CN103287590B - A kind of set composite for space environment simulation vacuum apparatus - Google Patents
A kind of set composite for space environment simulation vacuum apparatus Download PDFInfo
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- CN103287590B CN103287590B CN201310163396.7A CN201310163396A CN103287590B CN 103287590 B CN103287590 B CN 103287590B CN 201310163396 A CN201310163396 A CN 201310163396A CN 103287590 B CN103287590 B CN 103287590B
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- aluminum barrel
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- heating element
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- environment simulation
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Abstract
For a set composite for space environment simulation vacuum apparatus, comprise aluminum barrel, described aluminum barrel is arranged in vacuum chamber; Refrigerant pipe, described refrigerant pipe is distributed in the outer wall surface of aluminum barrel, and described refrigerant pipe connects bellows, and described bellows is connected with the refrigerator be arranged on outside vacuum chamber; Insulated tape heating element, described insulated tape heating element is connected with insulated tape heating element power supply, and described insulated tape heating element is distributed in aluminum barrel outside wall surface; Temperature switch, described temperature switch is arranged in the outside wall surface of aluminum barrel; Thermocouple, described thermocouple is placed on aluminum barrel outside wall surface, and described thermocouple connects temp controlled meter.Beneficial effect of the present invention: the integrated high/low temperature of the present invention is heat sink, total cross-section faraday, high-temperature infrared toast three kinds of functions in a device, its structure is simple, save space, economical and practical, and can reduce cost and the over-the-road expense of vacuum apparatus.
Description
Technical field
The present invention relates to a kind of space environment simulation vacuum apparatus, be specifically related to a kind of set composite for space environment simulation vacuum apparatus.
Background technology
Satellite and spacecraft thereof, after entering space orbit mission phase, are in vacuum and cold black space environment for a long time, simultaneously the joint effect of receiving space Orbital heat flux and inside satellite hot-fluid.A kind of large-sized multifunction comprehensive equipment of space environment simulation equipment in order to develop at the environment such as ground simulation space " cold black ", " high vacuum " and " Orbital heat flux " is satellite and spacecraft etc. thereof carry out various performance, reliability and long-life test key equipment on ground.
In order to study space technology, also under simulated space environment, will carry out electric propulsion experiment, novel space electric propulsion (electrical rocket) technology, has the features such as high specific impulse, low thrust, long life.These features are just being applicable to high-speed flight that spacecraft proposes propulsion system, are working and overcome the requirement compared with slight drag reliably and with long-term.To promoting mainly into all there is vital function of the control of near earth space spacecraft or survey of deep space and interplanetary and interstellar navigation.Just because of these features, and successful Application nearly ten years, electric propulsion technology is just more and more subject to people's attention.
In electric propulsion vacuum experiment, propellant pipeline system needs certain experimental temperature, but owing to relating to High-Voltage Insulation etc., general selection infrared radiation heating method, therefore, uses heat sink baking experimental system to be the best approach.But in order to the total cross-section plume electric current collection of electric propulsion device, need at internal vacuum chamber design total cross-section Faraday cage, therefore, need increase one deck design in heat sink inner space, this just conflicts with aforementioned toasting performance.
Vacuum chamber material and oil pollution are given vent to anger can greatly affect its final vacuum, reduces extract system performance, and reduce equipment and run degree of vacuum, its Improving Measurements mainly contains 2 points: regular operation and cleaning.250 DEG C of high-temperature bakings are one of most actv. cleaning means, and can recover final vacuum.In general environment analog machine, heat sink operating temperature is-190 DEG C to 150 DEG C, therefore, have certain cured effect, but temperature end is lower, needed for time of giving vent to anger longer.
Therefore, need badly a kind of make aluminum barrel heat sink can be operated in-190 DEG C to 250 DEG C and insulate with the earth and vacuum chamber, realize that plume total cross-section faraday collects, high-temperature infrared toasts and gives vent to anger and device that the heat sink three kinds of functions of high/low temperature are integrated.
