CN104049643B - A kind of adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method - Google Patents
A kind of adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method Download PDFInfo
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- CN104049643B CN104049643B CN201410245119.5A CN201410245119A CN104049643B CN 104049643 B CN104049643 B CN 104049643B CN 201410245119 A CN201410245119 A CN 201410245119A CN 104049643 B CN104049643 B CN 104049643B
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Abstract
The invention provides a kind of adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method, step one, the fabrication and installation multilayer sun-shading mechanism on required cooling system; Described sun-shading mechanism comprises sunshading board, mounting framework, driving mechanism A and driving mechanism B; Driving mechanism A is installed on the side of described cooling system, and its rotation axis and cooling system radiating surface is parallel; Driving mechanism B is installed on bottom surface or the side of described cooling system, and its rotation axis is vertical with cooling system radiating surface; Mounting framework is connected with driving mechanism A, and sunshading board is fixed on mounting framework; Step 2, control driving mechanism A and driving mechanism B rotate, and sunshading board is blocked the sunshine being incident to radiating surface.Adopt the inventive method can reach the object improving the cooling of system radiating energy force-summing device as required.
Description
Technical field
The invention belongs to the thermal design technical field under the vacuum environment such as space flight or ground, be specifically related to a kind of adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method.
Background technology
Thermal control system (Thermal Control Systems is called for short TCS) is an indispensable ingredient of the system developments such as modern spacecraft, and TCS is often called as spacecraft thermal design at space industry.Under vacuum environment, the key of the system thermal design such as spacecraft is radiating surface design, and the heat-sinking capability of radiating surface under certain design temperature depends on actual absorption Orbital heat flux density.
Radiating surface surface design generally takes the selective coating of low sunlight absorptivity and high IR emissivity, therefore radiating surface is generally arranged on the direction avoiding the infrared heat flow such as planet, satellite, so system can install the limited space of radiating surface, during special circumstances, only a face can be used as radiating surface, under the condition of certain area of dissipation, the heat-sinking capability improving radiating surface is to greatest extent the key of these special system thermal designs.As the moon surface detector due in the face of bottom surface and the high moon infrared heat flow environment of surrounding, its radiating surface is generally arranged on the system end face avoiding lunar surface infrared heat flow, and its area of dissipation is very limited.
The thermal dispersant coatings selecting as far as possible little solar absorptance is current usual way, and the solar absorptance as OSR sheet is 0.10 ~ 0.20.But radiating surface still exists certain absorption Solar heat flow, when radiating surface solar incident angle is 45 °, OSR absorbs Solar heat flow at 95W/m
2~ 190W/m
2between; Radiating surface coating also needs to consider that the ambient particle things such as space environment degeneration and lunar dust pollute, and when radiating surface coating degradation or covered with dust, its solar absorptance can reach 0.45, and now radiating surface absorbs 45 ° of incident angle Solar heat flows is 427W/m
2.
According to current conventional electronic device operating temperature range, general device temperature is no more than 55 DEG C, and therefore the general design temperature in system radiating face is no more than 45 DEG C, and the unit heat-sinking capability of OSR type radiating surface is at 460W/m
2.Without to degenerate or dust impact, under solar incident angle is the condition of 45 °, the clean heat-sinking capability of radiating surface is reduced to 355W/m
2~ 270W/m
2, reduce ratio and reach 41%; Affect that OSR solar absorptance reaches 0.45 at dust, under solar incident angle is the condition of 45 °, the clean heat-sinking capability of radiating surface is reduced to 33W/m
2, reduce ratio and reach 93%, radiating surface is substantially without heat-sinking capability.
Therefore reducing or eliminate radiating surface to absorb the key that Solar heat flow is the system radiating face designs such as spacecraft, is also the key of system thermal design.
Summary of the invention
In view of this, the invention provides a kind of adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method, the method can reach the object improving the cooling of system radiating energy force-summing device as required.
