CN102092482A - Cooling device for loop heat pipe of satellite borne equipment - Google Patents
Cooling device for loop heat pipe of satellite borne equipment Download PDFInfo
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- CN102092482A CN102092482A CN2009102003249A CN200910200324A CN102092482A CN 102092482 A CN102092482 A CN 102092482A CN 2009102003249 A CN2009102003249 A CN 2009102003249A CN 200910200324 A CN200910200324 A CN 200910200324A CN 102092482 A CN102092482 A CN 102092482A
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- electric heater
- exciter
- heat pipe
- evaporator
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Abstract
The invention discloses a cooling device for a loop heat pipe of satellite borne equipment, which comprises an evaporator (1), a capillary wick (2), an air pipeline (5), a radiator (7), a liquid pipeline (9) and a reservoir (3), wherein the reservoir (3) is provided with a semiconductor cooler (4); an air pipe electric heater (6) is coiled around the air pipeline (5); the radiator (7) is provided with a radiator compensation electric heater (8); the reservoir (3) is provided with a reservoir electric heater (10); the cooler and the electric heaters are connected with a thermal control subsystem; a thermistor temperature measurer is arranged on the evaporator (1), the radiator (7) and an embedded heat pipe and is connected with a thermal control subsystem; and all the pipelines are cladded by a plurality of layers of thermal insulation materials. The invention solves the problem of active control of the cooling device for satellite borne equipment, and has the advantages of high control capability, reasonability and feasibility for application, stability and reliability for operation, and the like.
Description
Technical field
The present invention relates to the loop circuit heat pipe heat sink of satellite carried equipment.
Background technology
Development along with satellite technology, especially at the satellite in various follow-up model satellites and the planning at present, have more than the satellite borne equipment and complicated, high, the characteristics such as cal val significantly increases, temperature control requirement height of survey precision requirement, traditional hot control device based on Passive Control can not adapt to fully, must come the active adjustment ability of further raising system by the thermal control technology of upgrading, improve temperature conditions, guarantee reliability and accuracy that satellite borne equipment uses, improve the reliability of the whole star of satellite, prolong satellite life.So-called initiatively heat control technology is under the inside and outside environment that changes, and utilizes certain autonomous cruise speed system, automatically regulates various relevant heat transfer parameters, and the instrument and equipment operating temperature in the spacecraft is kept within the limits prescribed.Compare with passive thermal control, its characteristics are exactly the characteristic parameter that can initiatively change heat exchange according to the requirement of temperature.
The structure and the working process of the loop circuit heat pipe heat sink of prior art are as follows: evaporator is installed on spaceborne instrument and equipment or the pre-buried heat pipe of satellite instrument plate, and the heat of instrument and equipment and satellite is delivered to the in-to-in capillary wick by the saddle of evaporator; Capillary wick in-to-in working medium ammonia absorbs heat of vaporization, on the exciter of steam outside air pipe flows to star; Exciter is directly facing to cold space, and gas progressively discharges the latent heat of vaporization and is condensed into liquid when the exciter pipeline flows; Liquid is back to along liquid pipeline and enters evaporator after reservoir compiles.
When heat sink started, action principle was the same with heat pipe, by working medium constantly circulation between evaporator and exciter, took away the unnecessary heat on celestial body or the spaceborne instrument and equipment, reached the temperature control purpose.During the heat sink blocking-up: have big resistance in the pipeline, do not have working medium to flow substantially, do not form working medium and circulate, cause heat sink not play the effect of transmission heat, make the heat of instrument and equipment be unlikely to excessively to scatter and disappear.
Therefore the loop circuit heat pipe heat sink of prior art is based on Passive Control, and often when satellite borne equipment need be lowered the temperature, loop circuit heat pipe can not effectively start work; When the satellite borne equipment temperature is on the low side, can not reliably block again; Thereby cause that satellite equipment is impaired.
Summary of the invention
For a series of problems that the heat sink that solves prior art brings owing to Passive Control, the object of the present invention is to provide a kind of loop circuit heat pipe heat sink of satellite carried equipment.Utilize the present invention, can start effectively in time or blocking-up loop circuit heat pipe heat sink, reach the purpose of ACTIVE CONTROL satellite borne equipment temperature according to the working condition that detects.
In order to reach the foregoing invention purpose, the technical scheme that the present invention is adopted for its technical matters of solution provides a kind of loop circuit heat pipe heat sink of satellite carried equipment, and this device comprises: evaporator, capillary wick, air pipe, exciter, liquid pipeline, reservoir; According to the present invention, this device also comprises:
A semiconductor cooler also is installed on reservoir; Around air pipe, also be wound with the tracheae electric heater; Exciter compensation electric heater also is installed on exciter; The reservoir electric heater also is installed on reservoir; Outside all pipelines, also be coated with multilayer insulation material; Evaporator, exciter and pre-buried heat pipe are provided with the thermistor temperature detecting element, are connected with a thermal control subsystem; Thermal control subsystem also is connected with above-mentioned semiconductor cooler, tracheae electric heater, exciter compensation electric heater, reservoir electric heater, by temperature element monitoring evaporator, exciter and pre-buried heat pipe in the rail temperature, control the startup and the blocking-up of described loop circuit heat pipe heat sink.
The loop circuit heat pipe heat sink of the satellite carried equipment of the present invention, by initiatively utilizations of thermal control measure such as electric heaters on thermal control subsystem, heat sink and the star, solved the initiative control of spaceborne instrument and equipment heat sink, the temperature of the satellite carried instrument and equipment of control that can be good satisfies the temperature index that totally provides.By using proof, the present invention has obtained beneficial effects such as control ability is strong, utilization is rationally feasible, stable and reliable operation.
Description of drawings
Fig. 1 is the structural representation of the loop circuit heat pipe heat sink of the satellite carried equipment of the present invention;
Be labeled as among the figure: the 1-evaporator; The 2-capillary wick; The 3-reservoir; The 4-semiconductor cooler; The 5-air pipe; 6-tracheae electric heater; The 7-exciter; 8-exciter compensation electric heater; The 9-liquid pipeline; 10-reservoir electric heater.
Fig. 2 is the test curve figure of heat sink starting state of the present invention.
The specific embodiment
Below in conjunction with description of drawings the preferred embodiments of the present invention.
Fig. 1 is the structural representation of the loop circuit heat pipe heat sink of the satellite carried equipment of the present invention, and shown in the embodiment of Fig. 1, this device comprises:
The prior art part: evaporator 1 is installed on spaceborne instrument and equipment or the pre-buried heat pipe of satellite instrument plate, has capillary wick 2 in the evaporator 1, and capillary wick 2 inside are filled with working medium ammonia; Capillary wick 2 in-to-in working medium ammonia absorb heat of vaporization and produce steam by air pipe 5, and steam is on air pipe 5 flows to exciter 7 outside the star; Exciter 7 progressively discharges the latent heat of vaporization when the pipeline of gas on exciter flows and is condensed into liquid directly facing to cold space; Liquid is back to reservoir 3 along liquid pipeline 9, enters the capillary wick 2 in the evaporator 1 after compiling, and for capillary wick 2 provides liquefied ammonia, constitutes heat-radiation loop.
When heat sink started, action principle was the same with heat pipe, by working medium constantly circulation between evaporator and exciter, took away the unnecessary heat on celestial body or the spaceborne instrument and equipment, reached the temperature control purpose.During the heat sink blocking-up: have big resistance in the pipeline, do not have working medium to flow substantially, do not form working medium and circulate, cause heat sink not play the effect of transmission heat.
The heat sink of above-mentioned prior art often can not in time start or block based on Passive Control, therefore, and less stable.