Have no the structure of identical function both at home and abroad: 1) common infrared baking is a kind of bar cage barrel structure; 2) total cross-section is collected Faraday cage and is not attached toasting performance; 3) common heat sink temperature end 150 DEG C, this structure can reach 250 DEG C.
Summary of the invention
The invention provides a kind of set composite for space environment simulation vacuum apparatus, to solve exist in prior art complicated for space environment simulation vacuum apparatus organization establishes, cannot realize collecting high-temperature infrared baking, high/low temperature is heat sink and Faraday cage plume collects three kinds of functions in an integrally-built problem.
For achieving the above object, by the following technical solutions:
For a set composite for space environment simulation vacuum apparatus, comprise aluminum barrel, described aluminum barrel is arranged in vacuum chamber; Electric propulsion device, described electric propulsion device is arranged in vacuum chamber, and it is anterior to be positioned at aluminum barrel open end; V-type plate, described V-type plate is arranged on the bottom surface of one end of aluminum barrel; Insulated tape heating element, described insulated tape heating element is connected with insulated tape heating element power supply, and described insulated tape heating element is distributed in aluminum barrel outside wall surface; Temperature switch, described temperature switch is arranged in the outside wall surface of aluminum barrel; Thermocouple, described thermocouple is placed on aluminum barrel outside wall surface, and described thermocouple connects temp controlled meter; Signal picker, described signal picker is connected with deflection power and aluminum barrel by high temperature wire; Refrigerant pipe, described refrigerant pipe is distributed in the outer wall surface of aluminum barrel, and described refrigerant pipe connects bellows, and described bellows is connected with the refrigerator be arranged on outside vacuum chamber.
Preferably, described V-type plate and aluminum barrel bottom surface normal direction angle are less than 30 °.
Preferably, described aluminum barrel is connected by insulating supporting with vacuum chamber.
Preferably, described temperature switch is the normally closed mechanical switch in Kick type contact.
Preferably, described refrigerant pipe is made up of red copper or stainless steel material, and it is wrapped with thermal insulation layer, insulate with aluminum barrel.
Preferably, described aluminum barrel is made up of hard aluminium alloy material, its outside wall surface polishing, internal face blackening process.
Preferably, described electric propulsion device is ion-conductance propelling unit.
Beneficial effect of the present invention: owing to being provided with insulated tape heating element and temperature switch on aluminum barrel, so can realize high-temperature infrared to toast the function of giving vent to anger; Due to aluminum barrel being provided with refrigerant pipe, so the heat sink function of high/low temperature can be realized; Bottom surface due to one end of aluminum barrel is provided with that V-type plate, aluminum barrel are also connected with signal picker and deflection power, the front end of aluminum barrel is provided with electric propulsion device, so can realize the function that plume total cross-section faraday collects; Invent integrated three kinds of functions in a device, its structure is simple, save space, economical and practical, and cost and the over-the-road expense of vacuum apparatus can be reduced.
Accompanying drawing explanation
According to embodiment and accompanying drawing, the present invention is described in further detail below.
Fig. 1 is the front view of a kind of set composite for space environment simulation vacuum apparatus of the present invention;
Fig. 2 is the lateral plan of Fig. 1;
Fig. 3 is A-A direction view of Fig. 1;
Fig. 4 is the partial enlarged drawing in region shown in label D in Fig. 3.
In figure:
1, insulated tape heating element power supply; 2, thermocouple; 3, temp controlled meter; 4, deflection power; 5, signal picker; 6, refrigerator; 7, bellows; 8, refrigerant pipe; 9, V-type plate; 10, insulating supporting; 11, aluminum barrel; 12, electric propulsion device; 13, plume; 14, vacuum chamber; 15, temperature switch; 16, thermal insulation layer; 17, insulated tape heating element.
