CN113985950B - High vacuum environment test piece temperature control device - Google Patents
High vacuum environment test piece temperature control device Download PDFInfo
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- CN113985950B CN113985950B CN202111388508.XA CN202111388508A CN113985950B CN 113985950 B CN113985950 B CN 113985950B CN 202111388508 A CN202111388508 A CN 202111388508A CN 113985950 B CN113985950 B CN 113985950B
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/30—Automatic controllers with an auxiliary heating device affecting the sensing element, e.g. for anticipating change of temperature
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Abstract
The utility model provides a high vacuum environment test piece temperature control device, its includes the vacuum tank body, is used for sealing the sealing flange of vacuum tank body tip, the inside heat sink that is used for testing work piece temperature regulation control of vacuum tank body and with heat sink and the pipeline of outside accuse temperature unit connection. The vacuum tank body is of a horizontal cylindrical structure. The heat sink comprises a bottom heat sink and an annular heat sink; the bottom heat sink and the annular heat sink form a test cavity for placing a test workpiece. And a plurality of groups of heat fins for contacting with a test workpiece to conduct heat are arranged on the surface of the heat sink on the inner side of the test cavity. The heat fins comprise an inner layer heat fin and an outer layer heat fin, wherein the two ends of the inner layer heat fin and the outer layer heat fin are overlapped and fixed on the surface of the heat sink; the inner layer hot fin and the outer layer hot fin are both of arch-shaped elastic structures with two ends fixed and middle suspended bulges. The invention has the beneficial technical effects of good adaptability and high heat conduction efficiency.
Description
Technical Field
The invention belongs to the field of high-vacuum environment test equipment, and particularly relates to a temperature control device for a high-vacuum environment test piece.
Background
In recent years, space flight activities such as space stations, satellites and the like in China are increasingly complex, the service life of a spacecraft is increasingly long, and the requirement of space equipment on reliability is also increasingly high. When the pressure is lower than 10-7Pa, the cold welding effect can occur to the key electrician and electronic components and elements such as switches, relays, connectors and the like which work in the vacuum environment under the action of temperature and high vacuum stress, thereby causing the electromechanical failure of the spacecraft.
When the metal solid is in the ultrahigh vacuum condition, the gas adsorbed on the surface escapes, the metal surfaces are directly contacted with each other under the conditions that various organic pollution films are resolved and disappear and the metal oxide layer is cracked, and the friction force between metals is increased by more than ten times compared with the friction force under the atmospheric condition. At this time, the molecules diffuse into each other to cause adhesion phenomena to different degrees. If the surface is atomically clean, further bulk adhesion occurs under a certain pressure load, i.e., cold welding is induced.
Through years of research at home and abroad, the main factors influencing adhesion and cold welding are generally considered as follows: surface cleanliness, pressure load, contact time, material properties, and temperature.
The vacuum degree selection magnitude of the high vacuum cold welding ground simulation test is usually between 10 < -7 > Pa and 10 < -9 > Pa, and the heat sink temperature is between 55 ℃ below zero and 90 ℃. It is considered that the vacuum having a pressure of 1X 10-7Pa or less is called an ultra-high vacuum, and the number of molecules per unit volume is only 1/1,000,000,000,000 at normal atmospheric pressure.
The latest version of the standard of the high vacuum cold welding test method which can be referred to in China at present is' QJ 20422.5-2016 aerospace component environmental test method part 5: the vacuum cold welding test is the aerospace industry standard of the people's republic of China. Where temperature control is described in appendix a (reference) as "clause a5.1.3 c) d) the vacuum chamber should be equipped with component heating and cooling devices (sometimes replaced with heat sinks). Clause 5.1.5 the test temperature control system has the function of temperature control of the test assembly and has a corresponding status display. Has the functions of warning, prompting, inquiring and storing. "
The vacuum cold welding test procedure is summarized as follows:
the test piece should be cleaned before testing, and oil-free treatment is carried out. The sample is installed in a vacuum chamber, the vacuum chamber is sealed by adopting a metal sealing ring, different installation modes are selected according to the appearance of the test piece, the sample can be installed on a fixed substrate or fixed on a corresponding device through an installation flange, a power line and a related test signal line are connected, and air suction is started after the reliable sealing is preliminarily confirmed. The vacuum pumping is at least 1 x 10-7Pa, and the heat sink of the temperature control device reaches the specified temperature. The test piece was checked for performance by keeping for a corresponding time as specified.