The present invention for achieving the above object, adopts following technical scheme:
A kind of adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method, concrete steps are:
Step one, the fabrication and installation multilayer sun-shading mechanism on required cooling system;
Described sun-shading mechanism comprises sunshading board, mounting framework, driving mechanism A and driving mechanism B; Wherein sunshading board is alternately stacked by two-sided aluminized mylar and terylene net and forms, and its outermost coated one deck polyimide metallized film, polyimide metallized film face is outwardly; Described mounting framework is the netted covering cellular board of carbon fiber; Above-mentioned parts annexation is:
Driving mechanism A is installed on the side of described cooling system, and its rotation axis and cooling system radiating surface is parallel; Driving mechanism B is installed on bottom surface or the side of described cooling system, and its rotation axis is vertical with cooling system radiating surface; Mounting framework is connected with driving mechanism A, and sunshading board is fixed on mounting framework;
Step 2, judge whether to need to carry out sunshade, when needs carry out complete sunshade, control driving mechanism A and driving mechanism B and rotate, make sunshading board block the sunshine being incident to radiating surface completely; When needs carry out part sunshade, control driving mechanism A and driving mechanism B and rotate, make sunshading board partial occlusion be incident to the sunshine of radiating surface; When without the need to carrying out sunshade, controlling driving mechanism A and driving mechanism B and rotating, sunshading board is not blocked the sunshine being incident to radiating surface.
Further, the present invention arranges the light activated element being installed on the sunshading board back side, and described light activated element is for responding to solar azimuth, and driving mechanism B adjusts in real time according to the solar azimuth that light activated element is responded to and carries out sunshade.
Further, driving mechanism B of the present invention has the solar azimuth delta data in cooling system place track or geographic position, driving mechanism B adjusts in real time according to described data and carries out sunshade.
Further, sunshading board of the present invention is alternately stacked by 16 layers of two-sided aluminized mylar and 15 layers of terylene net and forms, and the thickness of the coated polyimide metallized film of outermost layer is 25 microns.
Further, the present invention adopts the polyimide pin be pasted on mounting framework to be fixed on mounting framework by sunshading board.
Beneficial effect:
(1) feature in method provided by the present invention vacuum environment and sunshine direction residing for system, carbon fiber netted covering cellular board is installed the vacuum heat-insulation multilayer sunshading board of a high heat-proof quality, utilize two axially vertical cover driving mechanisms, need to regulate sun visor position according to solar direction, the complete sunshade of radiating surface, part sunshade and non-sunshade can be realized.The present invention can make every square metre of clean OSR radiating surface many heat radiations 95W ~ 190W blocking 45 ° of incident angle solar times completely, degenerates or covered with dust radiating surface (solar absorptance 0.45) heat-sinking capability increases 420W/m
2; Thus effectively reduce radiating surface and device temperature.
(2) the multilayer sunshading heat isolating board of the present invention's employing, based on 15 unit film, terylene net composite and flexible light structures, the features such as quality is light, installability good, vacuum heat-insulation superior performance that it has, the Resources Consumption of consumption is little and shaded effects are strong.Improve the heat-sinking capability of clean OSR radiating surface 41%, can solve and degenerate under ordinary temperature or problem that covered with dust radiating surface (solar absorptance 0.45) radiating surface cannot dispel the heat.
Accompanying drawing explanation
Fig. 1 is installed on the multilayer sun-shading mechanism composition structural representation of aerospace system;
Fig. 2 lunar surface rover sunshading board composition structural representation;
Fig. 3 lunar surface rover sunshading board fundamental diagram;
Fig. 4 moon Northern Hemisphere solar azimuth and sunshading board orientation regulate schematic diagram;
Radiating surface temperature analysis figure before and after Fig. 5 sunshade;
Wherein, 1-sunshading board, 2-mounting framework, 3-driving mechanism A, 4-driving mechanism B.
Embodiment
To develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
Design philosophy of the present invention is residing for the system feature in vacuum environment and sunshine direction, carbon fiber netted covering cellular board is installed the vacuum heat-insulation multilayer sunshading board of a high heat-proof quality, utilize two axially vertical cover driving mechanisms, need to regulate sun visor position according to solar direction and sunshade ratio, the complete sunshade of radiating surface, part sunshade and non-sunshade can be realized.