Detailed description of the invention
As shown in Figures 1 to 4, give a specific embodiment of the present invention, the present invention includes, vacuum chamber 14, electric propulsion device 12, aluminum barrel 11, the wall good earth of vacuum chamber 14, it is inner that described aluminum barrel 11 is installed on vacuum chamber 14 by insulating supporting 10, aluminum barrel 11 and vacuum chamber 14 insulate, its major dimension is less than vacuum chamber 14, and such vibrational power flow makes to there is a determining deviation between aluminum barrel 11 and vacuum chamber 14, is convenient to the work such as follow-up expansion cleaning.
Set forth below, the heat sink function of low temperature of a kind of set composite for space environment simulation vacuum apparatus of the present invention, space environmental simulation.
The shape of described aluminum barrel 11 is cylindric, and refrigerant pipe is provided with on aluminum barrel 11, refrigerant pipe 8 is distributed on the wall of aluminum barrel 11, refrigerant pipe 8 connects vacuum chamber 14 wall by bellows 7 and is connected the refrigerator 6 being positioned at vacuum chamber 14 outside, therefore, interchange of heat can be carried out with the refrigerator 6 of vacuum chamber 14 outer setting, described refrigerant pipe adopts red copper or stainless steel material to make, its outer wrapping thermal insulation layer 16, be wrapped in the outside wall surface of aluminum barrel 11, the outside face of the refrigerant pipe 8 wrapped up by thermal insulation layer 16 covers one deck aluminum alloy thin layer again, aluminium alloy layer is covered with refrigerant pipe 8, and be welded on aluminum barrel 11.
As preferred embodiment, aluminum barrel 11 outside wall surface light no marking, to reduce the warm wall in vacuum chamber room 14 to the heat load of heat sink low-temperature end; The internal face of aluminum barrel 11 through blackening process, to improve heat emissivity coefficient and absorptivity.Aluminum barrel 11 outside wall surface light, internal face turns black, inside and outside different thermal emissivity rate process, improves test article and the ratio of vacuum chamber 14 wall heat flux bearing power, reduces refrigeration load.
Set forth below, the plume total cross-section faraday collecting function of a kind of set composite for space environment simulation vacuum apparatus of the present invention.
The wall ground connection of vacuum chamber 14, aluminum barrel 11 is connected with signal picker 5 with the deflection power 4 be positioned at outside vacuum chamber 14 by high temperature wire, the electric potential difference of deflection power 4 for giving aluminum barrel 11 relative vacuum room 14 wall certain that aluminum barrel 11 is external, collect plume particle, described signal picker 5 is connected with sampling resistor, realizes total cross-section Faraday cage function.
Electric propulsion device in the present invention is small ion propelling unit, and electric propulsion device 12 is arranged in vacuum chamber 14, and is positioned at the front end of aluminum barrel 11, and plume 13 is coaxial with aluminum barrel 11, and aluminum barrel 11 bottom surface is welded with V-type plate 9, and V-type plate 9 and bottom surface normal direction angle are less than 30 °.The effect of V-type plate 9 reduces the electronic secondary effect caused due to propelling unit 12 plume bombardment Faraday cage bottom surface.
The plume signal that signal picker 5 is collected for gathering aluminum barrel 11.
Set forth below, the high-temperature infrared of a kind of set composite for space environment simulation vacuum apparatus of the present invention toasts out airway dysfunction.
Aluminum barrel 11 is made up of hard aluminium alloy material, has the advantage that coefficient of thermal conductivity is high, radiation coefficient is high, is conducive to giving vent to anger to the corrosion-resistant steel wall baking of vacuum chamber 14.
Aluminum barrel 11 has higher infrared emittance and absorptivity, with aluminum barrel 11 for infrared heating body, realizes giving vent to anger to the high-temperature baking of vacuum chamber 14 wall and inner structure, effective gas clean-up.
The outside wall surface of aluminum barrel 11 is provided with the insulated tape heating element 17 of flat, described insulated tape heating element 17 is looped around in the outside wall surface of aluminum barrel 11, the outer side covers aluminum alloy thin layer of described insulated tape heating element 17, is welded to connect with aluminum barrel, insulated tape heating element 17 and aluminum barrel 11 High-Voltage Insulation.