Because heat can not be transferred in a convection mode in a vacuum environment, the temperature control in the vacuum environment in the existing test method is mainly carried out through heat sink conduction or radiation, but most test pieces are irregular geometric shapes and can not be conducted through a fixing device by adopting heat sinks, and when the vacuum degree is less than 1 multiplied by 10 < -7 > Pa, the molecular density of the environment in a test chamber is extremely low, the radiation effect not only slowly transfers heat, but also the temperature of the test workpiece is difficult to control. The test piece can not reach the specified temperature condition or has poor uniformity in the test, so that the purpose of test examination can not be realized.
Disclosure of Invention
The invention aims to solve the problem of low heat conduction efficiency of a test piece in the vacuum cold welding test process.
In order to solve the problems, the invention provides a high-vacuum environment test piece temperature control device which is used for controlling the temperature of a test piece and improving the temperature conduction uniformity in a high-vacuum environment (the vacuum degree is less than 1 x 10 < -7 > Pa) so as to solve the problems of inaccurate temperature control, poor uniformity and low efficiency in the prior art.
The high vacuum environment test piece temperature control device comprises a vacuum tank body, a sealing flange used for sealing the end part of the vacuum tank body, a heat sink used for testing the temperature regulation and control of a workpiece in the vacuum tank body, and a pipeline connected with the heat sink and an external temperature control unit.
The external temperature control unit is a heat conduction oil unit, temperature control of the tested workpiece from minus 85 ℃ to 200 ℃ can be achieved, and control precision can reach plus or minus 0.1 ℃.
The vacuum tank body is of a horizontal cylindrical structure.
The heat sink comprises a bottom heat sink and an annular heat sink; the bottom heat sink and the annular heat sink form a test cavity for placing a test workpiece.
The test workpiece is also matched with a workpiece mounting disc, the workpiece mounting disc is used for testing the cold welding condition of the test workpiece under various temperature and vacuum conditions, and meanwhile, the workpiece mounting disc also has the functions of positioning, supporting and heat conducting. When the parts to be tested are matched in groups and have the size and shape suitable for the inner space of the vacuum tube body, a workpiece mounting disc is not needed; in view of the actual requirement of cold welding test, the material of the workpiece mounting plate is the same as that of the matching part in the working state of the test workpiece, so that the workpiece mounting plate can be regarded as a component or an accessory of the test workpiece.
And a plurality of groups of heat fins for contacting with a test workpiece to conduct heat are arranged on the surface of the heat sink on the inner side of the test cavity.
The heat fins comprise an inner layer heat fin and an outer layer heat fin, and the two ends of the inner layer heat fin and the two ends of the outer layer heat fin are overlapped and fixed on the surface of the heat sink; the inner layer hot fin and the outer layer hot fin are both of arch-shaped elastic structures with two ends fixed and middle suspended bulges.
The heat wing is made of beryllium bronze band.
The interval between the top ends of the inner layer hot fin and the outer layer hot fin is 2-3 mm.
The cutting size of the beryllium bronze strip is 100mm multiplied by 10mm multiplied by 0.2m.
Fixing areas with the length of 6mm are reserved at two ends of the inner-layer heat fin for pressing and fixing with the heat sink.
And fixing areas with the length of 15mm are reserved at two ends of the outer-layer heat fin for pressing and fixing with the heat sink.
The difference S between the end fixing areas of the inner layer heat fin and the outer layer heat fin is not less than 3mm.
