CN201348569Y - Space ship environment simulation test device utilizing mixed work substance refrigerating technology - Google Patents
Space ship environment simulation test device utilizing mixed work substance refrigerating technology Download PDFInfo
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- CN201348569Y CN201348569Y CNU200820199023XU CN200820199023U CN201348569Y CN 201348569 Y CN201348569 Y CN 201348569Y CN U200820199023X U CNU200820199023X U CN U200820199023XU CN 200820199023 U CN200820199023 U CN 200820199023U CN 201348569 Y CN201348569 Y CN 201348569Y
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Abstract
The utility model relates to a space ship environment simulation test device utilizing mixed work substance refrigerating technology, which comprises a vacuum container, a heat sink, a mixed work substance refrigerating system, a vacuum air pumping system and a measuring and controlling system, and is characterized in that the mixed work substance refrigerating system consists of a compressor, an oil separator, a condenser, an evaporator, a pressure relief electromagnetic valve, an air return manual valve, a defrosting electromagnetic valve, a defrosting manual valve, a refrigerating electromagnetic valve, a refrigerating manual valve, a four-level capillary pipe and an inflation barrel, and the refrigerating system is provided with local panel manual control and a remote control operations and is also provided with a digital temperature display device, a ten-level thermoelectric couple selecting switch and a plurality of alarming systems. The mixed work substance refrigerating system is utilized to substitute the traditional liquefied nitrogen flow procedures, thereby saving the test expense, and simplifying the test operation, and setting a foundation for the full-automatic-control and unattended operation environment device, and improving the thermal vacuum test capacity of the space ship components in China.
Description
Technical field
The utility model relates to a kind of spacecraft hot vacuum environment simulated test facility, relates in particular to the spacecraft environment simulated test facility of having used the mixed working fluid Refrigeration Technique.
Background technology
Parts hot vacuum environment simulated test facility is mainly used in the low pressure discharge test and the thermal vacuum test of spacecraft standalone component.By verifying that the spacecraft standalone component stands the ability of hot vacuum environment, check the rationality of its design, expose the components and parts of assembly and the defective of material and technology.Refrigerator system is one of major part in the simulated test facility, and the working medium of using in refrigerator system at present is liquid nitrogen normally, and this system operation complexity is made and the operating cost height, is unfavorable for carrying out of parts thermal vacuum test.
Summary of the invention
The purpose of this utility model provides a kind of spacecraft environment simulated test facility, it adopts the Using Mixed Refrigerants system to replace the liquid nitrogen flow process, save the test funds, the short form test operation, for develop full automatic control, unattended ring mould equipment is laid a good foundation, and has improved the parts thermal vacuum test ability of China.
Of the present utility model can finishing by following technical scheme:
A kind of spacecraft environment simulated test facility of application mix working medium Refrigeration Technique, described simulated test facility comprises vacuum tank, heat sink, the mixed working fluid refrigeration system, vacuum-pumping system, TT﹠C system, the mixed working fluid refrigeration system is by compressor, oil separator, condenser, evaporator, unload pressure electromagnetic valve, return-air hand valve, the defrosting solenoid valve, defrosting hand valve, the refrigeration solenoid valve, refrigeration hand valve, the level Four kapillary and the bucket that expands are formed, the mix refrigerant of five kinds of freon compositions passes through compressor successively, oil separator, condenser, the level Four kapillary, evaporator, behind the return-air hand valve, reenter the new refrigeration cycle of compressor starts, series connection is provided with refrigeration solenoid valve and refrigeration hand valve between level Four kapillary and the evaporator, defrosting solenoid valve and the series connection of defrosting hand valve, be connected in parallel on the two ends of level Four kapillary and evaporator then, bucket and unload the pressure electromagnetic valve series connection expands, be connected in parallel on the two ends of evaporator and oil separator then, refrigeration system has local panel manually control and Remote operation, and has a digital temperature indicator, ten grades of thermopair selector switch and multiple warning system.
