CN107539502A - Temperature-adjustment pressure-adjustment device for spacecraft environment experiment - Google Patents
Temperature-adjustment pressure-adjustment device for spacecraft environment experiment Download PDFInfo
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- CN107539502A CN107539502A CN201610565177.5A CN201610565177A CN107539502A CN 107539502 A CN107539502 A CN 107539502A CN 201610565177 A CN201610565177 A CN 201610565177A CN 107539502 A CN107539502 A CN 107539502A
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- vacuum tank
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Abstract
The invention discloses a kind of temperature-adjustment pressure-adjustment device for spacecraft environment experiment, including vacuum tank, container gate, heat sink, switch board, refrigeration machine etc.；It is heat sink to be placed on inside vacuum tank, it is heat sink to be connected with refrigeration machine by refrigeration piping, refrigeration valve is connected among refrigeration piping, heat exchanger passes through heat exchanger tube and refrigeration piping UNICOM, connected between vacuum tank and vavuum pump by vacuum pipe, vacuum valve is connected among vacuum pipe, tonifying Qi pipeline is connected with vacuum tank, gas flow controller is installed on tonifying Qi pipeline, gas in tonifying Qi pipeline is introduced into heat exchanger before entering vacuum tank and exchanged heat, nitrogen pipeline is arranged in parallel with air pipe line, source nitrogen is connected by nitrogen pipeline with tonifying Qi pipeline, air-source is connected by air duct with tonifying Qi pipeline, air dryer is connected among air duct, switch board passes through controlling cable and refrigeration machine, refrigeration valve, vavuum pump, vacuum valve, gas flow controller connects.
Description
Technical field
The invention belongs to environment test device technical field, it particularly relates to which a kind of internal pressure and temperature can essences
The experimental rig really automatically adjusted, environmental test is carried out for spacecraft.
Background technology
During spacecraft rises to high-altitude by ground, pressure and temperature is changing always in residing environment.In order to verify
Environmental suitability and the reliability of spacecraft are, it is necessary to which special temperature-adjustment pressure-adjustment environment test device carries out environmental test.Experiment
Apparatus main body structure is vacuum tank, heat sink, switch board, refrigeration machine, refrigeration piping, heat exchanger, vavuum pump, vacuum pipe, true
Empty valve, gas flow controller, source of the gas etc..It is existing for spacecraft environment experiment temperature-adjustment pressure-adjustment experimental rig be all by
Temperature adjustment and pressure regulation are separately tested, and device is typically all atmospheric high-low temperature equipment or low pressure equipment, and pressure and temperature can not be real
Existing precise synchronization control and regulation, such as Fifth Academy of Aerospace Industry's general assembly and environmental project portion high-low temperature test chamber are all this modes.
With increasing, it is necessary to which vacuum tank internal temperature and pressure carry out while regulation and essence for spacecraft reliability requirement
Really control.Because pressure and temperature has coupling effect, in order to avoid the drastically saltus step of temperature and pressure, reach temperature and pressure
Accurate control, it is desirable to which supplement enters inside temperature and the container of vacuum tank internal gas when vacuum tank Stress control
Existing gas temperature is consistent.Further, since surface can not have condensate during spacecraft testing, therefore it is required that experimental rig
In worst cold case, the gas added to inside vacuum tank is dry air or nitrogen.
The content of the invention
In order to solve the above problems, the present invention is intended to provide a kind of temperature-adjustment pressure-adjustment device for spacecraft environment experiment,
The device can realize automatically adjusting and accurately controlling for vacuum tank internal temperature and pressure, and it is true effectively to simulate spacecraft
Flight environment of vehicle, realize that the pressure and temp under high and low temperature environment accurately controls, preferably meet spacecraft environment test requirements document.
Present invention employs following technical scheme：
The present invention be used for spacecraft environment experiment temperature-adjustment pressure-adjustment device, including vacuum tank, container gate, it is heat sink,
Switch board, refrigeration machine, refrigeration piping, refrigeration valve, heat exchanger, heat exchanger tube, vavuum pump, vacuum pipe, vacuum valve, gas
Body flow controller, tonifying Qi pipeline, source nitrogen, nitrogen pipeline, air-source, air dryer, air duct；The appearance of vacuum tank
Device gate is opened, heat sink to be placed on inside vacuum tank, heat sink to be connected with refrigeration machine by refrigeration piping, is connected among refrigeration piping
Refrigeration valve is connected to, heat exchanger passes through vacuum by heat exchanger tube and refrigeration piping UNICOM between vacuum tank and vavuum pump
Pipeline connects, and is connected with vacuum valve among vacuum pipe, tonifying Qi pipeline is connected with vacuum tank, and gas is provided with tonifying Qi pipeline
Body flow controller, the gas in tonifying Qi pipeline are introduced into heat exchanger before entering vacuum tank and exchanged heat, nitrogen pipeline with
Air pipe line is arranged in parallel, and source nitrogen is connected by nitrogen pipeline with tonifying Qi pipeline, and air-source passes through air duct and blowdown pipe
Road connects, and is connected with air dryer among air duct, switch board passes through controlling cable and refrigeration machine, refrigeration valve, vacuum
Pump, vacuum valve, gas flow controller connection.
Wherein, refrigeration machine controls the temperature of temperature control medium in refrigeration piping, so as to adjust heat sink temperature.It is heat sink to be installed on very
Inside empty container, by conduction of heat, vacuum tank interior environment temperature and heat sink temperature synchronous adjustment.
Wherein, vavuum pump has fixed gas pumping speed, while it is evacuated to vacuum tank with fixing pumping speed,
The dry air or nitrogen flow that gas flow-control supplement enters inside vacuum tank, so as to realize in vacuum tank
The accurate control of portion's pressure.
Wherein, the gas that supplement enters inside vacuum tank can switch in two kinds of gases of dry air and nitrogen, energy
Enough meet different demands of the different tests task to gas, and can ensure not tie under worst cold case inside vacuum tank
Dew.
Wherein, heat exchanger is connected with refrigeration piping, the gas entered by gas flow controller supplement inside vacuum tank
Body is first exchanged heat with heat exchanger before vacuum tank is entered, reach gas temperature that supplement enters inside vacuum tank with very
Existing gas temperature is consistent inside empty container, effectively reduces the coupling effect between pressure and temperature, avoids true
The rapid fluctuation of empty container internal pressure and temperature.
Wherein, refrigeration machine, vavuum pump, valve, gas flow controller can be automatically controlled by switch board, from
And realize automatically adjusting for vacuum tank internal pressure temperature.
Compared with existing experimental rig, the temperature-adjustment pressure-adjustment device for being used for spacecraft environment experiment of the invention can be realized
Vacuum tank internal temperature and pressure are automatically adjusted, and pressure and temp can be controlled accurately under high and low temperature environment, effectively simulation
Spacecraft live flying environment, preferably meets spacecraft environment test requirements document.
Brief description of the drawings
Fig. 1 is the temperature-adjustment pressure-adjustment structure drawing of device for being used for spacecraft environment experiment of the present invention.
In figure, 1- containers gate, 2- vacuum tanks, 3- is heat sink, 4- switch boards, 5- refrigeration pipings, 6- vacuum pipes, and 7- is true
Empty valve, 8- gas flow controllers, 9- refrigeration valves, 10- tonifying Qi pipelines, 11- vavuum pumps, 12- heat exchangers, 13- heat exchangers
Pipeline, 14- nitrogen pipelines, 15- air ducts, 16- air dryers, 17- source nitrogens, 18- air-sources, 19- refrigeration machines.
Embodiment
Introduced below is the embodiment as present invention, below by embodiment to the present invention
Content is made further to illustrate.Certainly, it is only the content of example different aspect of the invention to describe following detailed description, and
It should not be construed as limiting the invention scope.
As shown in figure 1, the temperature-adjustment pressure-adjustment device for being used for spacecraft environment experiment of the present invention, including vacuum tank 2, container
Gate 1, heat sink 3, switch board 4, refrigeration machine 19, refrigeration piping 5, refrigeration valve 9, heat exchanger 12, heat exchanger tube 13, vavuum pump
11st, vacuum pipe 6, vacuum valve 7, gas flow controller 8, tonifying Qi pipeline 10, source nitrogen 17, nitrogen pipeline 14, air are done
Dry device 16, air duct 15.Container gate 1 is opened, and heat sink 3 are placed on inside vacuum tank 2, and heat sink 3 pass through with refrigeration machine 19
Refrigeration piping 5 is connected, and refrigeration valve 9 is connected among refrigeration piping 5, and heat exchanger 12 passes through heat exchanger tube 13 and refrigeration piping
5 UNICOMs, connected between vacuum tank 2 and vavuum pump 11 by vacuum pipe 6, vacuum valve 7 be connected among vacuum pipe 6,
Tonifying Qi pipeline 10 is connected with vacuum tank 2, is provided with gas flow controller 8 on tonifying Qi pipeline 10, the gas in tonifying Qi pipeline 10
Body is introduced into heat exchanger 12 before entering vacuum tank 2 and exchanged heat, and source nitrogen 17 passes through nitrogen pipeline 14 and tonifying Qi pipeline 10
Connection, air-source 18 are connected by air duct 15 with tonifying Qi pipeline 10, and air dryer 16 is connected among air duct 15,
Switch board 4 is connected by controlling cable and refrigeration machine 19, refrigeration valve 9, vavuum pump 11, vacuum valve 7, gas flow controller 8
Connect.
Wherein, refrigeration machine controls the temperature of temperature control medium in refrigeration piping, so as to adjust heat sink temperature.It is heat sink to be installed on very
Inside empty container, by conduction of heat, vacuum tank interior environment temperature and heat sink temperature synchronous adjustment.
Wherein, vavuum pump has fixed gas pumping speed, while it is evacuated to vacuum tank with fixing pumping speed,
The dry air or nitrogen flow that gas flow-control supplement enters inside vacuum tank, so as to realize in vacuum tank
The accurate control of portion's pressure.
Wherein, the gas that supplement enters inside vacuum tank can switch in two kinds of gases of dry air and nitrogen, energy
Enough meet different demands of the different tests task to gas, and can ensure not tie under worst cold case inside vacuum tank
Dew.
Wherein, heat exchanger is connected with refrigeration piping, the gas entered by gas flow controller supplement inside vacuum tank
Body is first exchanged heat with heat exchanger before vacuum tank is entered, reach gas temperature that supplement enters inside vacuum tank with very
Existing gas temperature is consistent inside empty container, effectively reduces the coupling effect between pressure and temperature, avoids true
The rapid fluctuation of empty container internal pressure and temperature.
Wherein, refrigeration machine, vavuum pump, valve, gas flow controller can be automatically controlled by switch board, from
And realize automatically adjusting for vacuum tank internal pressure temperature.
Compared with existing experimental rig, temperature-adjustment pressure-adjustment device of the invention can realize vacuum tank internal temperature and pressure
Power is automatically adjusted, and pressure can be controlled accurately under high and low temperature environment, effectively simulates spacecraft live flying environment, preferably
Meet spacecraft environment test requirements document.
Although giving detailed description and explanation to the embodiment of the present invention above, it should be noted that
We can carry out various equivalent changes and modification to above-mentioned embodiment according to the conception of the present invention, and its caused function is made
, all should be within protection scope of the present invention during with the spirit still covered without departing from specification and accompanying drawing.
Claims (7)
1. for the temperature-adjustment pressure-adjustment device of spacecraft environment experiment, including vacuum tank, container gate, heat sink, switch board, refrigeration
Machine, refrigeration piping, refrigeration valve, heat exchanger, heat exchanger tube, vavuum pump, vacuum pipe, vacuum valve, gas flow control
Device, tonifying Qi pipeline, source nitrogen, nitrogen pipeline, air-source, air dryer, air duct；Container gate is opened, heat sink placement
It is heat sink to be connected with refrigeration machine by refrigeration piping inside vacuum tank, refrigeration valve, heat exchanger are connected among refrigeration piping
By heat exchanger tube and refrigeration piping UNICOM, connected between vacuum tank and vavuum pump by vacuum pipe, in vacuum pipe
Between be connected with vacuum valve, tonifying Qi pipeline is connected with vacuum tank, and gas flow controller, blowdown pipe are provided with tonifying Qi pipeline
Gas in road is introduced into heat exchanger before entering vacuum tank and exchanged heat, and nitrogen pipeline is arranged in parallel with air pipe line, nitrogen
Source of the gas is connected by nitrogen pipeline with tonifying Qi pipeline, and air-source is connected by air duct with tonifying Qi pipeline, among air duct
Air dryer is connected with, switch board passes through controlling cable and refrigeration machine, refrigeration valve, vavuum pump, vacuum valve, gas flow
Controller connects.
2. temperature-adjustment pressure-adjustment device as claimed in claim 1, wherein, the temperature of temperature control medium in refrigeration machine control refrigeration piping,
To adjust heat sink temperature.
3. temperature-adjustment pressure-adjustment device as claimed in claim 2, wherein, it is heat sink to be installed on inside vacuum tank, by conduction of heat,
Vacuum tank interior environment temperature and heat sink temperature synchronous adjustment.
4. temperature-adjustment pressure-adjustment device as claimed in claim 1, wherein, vavuum pump has fixed gas pumping speed, at it to vacuum
While container is evacuated with fixing pumping speed, gas flow-control supplements the dry air entered inside vacuum tank
Or nitrogen flow, realize the accurate control of vacuum tank internal pressure.
5. temperature-adjustment pressure-adjustment device as claimed in claim 1, wherein, the gas that supplement enters inside vacuum tank is in dry air
Switch with two kinds of gases of nitrogen, meet different demands of the different tests task to gas, and ensure inside vacuum tank
Do not condensed under worst cold case.
6. the temperature-adjustment pressure-adjustment device as described in claim any one of 1-4, wherein, heat exchanger is connected with refrigeration piping, passes through gas
The gas that body flow controller supplement enters inside vacuum tank is first exchanged heat before vacuum tank is entered with heat exchanger, is reached
To the gas temperature supplemented into inside vacuum tank and existing gas temperature is consistent inside vacuum tank.
7. the temperature-adjustment pressure-adjustment device as described in claim any one of 1-4, wherein, refrigeration machine, vavuum pump, valve, gas flow
Controller can be automatically controlled by switch board, realize automatically adjusting for vacuum tank internal pressure temperature.
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| CN201610565177.5A CN107539502B (en) | 2016-07-18 | 2016-07-18 | Temperature-adjustment pressure-adjustment device for spacecraft environment test |
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| CN201610565177.5A CN107539502B (en) | 2016-07-18 | 2016-07-18 | Temperature-adjustment pressure-adjustment device for spacecraft environment test |
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| CN107539502B CN107539502B (en) | 2019-05-14 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108479865A (en) * | 2018-02-13 | 2018-09-04 | 中国科学院西安光学精密机械研究所 | It is a kind of can simulated high altitude climatic environment experimental rig |
| CN108945535A (en) * | 2018-07-12 | 2018-12-07 | 上海卫星装备研究所 | A kind of Space environment simulation facility nitrogen cooling type chilled water unit |
| CN109681417A (en) * | 2019-01-07 | 2019-04-26 | 台州学院 | A kind of vacuum system |
| CN109738012A (en) * | 2019-01-07 | 2019-05-10 | 台州学院 | A kind of condenser temperature pressure monitor system |
| CN109941464A (en) * | 2019-04-01 | 2019-06-28 | 北京卫星环境工程研究所 | The waveguide ring moulds vacuum tank at included spill spherical crown gate |
| CN110294149A (en) * | 2019-07-02 | 2019-10-01 | 北京卫星环境工程研究所 | Transient temperature simulation system and method under hypobaric |
| CN110525698A (en) * | 2019-08-13 | 2019-12-03 | 北京卫星环境工程研究所 | Test macro and test method for space capsule pressure guard system |
| CN111377068A (en) * | 2018-12-28 | 2020-07-07 | 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） | Heat dissipation method for sealed cabin in vacuum environment |
| CN112295630A (en) * | 2020-10-19 | 2021-02-02 | 北京卫星环境工程研究所 | Liquid nitrogen and bath oil double-medium compatible high-vacuum temperature regulating system and temperature regulating method |