The ratio of the height A of the outer heat fins to the width B of the middle arch structure is 0.3-0.8.
The vacuum tank body also comprises a connecting pipeline for vacuum air suction.
And the vacuum pump air pumping system is connected with the vacuum tank body and consists of a pre-pumping system and a main pumping system, the pre-pumping system consists of a set of imported molecular pump and a set of imported vortex dry pump, and the main pumping system consists of an ion pump and a titanium sublimation pump. The vacuum guarantee system helps equipment to obtain the vacuum degree required by the test, and mainly comprises a vacuum pump pumping system, a vacuum valve, a matched pipeline, a vacuum measuring device and the like.
The temperature guarantee of the vacuum pump air exhaust system is realized by the temperature control unit matched with a heat sink in the vacuum cavity. The cavity is internally composed of two groups of heat sinks, namely a bottom heat sink and an annular heat sink. The bottom heat sink is mainly used for large test samples and can be used as an auxiliary heat source. The heat exchange between the heat sink and the test piece is realized by the elastic heat conduction structure of the heat wing, and the structure is a special structure specially designed for solving the problem of temperature conduction in an ultrahigh vacuum environment and can ensure that the test piece has good heat conduction and uniformity.
The heat wing has high elasticity, wear resistance, ideal heat conducting property and good vacuum performance, and does not release gas to influence vacuum degree reduction while ensuring heat conduction.
The test workpiece is in elastic contact with the plurality of hot wings, so that the heat conduction area is large, the efficiency is high, and the heat conduction is uniform and good. The heat transfer between the heat sink and the test piece is ensured to the maximum extent, and the vacuum degree in the cabin is not influenced. The size of the 'hot wing' can be adjusted according to the size of the vacuum chamber and the size of the sample piece, and finally, a soft connection heat conduction mode in the test chamber is realized.
The hot wing is installed and pressed on the inner wall of the heat sink, so that the flat and tight fit of the hot wing and the heat sink is ensured, and the heat conduction efficiency is effectively improved. The whole body is placed on a cold and hot test platform in a vacuum test cavity, and the temperature conduction performance of the heat conduction device is verified through the temperatures of the heat sink, the test sample mounting disc and the test piece.
One end of the heat wing is close to the heat sink in the cabin, and the other end of the heat wing is of a flexible structure and can be changed randomly along with the appearance structure of the test piece, so that the heat wing can be in contact with the surface of the test piece to the maximum extent, and the heat can be better transferred to the test piece to reach the temperature specified by the test conditions. The number of "thermal fins" can be increased or decreased as appropriate for different volumes of sample. For a test piece with a larger volume, the 'hot wing' except the annular area in the cabin can be tightly attached to the sample, and the bottom of the test piece can be controlled by adopting a mode of installing the 'hot wing'. The elastic heat conduction contact is adopted to adapt to test workpieces with different sizes and shapes, and the contact heat conduction is faster, more efficient and easier to control than space heat radiation to test the temperature of the workpieces. The temperature of the test workpiece can be rapidly increased or decreased, and the temperature requirement of the test workpiece on the test workpiece can be met with higher precision and more efficiently.
In conclusion, the invention has the beneficial technical effects of good adaptability and high heat conduction efficiency.
Drawings
FIG. 1 is a schematic diagram of the principles of the present invention;
FIG. 2 is a cross-sectional view of a heat sink structure of the present invention;
FIG. 3 is a side view of a thermal wing structure of the present invention;
in the figure: 1. vacuum tank body: 2. sealing the flange; 3. testing the workpiece; 4. a heat sink; 5. a heat conducting engine oil group; 6. a pipeline; 7. a vacuum pump pumping system; 8. a thermal wing; 9. hot wing trim strips; 31. a workpiece mounting plate; 41. a bottom heat sink; 42. an annular heat sink; 71. a molecular pump; 72. a vortex dry pump; 73. an ion pump; 74. a titanium sublimation pump; 75. a self-pressurizing liquid nitrogen tank; 76. a vacuum valve; 81. an inner layer thermal fin; 82. an outer layer thermal fin; 311. and supporting the flange.