The beneficial effects of the utility model are:
A. this device first adopts Using Mixed Refrigerants system, has replaced the liquid nitrogen flow process, is first equipment that adopts the mixed working substance refrigeration machine to make heat sink reaching-130 ℃ in present China satellite parts thermal vacuum test facility;
B. this equipment adopts centralized control system, can carry out Centralized Monitoring to many same categories of device, and the automatic control level of equipment is the advanced level in the present domestic thermal vacuum test facility;
C. this equipment adopts advanced oil-free vacuum air-extractor, is the thermal vacuum test facility that does not have oil fully that present China is used for the test of satellite parts.
Description of drawings
Fig. 1 is the rotating mechanism synoptic diagram at vacuum tank gate.
Fig. 2 is the A-A diagrammatic cross-section of Fig. 1.
Fig. 3 is heat sink layout synoptic diagram.
Fig. 4 is the left view of Fig. 3.
Fig. 5 is the pipeline spacing figure of heat sink coil pipe.
Fig. 6 is a mixed working substance refrigeration system process flow diagram.
Fig. 7 is mixed working substance refrigeration machine PFC-1100HC refrigerating capacity and temperature relation figure.
Fig. 8 is the arrangenent diagram of infrared cage in heat sink.
Fig. 9 is the spacecraft environment simulated test facility front elevation of application mix working medium Refrigeration Technique.
Figure 10 is the spacecraft environment simulated test facility side view of application mix working medium Refrigeration Technique.
Figure 11 is the spacecraft environment simulated test facility vertical view of application mix working medium Refrigeration Technique.
Wherein, 1 is the gate, 2 is cylindrical shell, 3 is nut, 4 is bearing inner race, 5 is bearing outer ring, 6 is spring, 7 is the manual adjustments nut, 8 is heat sink, 9 is barricade, 10 is ring beam, 11 is mat insulation, 12 is guide rail, 13 is compressor, 14 is oil separator, 15 is condenser, 16 is evaporator, 17 for unloading pressure electromagnetic valve, 18 is return-air hand valve, 19 are the defrosting solenoid valve, 20 are defrosting hand valve, 21 are the refrigeration solenoid valve, 22 are refrigeration hand valve, 23 is the infrared cage of cylinder, 24 side's of being plates, 25 is the support platform dolly, and 26 is kapillary, 27 are the bucket that expands, 28 is vacuum tank, 30 is refrigeration system, 31 is infrared cage, 32 is vacuum-pumping system, 33 is TT﹠C system.
Embodiment
Below in conjunction with accompanying drawing the utility model is elaborated.
Referring to Fig. 9-Figure 11, adopt the parts hot vacuum environment simulated test facility of mixed working fluid Refrigeration Technique mainly to comprise five parts, that is: vacuum tank 28, heat sink 8, refrigeration system 30, vacuum-pumping system 32 and TT﹠C system 33.
Arrange at the cylindrical tube of vacuum tank 28 and dished (torispherical) head end heat sink 8, place, gate arranging shielding plate 9, as shown in Figure 3 and Figure 4.Test specimen is placed on heat sink inside.Heat sink 8 is horizontal heat sinks of cylindrical tube, and its end face near the vacuum tank gate is open, near the end face sealing of dished (torispherical) head.Cylindrical tube is selected thin-walled part, to reduce weight.A copper material coil pipe is flatly along the snakelike coiling of whole wallboard inwall, and links to each other with the coil pipe of the snakelike coiling of level that is provided with on the end face near dished (torispherical) head.Connect with silver-alloy brazing between coil pipe and the wallboard.Be equipped with perforate in the corresponding positions that cooperates with vacuum tank on the heat sink wall panel.The heat sink outside has ring beam 10 to surround heat sink wall panel, is equipped with mat insulation 11 on the ring beam 10 and is supported on the guide rail 12 of vacuum tank 28, and guide rail 12 can be sent in the vacuum tank 28 heat sink easily.The vacuum tank material uses stainless steel, soldering copper plate structure on the heat sink employing copper pipe, and the inside surface japanning,, hemisphere surface emissivity＞0.90.Gate barricade 9 is a plectane, and it is bright and clean that whole ground plane keeps.Barricade is furnished with angle aluminium as reinforcement towards the direction japanning of test specimen facing to vessel faces.On the end socket at gate 1 web member is installed, barricade is hung on the end socket by reinforcement.