The present invention's adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method, concrete steps are:
Step one, the multilayer sun-shading mechanism of fabrication and installation in required heat radiation aerospace system;
As shown in Figure 1, described sun-shading mechanism comprises sunshading board, mounting framework, driving mechanism A and driving mechanism B; Wherein sunshading board is alternately stacked by two-sided aluminized mylar and terylene net and forms, and its outermost coated one deck polyimide metallized film, polyimide metallized film face is outwardly; Described mounting framework is the netted covering cellular board of carbon fiber; Above-mentioned parts annexation is:
Driving mechanism A is installed on the side of described aerospace system, and its rotation axis and aerospace system radiating surface is parallel; Driving mechanism B is installed on bottom surface or the side of described aerospace system, and its rotation axis is vertical with aerospace system radiating surface; Mounting framework is connected with driving mechanism A, and sunshading board is fixed on mounting framework;
The present invention preferably makes sunshading board be alternately stacked by 16 layers of two-sided aluminized mylar and 15 layers of terylene net and forms, and the thickness of the coated polyimide metallized film of outermost layer is 25 microns.Adopt the sunshading board of the design of which can reflect the sunshine of more than 50%, 15 unit multi-layer sunshading boards heat-proof quality in vacuum environment is very good, is not isolated in outside sunshading board by multilayer sunshading board by the solar heat overwhelming majority reflected.
The present invention simultaneously preferably adopts the polyimide pin be pasted on mounting framework to be fixed on mounting framework by sunshading board.
Step 2, judge whether to need to carry out sunshade, when needs carry out complete sunshade, control driving mechanism A and driving mechanism B and rotate, make sunshading board block the sunshine being incident to radiating surface completely; When needs carry out part sunshade, control driving mechanism A and driving mechanism B and rotate, make sunshading board partial occlusion be incident to the sunshine of radiating surface; When without the need to carrying out sunshade, controlling driving mechanism A and driving mechanism B and rotating, sunshading board is not blocked the sunshine being incident to radiating surface.
In this step when sun height of incidence angle, system radiating face, equivalent incident energy density are larger, then represent and need to carry out sunshade, then control driving mechanism A and rotate sunshading board to erectting attitude, make sunshading board block incident sunshine; When radiating surface sun height of incidence angle less and without sun-shading requirements time, sunshading board maintenance level or the attitude that dips down, can keep radiating surface sunlight unobstructed.Meanwhile, when radiating surface sunlight height of incidence angle is 45 ° to the maximum, the size of sunshading board can equal radiating surface size, and the multilayer sunshading board of setting 100% can block the incident sunshine of radiating surface.As radiating surface sunlight height of incidence angle is greater than 45 °, energy partial occlusion sunshine, can erect the corresponding increase of height dimension under attitude by sunshading board.
The present invention can adopt and carry out sunshade judgement in two ways, the first, arrange the light activated element being installed on the sunshading board back side, described light activated element is for responding to solar azimuth, the solar azimuth that driving mechanism B responds to according to light activated element, judges whether to need to carry out sunshade.The second, driving mechanism B has the solar azimuth delta data in aerospace system place track or geographic position, driving mechanism B judges whether to need to carry out sunshade according to described data.
Along with the change of relative radiating surface solar azimuth, the orientation of adjustment sunshading board in real time, under making radiating surface be in the shade of sunshading board all the time.A kind of method is according to the solar azimuth delta data in system place certain tracks or geographic position, implant procedure controls driving mechanism B and rotates, real-time adjustment sunshading board points to solar azimuth, another kind method, at the sunshading board back side, light activated element is installed, induction solar azimuth, and it is servo-actuated to feed back to programmed control driving mechanism B, under making radiating surface be in the shade of sunshading board all the time.According to the needs of shaded effects and the realizability of action, adjust frequency and can be 5 °/time ~ 20 °/time.