Detailed Description
The following further description of the embodiments with reference to fig. 1-2 and the specific examples is provided to facilitate the understanding of the present invention.
As shown in fig. 1, the temperature control device for the high vacuum environment test piece comprises a vacuum tank body 1, a sealing flange 2 for sealing the end part of the vacuum tank body 1, a heat sink 4 for adjusting and controlling the temperature of a test workpiece 3 in the vacuum tank body 1, and a pipeline 6 connected with the heat sink 4 and a heat conduction oil unit 5.
The heat sink 4 is connected with the heat conduction oil unit 5 through a pipeline, and heat is transferred to the heat sink 4 through the heat conduction oil unit 5, so that the test workpiece 3 is heated or cooled.
The vacuum tank body 1 is connected with a vacuum pump air-extracting system 7, and the vacuum pump air-extracting system 7 comprises a pre-extracting system and a main extracting system; the pre-pumping system consists of a molecular pump 71, a vortex dry pump 72 and a vacuum valve 76; the main air pumping system consists of an ion pump 73, a titanium sublimation pump 74 and a self-pressurization liquid nitrogen tank 75. The vacuum pump exhaust system 7 obtains the vacuum degree required by the test for the equipment.
The vacuum tank body 1 is of a horizontal cylindrical structure.
As shown in fig. 2, the heat sink 4 includes a bottom heat sink 41 and a ring-shaped heat sink 42; the bottom heat sink 41 and the annular heat sink 42 form a test cavity for placing a test workpiece. The bottom heat sink 41 is mainly used for large test samples and can be used as an auxiliary heat source.
The test workpiece 3 is arranged in the workpiece mounting disc 31 to test the cold welding condition of the test workpiece 3 and the workpiece mounting disc 31 under various temperature and vacuum conditions; the workpiece mounting disk 31 is a cylindrical member having a support flange 311 for positioning and heat conduction of the test workpiece 3 therein; the support flange 311 is in close contact with the test workpiece 3 and suspends the bottom of the test workpiece 3.
And a plurality of groups of thermal fins 8 which are used for contacting with the outer side surface of the workpiece mounting disc 31 for heat conduction are arranged on the surface of the heat sink 4 at the inner side of the test cavity.
The heat fins 8 comprise an inner layer heat fin 81 and an outer layer heat fin 82, two ends of which are overlapped and fixed on the surface of the heat sink; the inner layer hot fin and the outer layer hot fin are both of arch-shaped elastic structures with two ends fixed with middle suspending bulges.
As shown in fig. 3, the heat fin 8 is mounted and pressed on the inner wall of the heat sink by the heat fin pressing strip 9, so as to ensure that the heat fin 8 is smoothly and tightly attached to the heat sink 4, thereby effectively improving the heat conduction efficiency.
The hot fin 8 is made of beryllium bronze strip.
The interval between the top ends of the inner layer heat fin 81 and the outer layer heat fin 82 is 2-3 mm.
The cutting size of the beryllium bronze strip is 100mm multiplied by 10mm multiplied by 0.2m.
The length of the fixing area at the two ends of the inner layer heat fin 81 is 6mm long so as to be used for compressing and fixing with the heat sink 4.
And fixing areas with the length of 15mm are reserved at two ends of the outer-layer heat fin for pressing and fixing with the heat sink.
The difference S between the end fixing areas of the inner heat fin 81 shown and the outer heat fin 82 shown is 9mm.
The ratio of the height A of the outer layer heat fins to the width B of the middle arch structure is 0.45;
the vacuum tank body 1 further comprises a connecting pipeline for vacuum air suction.