In order to make heat sink temperature even, must limit adjacent two the pipeline T1 point temperature differences of adjacent two pipeline mid point T2 point temperature of coil pipe with this, determine the pipeline spacing by temperature difference.The design pipeline spacing of this testing equipment is got l=135mm, and referring to Fig. 5, q is the unit area thermal load, and b is a heat sink wall panel thickness.
Mixed working fluid refrigeration system 30 by compressor 13, oil separator 14, condenser 15, evaporator 16, unload pressure electromagnetic valve 17, return-air hand valve 18, defrosting solenoid valve 19, defrosting hand valve 20, refrigeration solenoid valve 21, refrigeration hand valve 22, level Four kapillary 26 and the bucket 27 that expands and form, cold-producing medium is mixed by five kinds of freon, and the refrigeration system flow process as shown in Figure 6.Cold-producing medium enters oil separator 14 after the adiabatic compression in compressor 13, enter in the condenser 15 by the cold-producing medium after the oil removal treatment and to cool off heat release, adiabatic expansion and step-down in level Four kapillary 26, cooling subsequently, after the cold-producing medium of low-temp low-pressure enters evaporator 16 heat absorptions, by return-air hand valve 18, enter the new refrigeration cycle of compressor 13 beginnings at last.Series connection is provided with refrigeration solenoid valve 21 and refrigeration hand valve 22 between level Four kapillary 26 and the evaporator 16, is used for controlling the keying of refrigeration.Defrosting solenoid valve 19 and 20 series connection of defrosting hand valve are connected in parallel on the two ends of level Four kapillary 26 and evaporator 16 then, keep the operate as normal of level Four kapillary 26 and evaporator 16 under the low-temperature condition.Expand bucket 27 and unload pressure electromagnetic valve 17 series connection is connected in parallel on the two ends of evaporator 16 and oil separator 14 then.Refrigeration system provides heat sink low-temperature receiver, heat sink cryogenic temperature≤-130 ℃, and top pressure is lower than 1.6MPa, heat sink maximum heating load 2kW.
The refrigeration machine that the mixed working fluid refrigeration system is selected for use, its refrigerating capacity curve as shown in Figure 7, refrigerating capacity was the requirement of 430W when it can satisfy-130 ℃.Heat sink when worst hot case the thermal load maximum, be 2000W.Refrigeration machine can be realized local panel manually control and Remote operation.Refrigeration machine has a digital temperature indicator and ten grades of thermopair selector switch.Regulating selector switch can be in the remote supervision system variation of temperature, and temperature monitoring comprises that compressor temperature, condenser temperature, heat sink temperature in, heat sink outlet temperature, cold-producing medium output temperature, cold-producing medium return temperature, refrigeration built-in temperature etc.Refrigeration machine has that compressor pressure is low excessively, compressor pressure is too high, compressor temperature is too high, do not have chilled water or warnings such as discharge reduction, refluence or condenser inner product dilutional hyponatremia.
The air leakage of system mainly determined by the end vacuum and the working pressure of vacuum tank, generally chooses to be lower than 1/10th of gas load under the duty.According to the result of calculation of unloaded final vacuum of the vacuum tank of technical requirement and effective pumping speed, the cryopump that decision is equipped with a pumping speed 10000L/s is that the dried pump of 70L/s is slightly taken out as the main pump, pumping speed taken out.External cryopump links to each other with container by two-way seal insert plate valve and short tube tube.Heat sink be under-130 ℃ the situation, the extreme pressure of system is better than 2.7 * 10 in 5 hours
-5Pa.Select for use ZJ-52T type Pirani gauge and ZJ-27 type hot cathode ioization gauge to use as measuring vessel vacuum tightness.Select for use ZJ-52T type Pirani gauge that the vacuum tightness in the pipeline is monitored on the pipeline slightly taking out.Selecting for use corresponding vacuum meter ZDF-X-LED to regulate simultaneously three of being equipped with on the equipment in addition measures.Vacuum meter all is furnished with the RS232 interface and is connected with computing machine, realizes functions such as data storage, printing.
