six faces are made up of the heat insulation color steel of polyphenyl, polytetrafluoroethylmaterial material is adopted to support between manned spacecraft and ground, guarantee spacecraft and ground insulation, heat-insulating and sealing outdoor is also provided with freeze drying unit and refrigerating unit for providing low temperature dry air for manned spacecraft to be tested, refrigerating unit is connected on the self-contained Intermediate Heat Exchanger of manned spacecraft to be tested by fluid loop, fluid loop carries out interchange of heat with spacecraft inner looping by Intermediate Heat Exchanger in above-mentioned heat-insulating and sealing indoor, the cold side input port temperature that described fluid loop enters Intermediate Heat Exchanger is between-5 DEG C ~ 15 DEG C.
2. manned spacecraft normal pressure thermal test system as claimed in claim 1, wherein, described fluid loop is cooling media loop.
3. manned spacecraft normal pressure thermal test system as claimed in claim 2, wherein, described cooling media is water or glycol water.
4. utilize system described in any one of claim 1-3 to carry out a method for normal pressure thermal test, comprise the following steps:
1) freeze drying unit is by the space that is provided to after the cooling-dehumidifying air entered between heat-insulating and sealing room and the manned spacecraft to be tested of its inside, and the temperature of this low temperature dry air controls at 5 DEG C ~ 20 DEG C, and relative humidity controls below 15%;
2) refrigerating unit is connected on the Intermediate Heat Exchanger that carries of manned spacecraft to be tested inside by fluid loop, and controls fluid loop and enter the cold side input port temperature of Intermediate Heat Exchanger at-5 DEG C ~ 15 DEG C;
3) vacuum pump set is by vacuum reservoir for manned spacecraft internal unit to be tested provides vacuum environment, and the degree of vacuum in vacuum reservoir maintains 10
-3pa ~ 10
-2pa;
4) after setting above-mentioned condition, the thermal test of manned spacecraft normal pressure is carried out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210270054.0A CN102765488B (en) | 2012-08-01 | 2012-08-01 | Ordinary-pressure thermal test system and method of manned spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210270054.0A CN102765488B (en) | 2012-08-01 | 2012-08-01 | Ordinary-pressure thermal test system and method of manned spacecraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102765488A CN102765488A (en) | 2012-11-07 |
| CN102765488B true CN102765488B (en) | 2015-05-20 |
Family
ID=47093117
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210270054.0A Expired - Fee Related CN102765488B (en) | 2012-08-01 | 2012-08-01 | Ordinary-pressure thermal test system and method of manned spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102765488B (en) |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275492B (en) * | 2015-05-29 | 2018-03-27 | 北京卫星环境工程研究所 | Spacecraft thermal vacuum test distillation water collecting device |
| CN106467174B (en) * | 2015-08-10 | 2019-03-22 | 北京卫星环境工程研究所 | Large Spacecraft mechanism normal pressure temperature gradient pilot system |
| CN106484001B (en) * | 2015-08-25 | 2018-03-16 | 北京卫星环境工程研究所 | Cable high accuracy temperature control device on spacecraft thermal vacuum test star |
| CN106444946A (en) * | 2016-09-20 | 2017-02-22 | 天津航天瑞莱科技有限公司 | Constant pressure module of large constant-pressure thermal test system |
| CN108344590B (en) * | 2018-03-02 | 2019-03-08 | 北京空间技术研制试验中心 | Sealed compartment assembly manned spacecraft thermal test method |
| CN109398769B (en) * | 2018-10-24 | 2020-02-18 | 北京卫星环境工程研究所 | Normal-pressure thermal test system of large-scale walk-in manned spacecraft |
| CN109855893A (en) * | 2018-12-20 | 2019-06-07 | 上海微小卫星工程中心 | A kind of spacecraft thermal test tooling |
| CN110171583A (en) * | 2019-06-03 | 2019-08-27 | 北京卫星环境工程研究所 | Large Spacecraft normal pressure thermal environment simulation equipment gas treatment equipment |
| CN110222448A (en) * | 2019-06-14 | 2019-09-10 | 北京卫星环境工程研究所 | Spacecraft AIT process layout method with mechanical test area |
