CN102818978A - Satellite travelling-wave tube thermovacuum testing system - Google Patents
Satellite travelling-wave tube thermovacuum testing system Download PDFInfo
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- CN102818978A CN102818978A CN2012102872725A CN201210287272A CN102818978A CN 102818978 A CN102818978 A CN 102818978A CN 2012102872725 A CN2012102872725 A CN 2012102872725A CN 201210287272 A CN201210287272 A CN 201210287272A CN 102818978 A CN102818978 A CN 102818978A
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Abstract
The invention provides a satellite travelling-wave tube thermovacuum testing system which comprises a vacuum vessel, wherein the vacuum vessel is internally provided with a travelling-wave tube platform which is fixedly arranged on an elevating mechanism; the travelling-wave tube platform is of a hollow cavity structure; the cavity is internally provided with a heat exchange tube; the heat exchange tube is connected with a refrigerating unit through a coolant pipeline; and the refrigerating unit is positioned outside the vacuum vessel. According to the satellite travelling-wave tube thermovacuum testing system provided by the invention, a travelling-wave tube exchanges heat with the travelling-wave tube platform through a heat conduction mode, so that the heat exchange efficiency between the travelling-wave tube platform and a test piece is greatly improved, The travelling-wave tube cooling time is reduced, and one technical problem in a satellite travelling-wave tube thermovacuum testing process is solved.
Description
Technical field
The present invention relates to a kind of simulation experiment system, relate to a kind of satellite travelling wave tube thermal vacuum test system specifically.
Background technology
Satellite travelling wave tube belongs to one of important parts in the satellite celestial body; It is carried out thermal vacuum test; Mainly be the vacuum of virtual space, the cold black environment that reaches solar irradiation; Existing simulation experiment system mainly is made up of branch systems such as vacuum tank, heat sink, vacuum suction, refrigerant supply, infrared hot-fluid, equipment observing and controlling, and vacuum tank is the main body of system, and the high vacuum unit that draws gas can make its acquisition be superior to 1.3 * 10
-3The vacuum tightness of Pa; Be placed on heat sink in the vacuum tank and be an important component part of hot parts vacuum test system; Process with copper or stainless steel metal material, its inside surface is coated with the high IR absorptivity pitch-dark, behind the interior feeding of the pipe low temperature refrigerant; Make whole heat sink temperature remain below-75 ℃, come the cold darkness environment in the residing space of analog satellite intraware; The heating arrangement of infrared hot-fluid be installed in heat sink and test specimen between, simulated solar can make the test specimen surface temperature be elevated to 120 ℃ to the irradiation hot-fluid of satellite parts; In the thermovacuum simulation test procedure, generally be superior to 1.3 * 10 with satellite travelling wave tube environment vacuum tightness owing to heat sink
-3Pa; Therefore; With the heat exchange of heat radiation mode, evidence is even existing simulation test device becomes liquid nitrogen (196 ℃) feeding heat sink-75 ℃ refrigerant between them; Also can't the travelling-wave tube of heating power 70W be dropped to-35 ℃ of low temperature hot dipping districts from+70 ℃ of high temperature hot dipping districts in less than 4 hours time, can't satisfy the cooling time spent less than 4 hours test specification.
Summary of the invention
The purpose of this invention is to provide a kind of satellite travelling wave tube thermal vacuum test system, the heat exchange efficiency that it can improve between environment temperature and the test specimen travelling-wave tube satisfies testing requirements.
To achieve these goals, technical solution of the present invention is: a kind of satellite travelling wave tube thermal vacuum test system comprises vacuum tank; Be provided with the travelling-wave tube platform in the vacuum tank, the travelling-wave tube platform is provided with fixed orifice, and the travelling-wave tube platform is fixed on the elevating mechanism; Wherein, said travelling-wave tube platform is the hollow type cavity body structure, is provided with heat exchanger tube in its cavity; Said heat exchanger tube is connected with refrigeration unit through refrigerant pipe, and said refrigeration unit is positioned at outside the said vacuum tank.
Satellite travelling wave tube thermal vacuum test of the present invention system, wherein, said refrigeration unit is connected with the cold medium flux control device.
Satellite travelling wave tube thermal vacuum test of the present invention system wherein, is provided with heat insulating mattress between said travelling-wave tube platform and the said elevating mechanism.
Satellite travelling wave tube thermal vacuum test of the present invention system, wherein, said heat insulating mattress is processed by teflon.
Satellite travelling wave tube thermal vacuum test of the present invention system, wherein, said travelling-wave tube platform is become by stainless steel or copper.
Satellite travelling wave tube thermal vacuum test of the present invention system wherein, is connected through metal hose between said refrigerant pipe and the heat exchanger tube.
Satellite travelling wave tube thermal vacuum test of the present invention system, wherein, said heat exchanger tube adopts copper pipe or stainless-steel tube.
Satellite travelling wave tube thermal vacuum test of the present invention system wherein, saidly has the refrigerant pipe on heat sink; Vacuum tank is provided with the import and export of refrigerant pipe; Import and export end and have the vacuum tank flange, the position outer wall of turnover vacuum tank is with corrugated tube on the refrigerant pipe, and corrugated tube is away from being welded to each other between end of vacuum tank and the refrigerant pipe; Corrugated tube has the corrugated tube flange near an end of vacuum tank; Said corrugated tube flange is positioned at vacuum tank flange inner chamber with concentric setting of vacuum tank flange and corrugated tube flange, and the corrugated tube flange is removably connected with counter flange, and counter flange is positioned at the axial outside of corrugated tube flange; Removably connect between counter flange and the vacuum tank flange, be equipped with packoff between corrugated tube flange and the counter flange and between counter flange and the vacuum tank flange (13).
Satellite travelling wave tube thermal vacuum test of the present invention system wherein, is connected through screw (8) between said corrugated tube flange and the counter flange.
Satellite travelling wave tube thermal vacuum test of the present invention system wherein, is connected through clamp between said counter flange and the vacuum tank flange.
After adopting such scheme; Satellite travelling wave tube thermal vacuum test system of the present invention is that heat exchanger tube provides refrigerant owing to be provided with heat exchanger tube in the cavity of travelling-wave tube platform through refrigeration unit, and the travelling-wave tube platform temperature is reduced; Between travelling-wave tube and the travelling-wave tube platform through heat conducting mode heat exchange; Greatly improve the heat exchange efficiency between travelling-wave tube platform and the test specimen, shortened the time that makes the travelling-wave tube cooling, solved a technical barrier in the satellite travelling wave tube thermal vacuum test process.
In addition, be provided with heat insulating mattress between travelling-wave tube platform and the elevating mechanism, reduce the thermal loss of travelling-wave tube platform.
Also have, the travelling-wave tube platform is become by stainless steel or copper, and heat exchanger tube adopts copper pipe or stainless-steel tube, and copper and stainless heat conductivility are good, guarantee higher heat exchange efficiency between travelling-wave tube and the travelling-wave tube platform; Be connected through metal hose between refrigerant pipe and the heat exchanger tube, be convenient to travelling-wave tube platform adjustment position; Only need during heat sink dismounting get final product with taking apart between corrugated tube flange and the counter flange, both convenient, fast, safety, reliably again, and can not cause damage to original equipment, avoid waste.
Description of drawings
Fig. 1 is the structural representation of satellite travelling wave tube thermal vacuum test of the present invention system;
Fig. 2 is the cut-open view of satellite travelling wave tube thermal vacuum test system vacuum container of the present invention;
Fig. 3 is the cut-open view of heat sink refrigerant pipe of satellite travelling wave tube thermal vacuum test system of the present invention and vacuum tank coupling part.
Embodiment
As shown in Figure 1, satellite travelling wave tube thermal vacuum test of the present invention system comprises vacuum tank 1; Vacuum tank 1 is connected with vacuum suction unit 11 and vacuum suction control system 12, and is as shown in Figure 2, is provided with infrared heating device 2 in the vacuum tank 1; Be provided with heat sinkly 3 between infrared heating device 2 and the vacuum tank 1, be provided with travelling-wave tube platform 4 in the infrared heating device 2, travelling-wave tube platform 4 is provided with fixed orifice; Travelling-wave tube platform 4 is fixed on the elevating mechanism 5, is provided with heat insulating mattress 6 between travelling-wave tube platform 4 and the said elevating mechanism 5, and heat insulating mattress 6 is processed by teflon; Travelling-wave tube platform 4 is the hollow type cavity body structure, is provided with heat exchanger tube in its cavity, and heat exchanger tube adopts copper pipe or stainless-steel tube; Heat exchanger tube is connected with refrigeration unit 42 through refrigerant pipe 41, is connected the adjustment of travelling-wave tube platform 4 positions when making things convenient for the installation travelling-wave tube between refrigerant pipe 41 and the heat exchanger tube through metal hose; Refrigeration unit 42 is positioned at outside the said vacuum tank 1; Refrigeration unit 42 is connected with cold medium flux control device 43, and travelling-wave tube platform 4 is become by stainless steel or copper, has characteristics such as thermal conductivity is good, the vacuum deflation rate is low, welding performance is good.
As shown in Figure 3; Have refrigerant pipe 31 on heat sink 3; Vacuum tank 1 is provided with the import and export of refrigerant pipe 31; Import and export end and have vacuum tank flange 13, the position outer wall of turnover vacuum tank 1 is with corrugated tube 32 on the refrigerant pipe 31, and corrugated tube 32 is away from being welded to each other between end of vacuum tank 1 and the refrigerant pipe 31; Corrugated tube 32 has corrugated tube flange 321 near an end of vacuum tank 1; Corrugated tube flange 321 is positioned at vacuum tank flange 13 inner chambers with 13 concentric settings of vacuum tank flange and corrugated tube flange 321, and counter flange 7 is positioned at the axial outside of corrugated tube flange 321, and corrugated tube flange 321 removably connects through screw 8 with counter flange 7; Removably connect through clamp 9 between counter flange 7 and the vacuum tank flange 13, be equipped with O-ring seal between corrugated tube flange 321 and the counter flange 7 and between counter flange 7 and the vacuum tank flange 13.
In process of the test, the test specimen travelling-wave tube is fixed on the travelling-wave tube platform 4 through the fixed orifice on the travelling-wave tube platform 4, vacuumize through 11 pairs of vacuum tanks 1 of vacuum suction control system 12 control vacuum suction units, reach test required 1.3 * 10
-3Pa vacuum tightness is carried out hot-fluid heating through 2 pairs of travelling-wave tube of infrared heating device 7 then, makes travelling-wave tube 7 temperature in the testing requirements time reach+70 ℃ high temperature hot dipping district; Again through heat sink 3 with the 4 pairs of travelling-wave tube 7 of travelling-wave tube platform that feed refrigerant cooling that circulates, make travelling-wave tube 7 in the testing requirements time, cool to-35 ℃ of low temperature hot dipping districts from+70 ℃ of high temperature hot dipping districts; Adopt travelling-wave tube thermal vacuum test of the present invention system, make travelling-wave tube 7+70 ℃ of high-temperature regions in the thermal cycle process of-35 ℃ of low-temperature spaces, travelling-wave tube is raised to from-35 ℃ of high-temperature regions+70 ℃ of low-temperature spaces; When high temperature hot dipping test period reaches; Stop the hot-fluid heating, drop to-35 ℃ of low-temperature spaces again from+70 ℃ of high-temperature regions, the time spent is all less than 3 hours; In the thermal vacuum test process accuracy of temperature control reach ± 0.3 ℃, all be superior to test specification.
When needing dismounting heat sink, only need pull down screw 8, can refrigerant pipe 31 be pulled down from vacuum tank 1, from vacuum tank 1, pull out, maintenance or replacing heat sink 3.
Satellite travelling wave tube thermal vacuum test of the present invention system is applicable to the satellite travelling wave tube thermal vacuum test of tens watts to hundreds of watts of heating powers.
The above embodiment describes preferred implementation of the present invention; Be not that scope of the present invention is limited; Design under the prerequisite of spirit not breaking away from the present invention; Various distortion and improvement that the common engineering technical personnel in this area make technical scheme of the present invention all should fall in the definite protection domain of claims of the present invention.
Claims (10)
1. satellite travelling wave tube thermal vacuum test system; Comprise vacuum tank (1), heat sink (3); Be provided with travelling-wave tube platform (4) in the vacuum tank (1), travelling-wave tube platform (4) is provided with fixed orifice, and travelling-wave tube platform (4) is fixed on the elevating mechanism (5); It is characterized in that: said travelling-wave tube platform (4) is the hollow type cavity body structure; Be provided with heat exchanger tube in its cavity, said heat exchanger tube is connected with refrigeration unit (42) through refrigerant pipe (41), and said refrigeration unit (42) is positioned at outside the said vacuum tank (1).
2. satellite travelling wave tube thermal vacuum test as claimed in claim 1 system, it is characterized in that: said refrigeration unit (42) is connected with cold medium flux control device (43).
3. satellite travelling wave tube thermal vacuum test as claimed in claim 2 system is characterized in that: be provided with heat insulating mattress (6) between said travelling-wave tube platform (4) and the said elevating mechanism (5).
4. satellite travelling wave tube thermal vacuum test as claimed in claim 3 system, it is characterized in that: said heat insulating mattress (6) is processed by teflon.
5. satellite travelling wave tube thermal vacuum test as claimed in claim 4 system is characterized in that: said travelling-wave tube platform (4) is become by stainless steel or copper.
6. satellite travelling wave tube thermal vacuum test as claimed in claim 5 system is characterized in that: be connected through metal hose between said refrigerant pipe (41) and the heat exchanger tube.
7. satellite travelling wave tube thermal vacuum test as claimed in claim 6 system is characterized in that: said heat exchanger tube adopts copper pipe or stainless-steel tube.
8. satellite travelling wave tube thermal vacuum test as claimed in claim 7 system; It is characterized in that: have refrigerant pipe (31) on said heat sink (3); Vacuum tank (1) is provided with the import and export of refrigerant pipe (31); Import and export end and have vacuum tank flange (13); The position outer wall that refrigerant pipe (31) is gone up turnover vacuum tank (1) is with corrugated tube (32); Corrugated tube (32) is away from being welded to each other between end of vacuum tank (1) and the refrigerant pipe (31), and corrugated tube (32) has corrugated tube flange (321) near an end of vacuum tank (1), and said corrugated tube flange (321) is positioned at vacuum tank flange (13) inner chamber with concentric setting of vacuum tank flange (13) and corrugated tube flange (321); Corrugated tube flange (321) is removably connected with counter flange (7); Counter flange (7) is positioned at the axial outside of corrugated tube flange (321), removably connects between counter flange (7) and the vacuum tank flange (13), is equipped with packoff between corrugated tube flange (321) and the counter flange (7) and between counter flange (7) and the vacuum tank flange (13).
9. satellite travelling wave tube thermal vacuum test as claimed in claim 8 system is characterized in that: be connected through screw (8) between said corrugated tube flange (321) and the counter flange (7).