The test specimen heating arrangement is an infrared heating cage.Infrared cage 31 is arranged in heat sink 8 inside, and before in the face of the direction at vacuum tank 28 gates 1 being, infrared cage 31 is divided into three: the infrared cage in front, the infrared cage 23 of cylinder, rear end face aluminium sheet, aluminium sheet is towards japanning of test specimen.The infrared cage in front is a movable plate, and bolt connects, and can open.Adopt the wide heating tape of 6mm, the infrared cage 23 of cylinder is divided into four tunnel heating, the infrared cage in front is one tunnel heating.The side of being welded with, the bottom plate 24 of infrared cage, on open circular hole, available bolt and support platform dolly 25 is fixing, test specimen places on the support platform dolly.The arrangenent diagram of infrared cage in heat sink as shown in Figure 8.
Heat sink temperature is lower than-130 ℃, and the testpieces temperature controlling range is-80 ℃～+ 100 ℃, measuring accuracy ± 0.5 ℃, and temperature control precision is ± 1 ℃.
After test specimen installs, the closing containers gate, the affirmation container is a closed state, opens dried pump, opens cryopump, closes dried pump after the cryopump precooling begins.Precooling needs three hours, after precooling finishes, opens and slightly takes out a mouthful valve, opens dried pump container is slightly taken out, and slightly takes out to reach below the 5Pa, closes and slightly takes out a mouthful valve, opens low temperature pumping hole valve and carries out fine pumping, and vacuum tightness reaches 10
-3After the Pa magnitude, open refrigeration machine, the vacuum tightness in the testing experiment process.
After opening refrigeration machine, test specimen begins cooling, drop to-80 ℃, PID begins from adjusting, adjust finish after, test specimen keep-80 ℃ one hour, begin then test specimen to be heated with the heating cage, heating rate＞0.5 ℃/min, test specimen is warmed up to+95 ℃ stopped one hour, realize after the circulation off-test.
After test is finished, close low temperature pumping hole valve, close refrigeration machine, can rise again to heat sink heating, open dried pump, cryopump is carried out bolt down procedure.After the cryopump bolt down procedure is finished, close dried pump, the closes compression air is closed cooling circulating water, powered-down.
Before equipment test, equipment has carried out unloaded vacuum test, and equipment slightly was extracted into the time of 1.3Pa less than 20 minutes, and unloaded vacuum tightness is 4.6 * 10
-5Pa, requirement touches the mark.Having under the situation of carrying, the end vacuum of equipment reaches 2.9 * 10
-5Pa.Equipment pressure does not all surpass 1.3 * 10
-3Pa, equipment vacuum tightness is the poorest to reach 8.8 * 10
-4Pa.
Field control cabinet and remote computer are formed two stage control system, realize the operation of equipment and the automatic detection and the control of entire test, can switch to complete manually control simultaneously.
Although above embodiment of the present utility model has been given to describe in detail and explanation; but what should indicate is; we can carry out various equivalences to above-mentioned embodiment according to conception of the present utility model and change and modification; when the function that it produced does not exceed spiritual that instructions and accompanying drawing contain yet, all should be within protection domain of the present utility model.
Claims (10)
1, a kind of spacecraft environment simulated test facility of application mix working medium Refrigeration Technique, described simulated test facility comprises vacuum tank (28), heat sink (8), mixed working fluid refrigeration system (30), vacuum-pumping system (32), TT﹠C system (33), it is characterized in that, mixed working fluid refrigeration system (30) is by compressor (13), oil separator (14), condenser (15), evaporator (16), unload pressure electromagnetic valve (17), return-air hand valve (18), defrosting solenoid valve (19), defrosting hand valve (20), refrigeration solenoid valve (21), refrigeration hand valve (22), the level Four kapillary (26) and the bucket (27) that expands are formed, the mix refrigerant of five kinds of freon compositions is successively by compressor (13), oil separator (14), condenser (15), level Four kapillary (26), evaporator (16), behind the return-air hand valve (18), reenter the new refrigeration cycle of compressor (13) beginning, series connection is provided with refrigeration solenoid valve (21) and refrigeration hand valve (22) between level Four kapillary (26) and the evaporator (16), defrosting solenoid valve (19) and defrosting hand valve (20) series connection, be connected in parallel on the two ends of level Four kapillary (26) and evaporator (16) then, bucket (27) and unload pressure electromagnetic valve (17) and connect expands, be connected in parallel on the two ends of evaporator (16) and oil separator (14) then, refrigeration system (30) has local panel manually control and Remote operation, and has a digital temperature indicator, ten grades of thermopair selector switch and multiple warning system.
2, simulated test facility as claimed in claim 1 is characterized in that, vacuum tank adopts horizontal type structure, and the stage casing is columniform cylindrical shell (2), and cylindrical shell one end is gate (1), and the other end is a dished (torispherical) head, and dished (torispherical) head is welded on the cylindrical shell (2).
3, simulated test facility as claimed in claim 2, it is characterized in that, the rotating mechanism at vacuum tank gate (1) is by nut (3) locking, separable bearing inner ring (4), outer ring (5) separately connect, realize the rotation at gate, be arranged on the axially-movable that spring (6) between gate (1) and the cylindrical shell (2) and manual adjustments nut (7) can be realized the relative cylindrical shell in gate (1) (2).
4, simulated test facility as claimed in claim 1, it is characterized in that, cylindrical tube (2) and dished (torispherical) head end at vacuum tank are arranged heat sink (8), place, gate arranging shielding plate (9), heat sink (8) are the horizontal heat sinks of cylindrical tube, its end face near vacuum tank gate (1) is open, near the end face sealing of dished (torispherical) head.
5, simulated test facility as claimed in claim 4, it is characterized in that, coil pipe is flatly along the snakelike coiling of cylindrical tube wallboard inwall of whole heat sink (8), and link to each other with the coil pipe of the snakelike coiling of level that is provided with on the end face near dished (torispherical) head, connect with silver-alloy brazing between coil pipe and the wallboard, be equipped with perforate in the corresponding positions that cooperates with vacuum tank on the wallboard, heat sink (8) outside has ring beam (10) to surround heat sink wall panel, be equipped with mat insulation (11) on the ring beam (10) and be supported on the guide rail (12) of vacuum tank heat sink (8) inside surface japanning.
6, simulated test facility as claimed in claim 5 is characterized in that, the spacing of adjacent two pipelines that heat sink (8) coil pipe forms is 135mm.
7, simulated test facility as claimed in claim 4, it is characterized in that, barricade (9) is a plectane, direction japanning towards test specimen, be furnished with angle aluminium as reinforcement facing to vessel faces, on the end socket at vacuum tank gate (1) web member is installed, barricade (9) is hung on the end socket by reinforcement.
8, simulated test facility as claimed in claim 1 is characterized in that, it is main pump that vacuum tank is selected cryopump for use, chooses the roughing vacuum pump of dried pump as system, and the vacuum meter of vacuum tank all is connected with computing machine.
9, simulated test facility as claimed in claim 1, it is characterized in that, heat sink (8) internal placement has infrared cage (31), and infrared cage (31) is divided into three: the infrared cage in front, the infrared cage of cylinder (23), rear end face aluminium sheet, and aluminium sheet is towards japanning of test specimen, the infrared cage in front is a movable plate, bolt connects, and can open the side of being welded with, the bottom plate (24) of infrared cage, on open circular hole, available bolt and support platform dolly (25) are fixing.
10, simulated test facility as claimed in claim 8 is characterized in that, adopts the wide heating tape of 6mm, and the infrared cage of cylinder (23) is divided into four tunnel heating, and the infrared cage in front is one tunnel heating.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU200820199023XU CN201348569Y (en) | 2008-12-29 | 2008-12-29 | Space ship environment simulation test device utilizing mixed work substance refrigerating technology |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU200820199023XU CN201348569Y (en) | 2008-12-29 | 2008-12-29 | Space ship environment simulation test device utilizing mixed work substance refrigerating technology |
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| CN102284790A (en) * | 2011-07-07 | 2011-12-21 | 中国科学院上海光学精密机械研究所 | Femtosecond laser micro-nano processing device capable of controlling gas atmosphere and processing method thereof |
| CN102451971A (en) * | 2010-10-20 | 2012-05-16 | 北京卫星环境工程研究所 | Manufacturing process for coiled copper heat sink for spacecraft thermal test |
| CN102680239A (en) * | 2012-05-09 | 2012-09-19 | 北京航空航天大学 | Semi-underground large-size horizontal vacuum container for plume test |
| CN102717903A (en) * | 2012-06-29 | 2012-10-10 | 北京卫星环境工程研究所 | Honeycomb type stainless steel expansion plate heat sink |
| CN102768548A (en) * | 2012-07-25 | 2012-11-07 | 北京卫星环境工程研究所 | Heat sink temperature control system and method for thermal vacuum test |
| CN102818978A (en) * | 2012-08-13 | 2012-12-12 | 北京合丰天成科技有限公司 | Satellite travelling-wave tube thermovacuum testing system |
| CN102890006A (en) * | 2012-10-24 | 2013-01-23 | 上海交通大学 | High/low temperature space environment simulating container with high temperature change rate |
| CN102967479A (en) * | 2012-11-13 | 2013-03-13 | 北京空间飞行器总体设计部 | System for testing water sublimator performance |
| CN103914092A (en) * | 2014-03-20 | 2014-07-09 | 航天东方红卫星有限公司 | Temperature control method for equipment on satellite in system level thermal vacuum test |
| CN104571183A (en) * | 2014-12-02 | 2015-04-29 | 兰州华宇航天技术应用有限责任公司 | Backheating gas mixed circulating refrigeration, heating and temperature adjustment system |
| CN105181900A (en) * | 2015-09-21 | 2015-12-23 | 北京航天长征飞行器研究所 | High-temperature thermal radiation testing device and method capable of synchronously and continuously adjusting large-volume temperature and pressure |
| CN104458475B (en) * | 2014-12-05 | 2017-03-15 | 北京卫星制造厂 | A kind of spacecraft thermal control unit product carries pressure cold shock testing method |
| CN108711332A (en) * | 2018-07-02 | 2018-10-26 | 常州市乐萌压力容器有限公司 | A kind of vacuum simulation space capsule |
| CN109115430A (en) * | 2018-07-02 | 2019-01-01 | 常州市乐萌压力容器有限公司 | A kind of vacuum simulation space capsule and its leak hunting method |
| CN112407347A (en) * | 2020-11-26 | 2021-02-26 | 上海卫星装备研究所 | Wide-temperature-range temperature control system of aerospace ring mold equipment |
| 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 |
| CN114212283A (en) * | 2021-12-17 | 2022-03-22 | 重庆哈丁环境试验技术股份有限公司 | Space environment simulation test box |
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| CN102451971A (en) * | 2010-10-20 | 2012-05-16 | 北京卫星环境工程研究所 | Manufacturing process for coiled copper heat sink for spacecraft thermal test |
| CN102451971B (en) * | 2010-10-20 | 2014-02-19 | 北京卫星环境工程研究所 | Manufacturing process for coiled copper heat sink for spacecraft thermal test |