Example: the application of adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method in inspection tour prober for moon surface:
(1) multilayer sunshading board is a kind of 15 unit film, terylene net composite and flexible light structures, and be stacked by 16 layers of two-sided aluminized mylar and 15 layers of terylene net and form, as Fig. 2, two-sided aluminized mylar only 6 micron thickness, substance is about 9g/m
2, terylene net substance is about 10g/m
2, the polyimide metallized film of multilayer outermost coated one deck 25 micron thickness, substance is about 38g/m
2, 15 unit multi-layer sunshading board compound substances are no more than 350g/m
2, very light.Polyimide metallized film face, can reflect the sunshine of more than 50% outwardly, and 15 unit multi-layer sunshading boards heat-proof quality in vacuum environment is very good, is not isolated in outside sunshading board by multilayer sunshading board by the solar heat overwhelming majority reflected.
(2) radiating surface of lunar surface rover is the OSR type radiating surface of parallel moon local level, in the side of lunar surface rover, multilayer sunshading board is installed, multilayer size for sunshade board and rover thermal window consistent size, be designed to length 1240mm, width 800mm, be about 1m containing marginal dimension area
2, weight is about 350g.
(3) utilize moon rover side to open up and can receive the netted covering cellular board of solar wing carbon fiber as multilayer sunshading board mounting framework, multilayer sunshading board is installed on the moon rover solar wing cellular board back side, composition solar wing sunshading board composite structure; Because multilayer is flexible light weight structure, use 30 ~ 50 polyimide pins to fix multilayer sunshading board, dowel bushing uniform layout is in the solar wing back side and paste with silicon rubber, fixes multilayer, see Fig. 2 after multilayer thermal-insulating board punching is equipped with polyimide lamination.
(4) driving mechanism A is installed on the side of rover, when rover horizontal radiating surface sun height of incidence angle, equivalent incident energy density are larger, control driving mechanism A and rotates solar wing to erectting attitude, make sunshading board block incident sunshine; During when rover horizontal radiating surface sun height of incidence angle is less, without sun-shading requirements, solar wing maintenance level or the attitude that dips down, make solar wing just in the face of sun generating, radiating surface sunlight can be kept unobstructed.See Fig. 3.
When radiating surface sunlight height of incidence angle is 45 ° to the maximum, the size of sunshading board can equal radiating surface size, and the multilayer sunshading board of setting 100% can block the incident sunshine of radiating surface.As radiating surface sunlight height of incidence angle is greater than 45 °, energy partial occlusion sunshine, can erect the corresponding increase of height dimension under attitude by sunshading board.
(5) in the moon Northern Hemisphere, in a Lunar A, solar azimuth changes gradually southwester from the southeast, utilizes the mobile device original place of rover to rotate, multilayer sunshading board is between radiating surface and sunlight all the time, sees Fig. 4.Solar azimuth often change 5 ° be roughly equal to 15 hours adjustment once, have before adjustment be no more than 5% shine upon on radiating surface, need the arrival Orbital heat flux being thought of as radiating surface.
(6) for the lunar surface rover being in moon north latitude 44 °, Fig. 5 gives without multilayer sunshade with under having multilayer to erect sunshade two states, month period of the day from 11 a.m. to 1 p.m rover radiating surface temperature cloud picture, from figure, comparing can be found out, under multilayer sunshade, powder for cleaning hot-face temperature is compared and is on average declined about 28.9 DEG C without sunshade, be infected with lunar dust radiating surface (solar absorptance 0.45) temperature under multilayer sunshade to compare and on average decline about 57.5 DEG C without sunshade, effect clearly.
By adopting method provided by the present invention, a kind of making of high-performance multilayer sunshading board, installation and using method can be obtained, when radiating surface solar incident angle 45 °, every square metre of clean OSR radiating surface many heat radiations 95W ~ 190W can be made, degenerate or covered with dust radiating surface heat-sinking capability increase 420W/m
2; Thus effectively reduce system radiating face and device temperature.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included in protection scope of the present invention.