10. satellite travelling wave tube thermal vacuum test as claimed in claim 9 system is characterized in that: be connected through clamp (9) between said counter flange (7) and the vacuum tank flange (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102872725A CN102818978A (en) | 2012-08-13 | 2012-08-13 | Satellite travelling-wave tube thermovacuum testing system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012102872725A CN102818978A (en) | 2012-08-13 | 2012-08-13 | Satellite travelling-wave tube thermovacuum testing system |
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| CN102818978A true CN102818978A (en) | 2012-12-12 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105259208A (en) * | 2015-11-23 | 2016-01-20 | 上海卫星装备研究所 | Heat performance test device and method for heat pipe under vacuum |
| CN106184831A (en) * | 2016-06-29 | 2016-12-07 | 上海微小卫星工程中心 | Vacuum thermal test device for high heat flux satellite |
| CN106641697A (en) * | 2016-12-09 | 2017-05-10 | 中国科学院理化技术研究所 | Low-temperature liquid storage container with slit inner fin type heat exchanger and cold screen |
| CN107091802A (en) * | 2017-04-27 | 2017-08-25 | 上海吉通力实验设备有限公司 | Thermal vacuum test case |
| CN107124235A (en) * | 2017-04-26 | 2017-09-01 | 中国空间技术研究院 | Passive intermodulation wireless test system under a kind of hot vacuum environment |
| CN109317223A (en) * | 2018-11-23 | 2019-02-12 | 杭州杭氧低温容器有限公司 | Horizontal mailbox shape hypobaric simulator |
| CN111717425A (en) * | 2020-06-01 | 2020-09-29 | 北京空间飞行器总体设计部 | Heat source isolation and automatic temperature control system based on multi-satellite parallel thermal vacuum test |
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| JPH08192800A (en) * | 1995-01-19 | 1996-07-30 | Nippon Sanso Kk | Space environment testing device |
| JP2000095198A (en) * | 1998-09-21 | 2000-04-04 | Nippon Sanso Corp | Temperature control base plate and control method for the same |
| 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 |
| CN202748445U (en) * | 2012-08-13 | 2013-02-20 | 北京合丰天成科技有限公司 | Thermal-vacuum testing system of satellite travelling wave tube |
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2012
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105259208A (en) * | 2015-11-23 | 2016-01-20 | 上海卫星装备研究所 | Heat performance test device and method for heat pipe under vacuum |
| CN106184831A (en) * | 2016-06-29 | 2016-12-07 | 上海微小卫星工程中心 | Vacuum thermal test device for high heat flux satellite |
| CN106184831B (en) * | 2016-06-29 | 2018-04-13 | 上海微小卫星工程中心 | Vacuum thermal test device for high heat flux density satellite |
| CN106641697A (en) * | 2016-12-09 | 2017-05-10 | 中国科学院理化技术研究所 | Low-temperature liquid storage container with slit inner fin type heat exchanger and cold screen |
| CN106641697B (en) * | 2016-12-09 | 2018-11-23 | 中国科学院理化技术研究所 | A kind of low-temperature liquid storage container with the cold screen of slit wing type heat exchanger |
| CN107124235A (en) * | 2017-04-26 | 2017-09-01 | 中国空间技术研究院 | Passive intermodulation wireless test system under a kind of hot vacuum environment |
| CN107091802A (en) * | 2017-04-27 | 2017-08-25 | 上海吉通力实验设备有限公司 | Thermal vacuum test case |
| CN107091802B (en) * | 2017-04-27 | 2022-07-26 | 上海吉通力实验设备有限公司 | Thermal vacuum test box |
| CN109317223A (en) * | 2018-11-23 | 2019-02-12 | 杭州杭氧低温容器有限公司 | Horizontal mailbox shape hypobaric simulator |
| CN109317223B (en) * | 2018-11-23 | 2023-08-04 | 杭州杭氧低温容器有限公司 | Horizontal mail box shape low air pressure environment simulator |
| CN111717425A (en) * | 2020-06-01 | 2020-09-29 | 北京空间飞行器总体设计部 | Heat source isolation and automatic temperature control system based on multi-satellite parallel thermal vacuum test |
| CN111717425B (en) * | 2020-06-01 | 2022-03-04 | 北京空间飞行器总体设计部 | Heat source isolation and automatic temperature control system based on multi-satellite parallel thermal vacuum test |
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