| CN102284790A (en) * | 2011-07-07 | 2011-12-21 | 中国科学院上海光学精密机械研究所 | Femtosecond laser micro-nano processing device capable of controlling gas atmosphere and processing method thereof |
| CN102284790B (en) * | 2011-07-07 | 2014-05-07 | 中国科学院上海光学精密机械研究所 | Femtosecond laser micro-nano processing device capable of controlling gas atmosphere and processing method thereof |
| CN102680239A (en) * | 2012-05-09 | 2012-09-19 | 北京航空航天大学 | Semi-underground large-size horizontal vacuum container for plume test |
| CN102680239B (en) * | 2012-05-09 | 2014-06-18 | 北京航空航天大学 | Semi-underground large-size horizontal vacuum container for plume test |
| CN102717903A (en) * | 2012-06-29 | 2012-10-10 | 北京卫星环境工程研究所 | Honeycomb type stainless steel expansion plate heat sink |
| CN102717903B (en) * | 2012-06-29 | 2015-07-08 | 北京卫星环境工程研究所 | Honeycomb type stainless steel expansion plate heat sink |
| CN102768548B (en) * | 2012-07-25 | 2014-09-03 | 北京卫星环境工程研究所 | Heat sink temperature control system and method for thermal vacuum test |
| CN102768548A (en) * | 2012-07-25 | 2012-11-07 | 北京卫星环境工程研究所 | Heat sink temperature control system and method for thermal vacuum test |
| CN102818978A (en) * | 2012-08-13 | 2012-12-12 | 北京合丰天成科技有限公司 | Satellite travelling-wave tube thermovacuum testing system |
| CN102890006A (en) * | 2012-10-24 | 2013-01-23 | 上海交通大学 | High/low temperature space environment simulating container with high temperature change rate |
| CN102890006B (en) * | 2012-10-24 | 2015-09-30 | 上海交通大学 | A kind of high/low temperature space environment simulation container of high Cooling rate |
| CN102967479A (en) * | 2012-11-13 | 2013-03-13 | 北京空间飞行器总体设计部 | System for testing water sublimator performance |
| CN102967479B (en) * | 2012-11-13 | 2014-10-08 | 北京空间飞行器总体设计部 | System for testing water sublimator performance |
| CN103914092B (en) * | 2014-03-20 | 2016-03-02 | 航天东方红卫星有限公司 | System-level thermal vacuum test on-board equipment temperature-controlled process |
| CN103914092A (en) * | 2014-03-20 | 2014-07-09 | 航天东方红卫星有限公司 | Temperature control method for equipment on satellite in system level thermal vacuum test |
| CN104571183A (en) * | 2014-12-02 | 2015-04-29 | 兰州华宇航天技术应用有限责任公司 | Backheating gas mixed circulating refrigeration, heating and temperature adjustment system |
| CN104571183B (en) * | 2014-12-02 | 2016-10-12 | 兰州华宇航天技术应用有限责任公司 | A kind of back-heating type gas mixing circulation refrigeration heating thermoregulating system |
| CN104458475B (en) * | 2014-12-05 | 2017-03-15 | 北京卫星制造厂 | A kind of spacecraft thermal control unit product carries pressure cold shock testing method |
| CN105181900A (en) * | 2015-09-21 | 2015-12-23 | 北京航天长征飞行器研究所 | High-temperature thermal radiation testing device and method capable of synchronously and continuously adjusting large-volume temperature and pressure |
| CN108711332A (en) * | 2018-07-02 | 2018-10-26 | 常州市乐萌压力容器有限公司 | A kind of vacuum simulation space capsule |
| CN109115430A (en) * | 2018-07-02 | 2019-01-01 | 常州市乐萌压力容器有限公司 | A kind of vacuum simulation space capsule and its leak hunting method |
| CN112407347A (en) * | 2020-11-26 | 2021-02-26 | 上海卫星装备研究所 | Wide-temperature-range temperature control system of aerospace ring mold equipment |
| 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 |
| CN114212283A (en) * | 2021-12-17 | 2022-03-22 | 重庆哈丁环境试验技术股份有限公司 | Space environment simulation test box |
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