Described insulated tape heating element 17 is connected with insulated tape heating element power supply 1, provides energy by insulated tape heating element power supply 1, heating-up temperature can be greater than 250 DEG C.
The outside wall surface of aluminum barrel 11 is provided with temperature switch 15, and described temperature switch 15 is the normally closed mechanical switch in Kick type contact, and kick temperature switch, is distributed in the outside wall surface of aluminum barrel 11, with the terminal series-shunt of insulated tape heating element 17, for preventing temperature too high.
The external temperature thermocouple 2 of aluminum barrel 11, thermocouple 2 is affixed on the outside wall surface of aluminum barrel 11 and insulate with it, and aluminum barrel temperature is measured in the effect of thermocouple 2 in real time, temp controlled meter 3 is connected to through vacuum wall, temp controlled meter 3 is placed in the outside of vacuum chamber 14, and described temp controlled meter 3 is that 220V, PID control.Temp controlled meter 3 has optional pid parameter, self-tuning function,
Insulated tape heating element 17, temperature switch 15, thermocouple 2 and temp controlled meter 3 realize experimental section temperature control and heating functions.
In sum, a kind of set composite for space environment simulation vacuum apparatus of the present invention can realize the heat sink function of low temperature, plume total cross-section faraday collecting function, high-temperature infrared toast out airway dysfunction.
In the present embodiment, internal vacuum chamber diameter 800mm, long 1200mm.The composite molecular pump of vacuum pump group used to be a pumping speed be 1600L/s and pumping speed are the blade mechanical pump of 14L/s.
Through baking in 24 hours of the present invention, final vacuum can be 3.0 × 10
-5pa, runs degree of vacuum and is less than 1.0 × 10
-4pa, is better than vacuum chamber of the same type.
End vacuum can be regenerated by baking.Because in experiment, material and greasy dirt are given vent to anger, long-time running final vacuum degree rises to 3.0 × 10
-4pa, carries out after 200 DEG C of 24h baking gives vent to anger, can returning to 3.0 × 10
-5pa.
Heating of the present invention and refrigeration adhere to two cover autonomous systems separately, and heating efficiency is high, and during 200 DEG C of bakings, baking power is less than 2kW.
Common heat sink temperature end 150 DEG C, the present invention can reach 250 DEG C, effectively improves baking outgassing rate.
Therefore, the integrated three kinds of functions of the present invention are in a device, make that aluminum barrel 11 is heat sink can be operated in-190 DEG C to 250 DEG C, and insulate with the earth and vacuum chamber 14, realize that high/low temperature is heat sink, plume total cross-section faraday collects and high-temperature infrared baking is given vent to anger the set composite of three kinds of functions, its structure is simple, save space, economical and practical, and the effective measures of vacuum apparatus cost and over-the-road expense can be reduced.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (7)
1. for a set composite for space environment simulation vacuum apparatus, it is characterized in that, comprise aluminum barrel, described aluminum barrel is arranged in vacuum chamber; Electric propulsion device, described electric propulsion device is arranged in vacuum chamber, and it is anterior to be positioned at aluminum barrel open end; V-type plate, described V-type plate is arranged on the bottom surface of one end of aluminum barrel;
Insulated tape heating element, described insulated tape heating element is connected with insulated tape heating element power supply, and described insulated tape heating element is distributed in aluminum barrel outside wall surface;
Temperature switch, described temperature switch is arranged in the outside wall surface of aluminum barrel;
Thermocouple, described thermocouple is placed on aluminum barrel outside wall surface, and described thermocouple connects temp controlled meter;
Signal picker, described signal picker is connected with deflection power and aluminum barrel by high temperature wire;
Refrigerant pipe, described refrigerant pipe is distributed in the outer wall surface of aluminum barrel, and described refrigerant pipe connects bellows, and described bellows is connected with the refrigerator be arranged on outside vacuum chamber.
2. a kind of set composite for space environment simulation vacuum apparatus as claimed in claim 1, it is characterized in that, described V-type plate and aluminum barrel bottom surface normal direction angle are less than 30 °.