| CN110210164A (en) * | 2019-06-14 | 2019-09-06 | 北京卫星环境工程研究所 | Super-large space capsule AIT process layout method with the area Zhi Ce and electrical measurement area |
| CN110222449A (en) * | 2019-06-14 | 2019-09-10 | 北京卫星环境工程研究所 | Spacecraft AIT process layout method with leak detection area |
| CN113375400A (en) * | 2020-03-09 | 2021-09-10 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Liquid loop circulation refrigeration method for sealed cabin in vacuum environment |
| CN113928604B (en) * | 2021-10-19 | 2024-04-09 | 上海卫星装备研究所 | Device and method for testing performance of high-temperature heat shield of deep space exploration spacecraft |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102360045A (en) * | 2011-06-21 | 2012-02-22 | 北京圣涛平北科检测技术有限公司 | Thermal vacuum test method for power device |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6719564B2 (en) * | 2000-03-22 | 2004-04-13 | Chart Inc. | Space simulation chamber and method |
| JP2003276700A (en) * | 2002-03-27 | 2003-10-02 | Mitsubishi Electric Corp | Apparatus and method for thermal vacuum test of satellite |
-
2012
- 2012-08-01 CN CN201210270054.0A patent/CN102765488B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102360045A (en) * | 2011-06-21 | 2012-02-22 | 北京圣涛平北科检测技术有限公司 | Thermal vacuum test method for power device |
Non-Patent Citations (2)
| Title |
|---|
| Joe Chambliss.Thermal Control Test and Verification for the International Space Station-Approach and Status.《SAE TECHNICAL PAPER SERIES》.1998,第7页. * |
| 常压热试验技术在整星级航天器研制中的应用研究;唐伯昶;《中国空间科学技术》;20071030(第5期);第7页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102765488A (en) | 2012-11-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102765488B (en) | Ordinary-pressure thermal test system and method of manned spacecraft | |
| CN201016871Y (en) | Walking-in type three-integrated environmental test system | |
| CN111829784A (en) | Test system for fuel cell engine | |
| CN209513268U (en) | A kind of fuel battery engines test macro | |
| CN201215699Y (en) | Analogue multifunctional central air-conditioner experiment device for teaching | |
| CN110715954B (en) | Building curtain wall thermal cycle performance detection equipment | |
| CN211014091U (en) | Building curtain wall thermal cycle performance detection equipment | |
| RU2516023C2 (en) | Plant for tests of external exposures and method of its use (versions) | |
| CN102289964A (en) | Test platform for simulating environment of comprehensive protection test of underground rescue capsule | |
| CN109238340B (en) | Comprehensive environment test system for Mars detector product | |
| CN203108544U (en) | High and low temperature shock environmental test chamber | |
| CN202433449U (en) | Cold-and-hot impact test box for mixed humidity cyclic test | |
| CN202547014U (en) | Working environment monitoring and conditioning system for 10kV power distribution station | |
| CN210142170U (en) | High low temperature test machine of power lithium cell | |
| CN204759801U (en) | Real standard operation examination device of freezer | |
| CN102306033A (en) | Environmental temperature and humidity control system of integrated testing platform of controlled ecological life support system | |
| Zhou et al. | Case study of industrial-building energy performance in a cold-climate region in a developing country | |
| CN104458142A (en) | Floating air bag leak test device | |
| CN201436573U (en) | Temperature case integrated starter endurance test equipment | |
| Davis et al. | Using the “pressure pan” technique to prioritize duct sealing efforts: A study of 18 Arkansas homes | |
| CN201780205U (en) | Testing platform for engine hot box tests | |
| CN210803230U (en) | Environmental test system for high-low temperature damp-heat test of large product | |
| CN212159082U (en) | Low-pressure air-conditioning laboratory | |
| CN114659712A (en) | Method and device for testing sealing performance of membrane material | |
| JP7278797B2 (en) | Mobile humidity and temperature bath and test equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150520 Termination date: 20210801 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |