CN109649694B - Electrochromic thermal control mechanism - Google Patents
Electrochromic thermal control mechanism Download PDFInfo
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- CN109649694B CN109649694B CN201811560798.XA CN201811560798A CN109649694B CN 109649694 B CN109649694 B CN 109649694B CN 201811560798 A CN201811560798 A CN 201811560798A CN 109649694 B CN109649694 B CN 109649694B
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- thermal control
- electrode layer
- thermal
- control mechanism
- control unit
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
Abstract
The invention provides an electrochromic thermal control mechanism, wherein the upper surface of the thermal control mechanism is a transparent heat radiation surface, and the lower surface of the thermal control mechanism is a substrate; a plurality of thermal control units with electrochromism are closely arranged between the upper surface and the lower surface; a first electrode layer is arranged below the upper surface of each thermal control unit, a second electrode layer is arranged above the lower surface of each thermal control unit, and the polarities of the first electrode layer and the second electrode layer are opposite; a transparent hollow cylindrical box is arranged between the two electrode layers, a rotatable shaft is axially arranged at the center of the box, and semi-cylinders with opposite charges are respectively arranged on two cylindrical surfaces of the rotatable shaft. By controlling the polarity of the two electrode layers of each thermal control unit, the two semicylinders with opposite charges rotate to a target position according to electric field distribution, and therefore the thermal emissivity of the upper surface of the unit is controlled. The electrochromic thermal control mechanism has a simple structure and low power consumption, and can realize the various control of the surface thermal radiation emissivity of the whole mechanism by controlling the thermal emissivity of each unit, thereby flexibly and effectively controlling the temperature field of a satellite.
Description
Technical Field
The invention relates to the technical field of thermal control of spacecrafts, in particular to a radiation type thermal control mechanism.
Background
The thermal control mechanism of the spacecraft is mainly used for ensuring that structural components and instrument equipment of the spacecraft are in a proper temperature range in a space environment so as to enable the structural components and the instrument equipment to work normally. Thermal control methods widely used in current spacecraft are roughly classified into two types, passive type and active type.
The passive thermal control is an open-loop control, which mainly depends on reasonable layout, selection of materials with proper thermophysical properties and a thermal control device with a simpler structure to organize the heat exchange process.
The radiation type active thermal control mechanism utilizes a driver to drive an action part, and adjusts the radiation heat dissipation capacity and controls the temperature. The prior applied radiation thermal control mechanisms on the spacecraft comprise thermal control shutters, thermal control turntables, flexible blade thermal control mechanisms and the like. The active thermal control mechanism generally adopts closed-loop control, and generally comprises a temperature sensor, a controller and an actuator. When the active thermal control mechanism is adopted, the temperature information of the controlled object can be fed back to the controller to be compared with a preset value, then the execution mechanism is commanded to act according to needs to realize automatic temperature control, and the application of the active thermal control mechanism on the spacecraft is wide because the more severe temperature guarantee can be realized.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides an electrochromic thermal control mechanism, which realizes the control of the thermal radiation characteristic of the whole mechanism by controlling each thermal control unit electrode. The invention is realized by the following technical scheme:
an electrochromic thermal control mechanism, the upper surface of the thermal control mechanism is a transparent heat radiation surface, and the lower surface is a substrate; a plurality of thermal control units with electrochromism are closely arranged between the upper surface and the lower surface; a first electrode layer is arranged below the upper surface of each thermal control unit, a second electrode layer is arranged above the lower surface of each thermal control unit, and the polarities of the first electrode layer and the second electrode layer are opposite; a transparent hollow cylindrical box is arranged between the two electrode layers, a rotatable shaft is axially arranged at the center of the box, and semi-cylinders with opposite charges are respectively arranged on two cylindrical surfaces of the rotatable shaft.
As a further improvement of the invention, the electrode layer is an infrared transparent thin film electrode layer.
As a further improvement of the invention, the rotation shaft is in heat conduction with the substrate and the two cylindrical surfaces.
As a further improvement of the invention, one of the semi-cylinders is positively charged and the surface has a high thermal emissivity, the other semi-cylinder is negatively charged and the surface has a low thermal emissivity.
As a further improvement of the invention, the polarity of each thermal control unit electrode layer is controlled, so that the two semicylinders with opposite charges rotate to a target position according to the electric field distribution, thereby controlling the thermal emissivity of the upper surface of the unit and further controlling the thermal emissivity of the whole panel.
As a further improvement of the present invention, when the first electrode layer of the thermal control unit is positive and the second electrode layer is negative, the negatively charged half-cylinder is on top and the positively charged half-cylinder is on bottom, and the top surface of the thermal control unit has a low thermal emissivity.
As a further improvement of the invention, when the first electrode layer of the thermal control unit is negative and the second electrode layer is positive, the half cylinder with positive charge is on the upper part and the half cylinder with negative charge is on the lower part, and the upper surface of the thermal control unit has high thermal emissivity.
The invention has the beneficial effects that: the electrochromic thermal control mechanism has a simple structure and low power consumption, and can realize the various control of the surface thermal radiation emissivity of the whole mechanism by controlling the thermal emissivity of each unit, thereby flexibly and effectively controlling the temperature field of a satellite.
Drawings
FIG. 1 is a schematic diagram of the partial composition of an electrochromic thermal control mechanism of the present invention.
Detailed Description
The invention is further described with reference to the following description and embodiments in conjunction with the accompanying drawings.
As shown in fig. 1, the electrochromic thermal control mechanism of the present invention has a transparent heat radiation surface 2 on the upper surface and a substrate 1 on the lower surface. A plurality of thermal control units with electrochromism are closely arranged between the upper surface and the lower surface. Fig. 1 shows only 2 thermal control units, and the number of the thermal control units is set according to the practical application of the thermal control mechanism, and is not limited to the scope of the patent claims of the present invention.
A first electrode layer 3 is arranged below the upper surface of each thermal control unit, a second electrode layer 4 is arranged above the lower surface of each thermal control unit, and the polarities of the first electrode layer and the second electrode layer are opposite. A transparent hollow cylindrical box 5 is arranged between the two electrode layers, a rotatable shaft is axially arranged in the center of the box, two cylindrical surfaces of the rotatable shaft are respectively provided with a semi-cylinder 6 with opposite charges, one end of the semi-cylinder is positively charged, the surface of the semi-cylinder has high thermal emissivity, and the other end of the semi-cylinder is negatively charged and has low thermal emissivity. The rotation axis and the substrate and the two cylindrical surfaces are all heat-conducting. The electrode layer is an infrared transparent film electrode layer. By controlling the polarity of each thermal control unit electrode layer, according to the principle that like poles repel each other and opposite poles attract each other, two semicylinders with opposite charges can rotate to a target position according to electric field distribution, so that the thermal emissivity of the upper surface of the unit is controlled, and the thermal emissivity of the whole panel is controlled.
If the first electrode layer of the thermal control unit is positive and the second electrode layer is negative, the half-cylinder with negative charge is on the upper part and the half-cylinder with positive charge is on the lower part, and the upper surface of the thermal control unit has low thermal emissivity at the moment. If the first electrode layer of the thermal control unit is negative and the second electrode layer is positive, the semi-cylinder with positive charge is arranged on the upper part, and the semi-cylinder with negative charge is arranged on the lower part, at the moment, the upper surface of the thermal control unit has high thermal emissivity.
The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
For those skilled in the art, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (5)
1. An electrochromic thermal control mechanism, characterized in that: the upper surface of the thermal control mechanism is a transparent heat radiation surface, and the lower surface of the thermal control mechanism is a substrate; a plurality of thermal control units with electrochromism are closely arranged between the upper surface and the lower surface; a first electrode layer is arranged below the upper surface of each thermal control unit, a second electrode layer is arranged above the lower surface of each thermal control unit, and the polarities of the first electrode layer and the second electrode layer are opposite; a transparent hollow cylindrical box is arranged between the two electrode layers, a rotatable shaft is axially arranged at the center of the box, and two cylindrical surfaces of the rotatable shaft are respectively provided with a semi-cylinder with opposite charges; one of the semi-cylinders has positive charge, the surface has high thermal emissivity, the other semi-cylinder has negative charge, and the surface has low thermal emissivity; by controlling the polarity of the electrode layer of each thermal control unit, the two semicylinders with opposite charges rotate to a target position according to electric field distribution, so that the thermal emissivity of the upper surface of the unit is controlled, and the thermal emissivity of the whole panel is controlled.
2. The electrochromic thermal control mechanism of claim 1, wherein: the electrode layer is an infrared transparent film electrode layer.
3. The electrochromic thermal control mechanism of claim 1, wherein: the rotation axis and the substrate and the two cylindrical surfaces are all heat-conducting.
4. The electrochromic thermal control mechanism of claim 1, wherein: when the first electrode layer of the thermal control unit is positive and the second electrode layer is negative, the half-cylinder with negative charge is on the upper part and the half-cylinder with positive charge is on the lower part, and the upper surface of the thermal control unit has low thermal emissivity at the moment.
5. The electrochromic thermal control mechanism of claim 1, wherein: when the first electrode layer of the thermal control unit is negative and the second electrode layer is positive, the semi-cylinder with positive charge is arranged on the upper part, the semi-cylinder with negative charge is arranged on the lower part, and the upper surface of the thermal control unit has high thermal emissivity at the moment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811560798.XA CN109649694B (en) | 2018-12-20 | 2018-12-20 | Electrochromic thermal control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811560798.XA CN109649694B (en) | 2018-12-20 | 2018-12-20 | Electrochromic thermal control mechanism |
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| CN109649694A CN109649694A (en) | 2019-04-19 |
| CN109649694B true CN109649694B (en) | 2022-01-11 |
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| CN201811560798.XA Active CN109649694B (en) | 2018-12-20 | 2018-12-20 | Electrochromic thermal control mechanism |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110673418A (en) * | 2019-10-11 | 2020-01-10 | 深圳航天东方红海特卫星有限公司 | Graphene intelligent thermal control film |
Family Cites Families (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS60179400A (en) * | 1984-02-24 | 1985-09-13 | 日本電気株式会社 | Controller for heat of artificial satellite using electrochromic element |
| JPS61119097A (en) * | 1984-11-15 | 1986-06-06 | 株式会社東芝 | Heat dissipation controller |
| DE3643691C1 (en) * | 1986-12-20 | 1992-03-05 | Dornier Gmbh | Thermal control layer |
| NL9400303A (en) * | 1994-02-28 | 1995-10-02 | Rudolf Wolfgang Van Der Pol | Heat-radiating screen with adjustable absorptance |
| JP2000021800A (en) * | 1998-07-03 | 2000-01-21 | Hitachi Ltd | Wafer treating apparatus |
| DE19914093A1 (en) * | 1999-03-27 | 2000-10-19 | Dornier Gmbh | Electrochromic element |
| US6538796B1 (en) * | 2000-03-31 | 2003-03-25 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | MEMS device for spacecraft thermal control applications |
| GB0015664D0 (en) * | 2000-06-28 | 2000-08-16 | Secr Defence | Electrochromic devices |
| US6899170B2 (en) * | 2001-11-15 | 2005-05-31 | William J. Biter | Electrostatic switched radiator for space based thermal control |
| US20050074666A1 (en) * | 2002-08-29 | 2005-04-07 | Hirokazu Kimiya | Heat control device for battery |
| CN2874484Y (en) * | 2006-03-30 | 2007-02-28 | 朱先德 | Calorimeter of circular temperature controller with closed chamber at external bucket |
| DE102007062150A1 (en) * | 2007-09-14 | 2009-04-02 | Thales Electron Devices Gmbh | Device for dissipating heat loss and ion accelerator arrangement and traveling wave tube arrangement with a Wärmeleitanordnung |
| JP2012529268A (en) * | 2009-06-05 | 2012-11-22 | インテジェンクス，インコーポレイテッド | Use of universal sample preparation system and integrated analysis system |
| CN101633411B (en) * | 2009-08-24 | 2012-05-23 | 哈尔滨工业大学 | Actuating mechanism of spacecraft for integrating heat control and liquid momentum wheel |
| FR2958449B1 (en) * | 2010-03-30 | 2013-06-14 | Astrium Sas | THERMAL CONTROL DEVICE OF A RADIANT COLLECTOR TUBE |
| JP2012186455A (en) * | 2011-02-16 | 2012-09-27 | Ricoh Co Ltd | Hole formation method and multilayer interconnection, semiconductor device, display element, image display device, and system that form via holes using the method |
| US10739658B2 (en) * | 2011-12-12 | 2020-08-11 | View, Inc. | Electrochromic laminates |
| CN102830064B (en) * | 2012-08-20 | 2014-12-03 | 中国科学院宁波材料技术与工程研究所 | Middle/high-temperature infrared emissivity testing device |
| CN105122094B (en) * | 2012-11-01 | 2018-06-12 | 依视路国际公司 | The changeable color applicator being influenced by heat |
| CN104898345B (en) * | 2015-04-30 | 2017-12-22 | 浙江上方电子装备有限公司 | A kind of drive arrangement of electrochomeric glass |
| CN105093772B (en) * | 2015-08-25 | 2018-12-11 | 京东方科技集团股份有限公司 | Display base plate and preparation method thereof, display device and preparation method thereof |
| US11414220B2 (en) * | 2016-03-31 | 2022-08-16 | Mitsubishi Electric Corporation | Heat radiator using heat pipe panel |
| CN106240848B (en) * | 2016-08-17 | 2018-07-27 | 长沙天仪空间科技研究院有限公司 | A kind of heat dissipation equipment of intelligence microsatellite |
| CN106292788B (en) * | 2016-08-19 | 2018-04-10 | 北京精密机电控制设备研究所 | A kind of thermal control structure of space application servo controller |
| CN106742077B (en) * | 2016-11-29 | 2019-07-12 | 深圳航天东方红海特卫星有限公司 | A kind of thermal control mechanism of iris component and its iris formula |
| CN107792401A (en) * | 2017-10-10 | 2018-03-13 | 深圳航天东方红海特卫星有限公司 | A kind of satellite ceramic aerogel multilayer insulation mechanism |
| CN108803728B (en) * | 2018-06-01 | 2020-11-20 | 北京空间飞行器总体设计部 | Self-adjusting temperature control heater for spacecraft |
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Address after: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Shenzhen Aerospace Dongfanghong Satellite Co.,Ltd. Address before: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee before: AEROSPACE DONGFANGHONG DEVELOPMENT Ltd. |