3. a kind of set composite for space environment simulation vacuum apparatus as claimed in claim 1, it is characterized in that, described aluminum barrel is connected by insulating supporting with vacuum chamber.
4. a kind of set composite for space environment simulation vacuum apparatus as claimed in claim 1, it is characterized in that, described temperature switch is the normally closed mechanical switch in Kick type contact.
5. a kind of set composite for space environment simulation vacuum apparatus as claimed in claim 1, it is characterized in that, described refrigerant pipe is made up of red copper or stainless steel material, and it is wrapped with thermal insulation layer, insulate with aluminum barrel.
6. a kind of set composite for space environment simulation vacuum apparatus as claimed in claim 1, it is characterized in that, described aluminum barrel is made up of hard aluminium alloy material, its outside wall surface polishing, internal face blackening process.
7. a kind of set composite for space environment simulation vacuum apparatus as claimed in claim 1, it is characterized in that, described electric propulsion device is ion-conductance propelling unit.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310163396.7A CN103287590B (en) | 2013-05-07 | 2013-05-07 | A kind of set composite for space environment simulation vacuum apparatus |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310163396.7A CN103287590B (en) | 2013-05-07 | 2013-05-07 | A kind of set composite for space environment simulation vacuum apparatus |
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| CN103287590A CN103287590A (en) | 2013-09-11 |
| CN103287590B true CN103287590B (en) | 2015-10-07 |
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Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103538734A (en) * | 2013-09-23 | 2014-01-29 | 上海卫星装备研究所 | Infrared heating cage hanging device |
| CN104210678A (en) * | 2014-09-17 | 2014-12-17 | 九江精密测试技术研究所 | Two-dimensional turntable system under vacuum temperature change environment |
| 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 |
| CN105716892A (en) * | 2016-02-01 | 2016-06-29 | 西安交通大学 | Ground simulating experimental device for 3D printing in space environment |
| CN106092512A (en) * | 2016-06-12 | 2016-11-09 | 中国电子科技集团公司第八研究所 | A kind of irradiation, thermal vacuum and high/low temperature integrated synthesis multichannel on-line monitoring system |
| 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 |
| CN108263623A (en) * | 2017-01-03 | 2018-07-10 | 北京机电工程研究所 | A kind of cruising missile deck store structure |
| CN106802125B (en) * | 2017-01-24 | 2020-02-11 | 上海空间推进研究所 | Method for determining thrust vector eccentricity of electric thruster for spacecraft |
| CN108195478A (en) * | 2018-03-30 | 2018-06-22 | 中国计量科学研究院 | A kind of device of temperature survey |
| 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 |
| CN109460086A (en) * | 2018-12-26 | 2019-03-12 | 仪晟科学仪器(嘉兴)有限公司 | Multi-channel intelligent temperature control vacuum system apparatus for baking |
| CN109855792B (en) * | 2019-01-21 | 2021-03-02 | 北京卫星环境工程研究所 | Plume particle sedimentation protection device for electric propulsion test and vacuum test system thereof |
| CN111966145B (en) * | 2020-07-01 | 2021-06-11 | 北京卫星制造厂有限公司 | High-precision in-plane temperature control system in vacuum environment |
| CN112522676B (en) * | 2020-11-05 | 2021-08-31 | 中国科学院力学研究所 | Space magnetron sputtering coating device |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3405561A (en) * | 1964-09-29 | 1968-10-15 | Lummus Co | Flight simulator |
| JP3069909B2 (en) * | 1990-10-18 | 2000-07-24 | 日本酸素株式会社 | Space environment test equipment |
| CN101539481B (en) * | 2009-04-17 | 2010-09-08 | 北京航空航天大学 | Plume diagnosis device of electric propulsion engine |
| CN201637485U (en) * | 2010-04-09 | 2010-11-17 | 中国科学院上海技术物理研究所 | Testing device for testing affect of vacuum plume on infrared laser characteristics |
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