In order to allow the heat sink can safe and reliable stable work, the present invention have increased the function of ACTIVE CONTROL; According to the present invention, a semiconductor cooler 4 has been installed also on reservoir 3; Around air pipe 5 also coiling tracheae electric heater 6; Exciter compensation electric heater 8 also has been installed on exciter 7; Reservoir electric heater 10 also has been installed on reservoir 3; And outside all pipelines, also be coated with multilayer insulation material; Evaporator 1, exciter 7 and pre-buried heat pipe are provided with the thermistor temperature detecting element, are connected with a thermal control subsystem; Thermal control subsystem also is connected with above-mentioned semiconductor cooler 4, tracheae electric heater 6, exciter compensation electric heater 8, reservoir electric heater 10, by the mode of operation at rail temperature, analysis heat sink of temperature element monitoring evaporator 1, exciter 7 and pre-buried heat pipe, control the startup and the blocking-up of described loop circuit heat pipe heat sink timely and effectively.
Fig. 2 is the test curve figure of heat sink starting state of the present invention, as shown in Figure 2, and when temperature is lower than subzero 5 when spending, the blocking-up of this heat sink; When temperature is higher than 5 when spending, this heat sink starts; Thereby make satellite borne equipment reliably maintain low-temperature condition.This evidence, the present invention have obtained following beneficial effect:
1. the result of associated hot analytical calculation shows, can reduce satellite temperature effectively during heat sink startup work of the present invention.
Ground repeatedly know the real situation test and satellite first sample star, just sample star thermal balance test shows that thermal control subsystem has stronger control ability to this heat sink, can control the startup and the blocking-up of this device according to the service condition of satellite.
3. repeatedly know the real situation through ground and test and satellite first sample star, positive sample star thermal balance test and Heaven flight experiment, draw after the analysis related data: open heat sink when satellite temperature is higher, satellite just has stronger cooling ability; Blocking-up heat sink when satellite temperature is low can actv. stops the loss of heat.
Claims (1)
1. the loop circuit heat pipe heat sink of a satellite carried equipment comprises: evaporator [1], capillary wick [2], air pipe [5], exciter [7], liquid pipeline [9], reservoir [3]; It is characterized in that this device also comprises:
A semiconductor cooler [4] also is installed on reservoir [3]; Around air pipe [5], also be wound with tracheae electric heater [6]; Exciter compensation electric heater [8] also is installed on exciter [7]; Reservoir electric heater [10] also is installed on reservoir [3]; Outside all pipelines, also be coated with multilayer insulation material; Evaporator [1], exciter [7] and pre-buried heat pipe are provided with the thermistor temperature detecting element, are connected with a thermal control subsystem; Described thermal control subsystem also is connected with above-mentioned semiconductor cooler [4], tracheae electric heater [6], exciter compensation electric heater [8], reservoir electric heater [10], by temperature element monitoring evaporator [1], exciter [7] and pre-buried heat pipe in the rail temperature, control the startup and the blocking-up of described loop circuit heat pipe heat sink.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102003249A CN102092482A (en) | 2009-12-11 | 2009-12-11 | Cooling device for loop heat pipe of satellite borne equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102003249A CN102092482A (en) | 2009-12-11 | 2009-12-11 | Cooling device for loop heat pipe of satellite borne equipment |
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| CN102092482A true CN102092482A (en) | 2011-06-15 |
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| CN2009102003249A Pending CN102092482A (en) | 2009-12-11 | 2009-12-11 | Cooling device for loop heat pipe of satellite borne equipment |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103256841A (en) * | 2013-04-25 | 2013-08-21 | 上海卫星工程研究所 | Novel energy storage cooling device |
| CN104501473A (en) * | 2014-12-02 | 2015-04-08 | 北京空间飞行器总体设计部 | Matching designing method of evaporator adapting to heat shock |
| CN105383714A (en) * | 2015-11-27 | 2016-03-09 | 上海卫星工程研究所 | Satellite borne active temperature control system |
| CN105523198A (en) * | 2015-12-22 | 2016-04-27 | 中国科学院长春光学精密机械与物理研究所 | Space heat pipe radiator based on loop heat pipe |
| CN107994890A (en) * | 2017-12-28 | 2018-05-04 | 中国科学院西安光学精密机械研究所 | Spaceborne refrigerating device controller internal reset circuit and method based on anti-fuse FPGA |
| US10225953B2 (en) | 2014-10-31 | 2019-03-05 | Thermal Corp. | Vehicle thermal management system |
| CN113815908A (en) * | 2020-11-05 | 2021-12-21 | 山东大学 | Intelligent heat-preservation loop heat pipe and thermal control system thereof |
| CN113815905A (en) * | 2020-11-05 | 2021-12-21 | 山东大学 | Composite thermal control system of aerospace loop heat pipe radiator |
| CN116067211A (en) * | 2021-11-02 | 2023-05-05 | 山东大学 | Loop heat pipe provided with thermoelectric refrigerator |
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| US20070175615A1 (en) * | 2006-01-30 | 2007-08-02 | Jaffe Limited | Loop heat pipe |
| CN201260287Y (en) * | 2008-10-09 | 2009-06-17 | 纬创资通股份有限公司 | Heat radiating module and electronic device having the module |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103256841A (en) * | 2013-04-25 | 2013-08-21 | 上海卫星工程研究所 | Novel energy storage cooling device |
| CN103256841B (en) * | 2013-04-25 | 2016-05-11 | 上海卫星工程研究所 | A kind of energy storage heat abstractor |
| US10225953B2 (en) | 2014-10-31 | 2019-03-05 | Thermal Corp. | Vehicle thermal management system |
| US10932392B2 (en) | 2014-10-31 | 2021-02-23 | Aavid Thermal Corp. | Vehicle thermal management system |
| CN104501473A (en) * | 2014-12-02 | 2015-04-08 | 北京空间飞行器总体设计部 | Matching designing method of evaporator adapting to heat shock |
| CN104501473B (en) * | 2014-12-02 | 2016-03-30 | 北京空间飞行器总体设计部 | A kind of evaporimeter adaptation design method adapting to thermal shock |
| CN105383714A (en) * | 2015-11-27 | 2016-03-09 | 上海卫星工程研究所 | Satellite borne active temperature control system |
| CN105523198A (en) * | 2015-12-22 | 2016-04-27 | 中国科学院长春光学精密机械与物理研究所 | Space heat pipe radiator based on loop heat pipe |
| CN107994890A (en) * | 2017-12-28 | 2018-05-04 | 中国科学院西安光学精密机械研究所 | Spaceborne refrigerating device controller internal reset circuit and method based on anti-fuse FPGA |
| CN107994890B (en) * | 2017-12-28 | 2023-09-01 | 中国科学院西安光学精密机械研究所 | Internal reset circuit and method for satellite-borne refrigerator controller based on anti-fuse FPGA |
| CN113815908A (en) * | 2020-11-05 | 2021-12-21 | 山东大学 | Intelligent heat-preservation loop heat pipe and thermal control system thereof |
| CN113815905A (en) * | 2020-11-05 | 2021-12-21 | 山东大学 | Composite thermal control system of aerospace loop heat pipe radiator |
| CN113815905B (en) * | 2020-11-05 | 2024-01-30 | 山东大学 | Composite thermal control system of spaceflight loop heat pipe radiator |
| CN113815908B (en) * | 2020-11-05 | 2024-03-08 | 山东大学 | Intelligent heat-preserving loop heat pipe and heat control system thereof |
| CN116067211A (en) * | 2021-11-02 | 2023-05-05 | 山东大学 | Loop heat pipe provided with thermoelectric refrigerator |
| CN116067211B (en) * | 2021-11-02 | 2024-03-01 | 山东大学 | Loop heat pipe provided with thermoelectric refrigerator |
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Application publication date: 20110615 |