The heat exchange between the heat sink 4 and the test workpiece 3 is realized by the elastic heat conduction structure of the heat wing 8, which is a special structure specially designed for solving the problem of temperature conduction in an ultrahigh vacuum environment, and can ensure that the heat conduction and uniformity of the test workpiece 3 are good.
The hot wing 8 has high elasticity, wear resistance, ideal temperature conduction performance and good vacuum performance, and does not release gas to influence vacuum degree reduction while ensuring the temperature conduction.
The workpiece mounting disc 31 is in elastic contact with the plurality of hot wings 8, so that the heat conduction area is large, the efficiency is high, and the heat conduction is uniform. The heat transfer between the heat sink 4 and the test workpiece 3 is ensured to the maximum extent, and the vacuum degree in the cabin is not influenced.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (7)
1. The utility model provides a high vacuum environment test piece temperature control device which characterized in that: the device comprises a vacuum tank body, a sealing flange used for sealing the end part of the vacuum tank body, a heat sink used for testing the temperature regulation and control of a workpiece in the vacuum tank body, and a pipeline connected with the heat sink and an external temperature control unit;
the heat sink comprises a bottom heat sink and an annular heat sink; the bottom heat sink and the annular heat sink form a test cavity for placing a test workpiece;
a plurality of groups of heat fins for contacting with a test workpiece to conduct heat are arranged on the surface of the heat sink on the inner side of the test cavity;
the heat fins comprise an inner layer heat fin and an outer layer heat fin, and the two ends of the inner layer heat fin and the two ends of the outer layer heat fin are overlapped and fixed on the surface of the heat sink; the inner layer hot fin and the outer layer hot fin are both of arch-shaped elastic structures with two ends fixed with middle suspending bulges.
2. The temperature control device for the high vacuum environment test piece according to claim 1, characterized in that: the vacuum tank body is of a horizontal cylindrical structure.
3. The temperature control device for the high vacuum environment test piece according to claim 1, characterized in that: the heat wing is made of beryllium bronze strip.
4. The temperature control device for the high vacuum environment test piece according to claim 1, characterized in that: the interval between the top ends of the inner layer hot fin and the outer layer hot fin is 2-3 mm.
5. The temperature control device for the high vacuum environment test piece according to claim 3, characterized in that: the cutting size of the beryllium bronze strip is 100mm multiplied by 10mm multiplied by 0.2m.
6. The temperature control device for the high vacuum environment test piece according to claim 1, characterized in that: and fixing areas with the length of 6mm are reserved at two ends of the inner-layer heat fin for pressing and fixing with the heat sink.
7. The temperature control device for the high vacuum environment test piece according to claim 1, characterized in that: fixing areas with the length of 15mm are reserved at two ends of the outer layer heat fin for pressing and fixing with the heat sink.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111388508.XA CN113985950B (en) | 2021-11-22 | 2021-11-22 | High vacuum environment test piece temperature control device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111388508.XA CN113985950B (en) | 2021-11-22 | 2021-11-22 | High vacuum environment test piece temperature control device |
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| CN113985950A CN113985950A (en) | 2022-01-28 |
| CN113985950B true CN113985950B (en) | 2023-04-07 |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0735992B2 (en) * | 1985-08-29 | 1995-04-19 | 株式会社島津製作所 | High / low temperature tensile tester |
| CN201541414U (en) * | 2009-07-28 | 2010-08-04 | 中国科学院西安光学精密机械研究所 | Heat sink device |
| 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 |
| CN203428046U (en) * | 2013-07-25 | 2014-02-12 | 中国科学院武汉物理与数学研究所 | Miniaturized vacuum thermal environment simulator |
| CN107539502B (en) * | 2016-07-18 | 2019-05-14 | 北京卫星环境工程研究所 | Temperature-adjustment pressure-adjustment device for spacecraft environment test |
| CN112660431A (en) * | 2020-12-22 | 2021-04-16 | 北京卫星环境工程研究所 | Integrated environmental simulation test device and method |
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