| CN113985950A (en) * | 2021-11-22 | 2022-01-28 | 中国电子技术标准化研究院 | High vacuum environment test piece temperature control device |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2185560B (en) * | 1985-05-13 | 1990-07-18 | Pittsburgh Des Moines Corp | Liquid nitrogen distribution system |
| CN101920792A (en) * | 2010-08-02 | 2010-12-22 | 浙江大学 | Environmental chamber for multi-parameter composite test |
| CN102009748A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | 20K cold shield refrigerating device |
| CN103287590A (en) * | 2013-05-07 | 2013-09-11 | 中国科学院力学研究所 | Composite device for space environment simulation vacuum equipment |
| CN103318427A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航系统工程研究所 | Space environment simulation testing system |
| CN105493656B (en) * | 2008-12-11 | 2013-09-25 | 上海卫星装备研究所 | The vacuum suction pipeline device of spacecraft environment simulated test facility |
| CN105584646A (en) * | 2014-10-21 | 2016-05-18 | 北京航天长征飞行器研究所 | Temperature control constant-pressure closed cabin in vacuum low-temperature environment |
-
2016
- 2016-07-18 CN CN201610565177.5A patent/CN107539502B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2185560B (en) * | 1985-05-13 | 1990-07-18 | Pittsburgh Des Moines Corp | Liquid nitrogen distribution system |
| CN105493656B (en) * | 2008-12-11 | 2013-09-25 | 上海卫星装备研究所 | The vacuum suction pipeline device of spacecraft environment simulated test facility |
| CN102009748A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | 20K cold shield refrigerating device |
| CN101920792A (en) * | 2010-08-02 | 2010-12-22 | 浙江大学 | Environmental chamber for multi-parameter composite test |
| CN103287590A (en) * | 2013-05-07 | 2013-09-11 | 中国科学院力学研究所 | Composite device for space environment simulation vacuum equipment |
| CN103318427A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航系统工程研究所 | Space environment simulation testing system |
| CN105584646A (en) * | 2014-10-21 | 2016-05-18 | 北京航天长征飞行器研究所 | Temperature control constant-pressure closed cabin in vacuum low-temperature environment |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108479865A (en) * | 2018-02-13 | 2018-09-04 | 中国科学院西安光学精密机械研究所 | It is a kind of can simulated high altitude climatic environment experimental rig |
| CN108945535A (en) * | 2018-07-12 | 2018-12-07 | 上海卫星装备研究所 | A kind of Space environment simulation facility nitrogen cooling type chilled water unit |
| CN111377068A (en) * | 2018-12-28 | 2020-07-07 | 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） | Heat dissipation method for sealed cabin in vacuum environment |
| CN109681417A (en) * | 2019-01-07 | 2019-04-26 | 台州学院 | A kind of vacuum system |
| CN109738012A (en) * | 2019-01-07 | 2019-05-10 | 台州学院 | A kind of condenser temperature pressure monitor system |
| CN109681417B (en) * | 2019-01-07 | 2020-04-17 | 台州学院 | Vacuum system |
| CN109738012B (en) * | 2019-01-07 | 2020-12-25 | 台州学院 | Condenser temperature and pressure monitoring system |
| CN109941464A (en) * | 2019-04-01 | 2019-06-28 | 北京卫星环境工程研究所 | The waveguide ring moulds vacuum tank at included spill spherical crown gate |
| CN110294149A (en) * | 2019-07-02 | 2019-10-01 | 北京卫星环境工程研究所 | Transient temperature simulation system and method under hypobaric |
| CN110525698A (en) * | 2019-08-13 | 2019-12-03 | 北京卫星环境工程研究所 | Test macro and test method for space capsule pressure guard system |
| CN112295630A (en) * | 2020-10-19 | 2021-02-02 | 北京卫星环境工程研究所 | Liquid nitrogen and bath oil double-medium compatible high-vacuum temperature regulating system and temperature regulating method |
| CN113985950A (en) * | 2021-11-22 | 2022-01-28 | 中国电子技术标准化研究院 | High vacuum environment test piece temperature control device |
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| CN107539502B (en) | 2019-05-14 |
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