Claims (5)
1. an adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method, it is characterized in that, concrete steps are:
Step one, the fabrication and installation multilayer sun-shading mechanism on required cooling system;
Described sun-shading mechanism comprises sunshading board, mounting framework, driving mechanism A and driving mechanism B; Wherein sunshading board is alternately stacked by two-sided aluminized mylar and terylene net and forms, and its outermost coated one deck polyimide metallized film, polyimide metallized film face is outwardly; Described mounting framework is the netted covering cellular board of carbon fiber; Above-mentioned parts annexation is:
Driving mechanism A is installed on the side of described cooling system, and its rotation axis and cooling system radiating surface is parallel; Driving mechanism B is installed on bottom surface or the side of described cooling system, and its rotation axis is vertical with cooling system radiating surface; Mounting framework is connected with driving mechanism A, and sunshading board is fixed on mounting framework;
Step 2, judge whether to need to carry out sunshade, when needs carry out complete sunshade, control driving mechanism A and driving mechanism B and rotate, make sunshading board block the sunshine being incident to radiating surface completely; When needs carry out part sunshade, control driving mechanism A and driving mechanism B and rotate, make sunshading board partial occlusion be incident to the sunshine of radiating surface; When without the need to carrying out sunshade, controlling driving mechanism A and driving mechanism B and rotating, sunshading board is not blocked the sunshine being incident to radiating surface.
2. adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method according to claim 1, it is characterized in that, in step one manufacturing process, the light activated element being installed on the sunshading board back side is set, described light activated element is for responding to solar azimuth, and driving mechanism B adjusts in real time according to the solar azimuth that light activated element is responded to and carries out sunshade.
3. adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method according to claim 1, it is characterized in that, described driving mechanism B has the solar azimuth delta data in cooling system place track or geographic position, driving mechanism B adjusts in real time according to described data and carries out sunshade.
4. adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method according to claim 1, it is characterized in that, described sunshading board is alternately stacked by 16 layers of two-sided aluminized mylar and 15 layers of terylene net and forms, and the thickness of the coated polyimide metallized film of outermost layer is 25 microns.
5. adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method according to claim 1, is characterized in that, adopts the polyimide pin be pasted on mounting framework to be fixed on mounting framework by sunshading board.
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| CN106553773B (en) * | 2016-10-28 | 2019-05-07 | 深圳航天东方红海特卫星有限公司 | A kind of reversible locking radiation thermal control mechanism |
| CN111891408A (en) * | 2020-06-30 | 2020-11-06 | 北京空间飞行器总体设计部 | Multilayer heat insulation assembly system for increasing heat insulation effect of spacecraft |
| CN113772131B (en) * | 2021-09-13 | 2023-02-10 | 南京理工大学 | Thermotropic deformation expansion radiator device |
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|---|---|---|---|---|
| EP0271370A1 (en) * | 1986-10-16 | 1988-06-15 | Centre National D'etudes Spatiales | Shading device for use in a geostatic satellite |
| US5527001A (en) * | 1993-06-11 | 1996-06-18 | Teledesic Corporation | Modular communication satellite |
| CN1205960A (en) * | 1997-06-26 | 1999-01-27 | 国家航空工业公司 | Satellite with improved heat sinkage |
| CN1308581A (en) * | 1998-04-17 | 2001-08-15 | 特伯赛科技公司 | Spacecraft shading device |
| CN201878050U (en) * | 2010-11-18 | 2011-06-22 | 浙江德裕科技有限公司 | Ecological intelligent power generation sunshade board |
| CN102650189A (en) * | 2011-02-28 | 2012-08-29 | 许�鹏 | Heat preservation type sunshade and energy-saving device |
-
2014
- 2014-06-04 CN CN201410245119.5A patent/CN104049643B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0271370A1 (en) * | 1986-10-16 | 1988-06-15 | Centre National D'etudes Spatiales | Shading device for use in a geostatic satellite |
| US5527001A (en) * | 1993-06-11 | 1996-06-18 | Teledesic Corporation | Modular communication satellite |
| CN1205960A (en) * | 1997-06-26 | 1999-01-27 | 国家航空工业公司 | Satellite with improved heat sinkage |
| CN1308581A (en) * | 1998-04-17 | 2001-08-15 | 特伯赛科技公司 | Spacecraft shading device |
| CN201878050U (en) * | 2010-11-18 | 2011-06-22 | 浙江德裕科技有限公司 | Ecological intelligent power generation sunshade board |
| CN102650189A (en) * | 2011-02-28 | 2012-08-29 | 许�鹏 | Heat preservation type sunshade and energy-saving device |
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