CN1205960A - Satellite with improved heat sinkage - Google Patents
Satellite with improved heat sinkage Download PDFInfo
- Publication number
- CN1205960A CN1205960A CN 98115607 CN98115607A CN1205960A CN 1205960 A CN1205960 A CN 1205960A CN 98115607 CN98115607 CN 98115607 CN 98115607 A CN98115607 A CN 98115607A CN 1205960 A CN1205960 A CN 1205960A
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- satellite
- plane
- cell panel
- solar cell
- shield
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Abstract
A satellite, especially a geostationary satellite, which includes: at least one face (5) which is arranged in the path of the solar radiation (9); at least one solar panel (7) which is a generator of electricity, which is pointed continuously toward the sun and projects from the face (5); and a screen (14) secured to the solar panel (7). The satellite is noteworthy in that the solar panel (7) is arranged centrally with respect to the face (5) and the screen (14) is secured to the solar panel (7) by an arm (15).
Description
The present invention relates to artificial satellite, particularly geostationary satellite relates in particular to described temperature control of satellites.
As everyone knows, the above live subset of satellite is with the dissipated in heat energy.For described equipment is remained in the optimum working temperature scope, must remove unnecessary heat energy from inside satellite.And people know that also the removal of this unnecessary heat energy generally goes in the space to realize by they are radiated.
One comprise opposed orientation and respectively with the situation of perpendicular be exposed to the north a plane and the satellite (particularly communication satellite) of earth pole axis line towards the Nan Ping face under, normally go the space by the described plane and heat is radiated from this satellite of being exposed to the north towards Nan Ping face (they are used as a heat radiator).This method is superior, the plane and towards the Nan Ping face because this is exposed to the north:
-in year, compare with other planes of satellite and to be subjected to minimum solar radiation; And
-in one day (in other words one change in) have constant solar illumination, so make it can avoid excessive temperature traverse.
But, because this solar illumination is exposed to the north and is provided heat energy towards the Nan Ping face to described, can not be best exactly by these surface radiatings, and for providing the suitable operating temperature to described equipment even may being inadequate.
This shortcoming is owing to following reason will become more obvious, usually in a simple form known, describedly be exposed to the north and be provided with the sunshine reflectance coating with higher infrared emittance of an OSR (Optical Solar Reflector Optical Solar Reflector) type towards the radiating surface (those radiating surfaces are bases of temperature control of satellites) of Nan Ping face, this coating covers described plane at least in part.In fact, this coating has absorbed a very important part of incident solar power, thereby presents limited heat-sinking capability.In addition, the OSR coating also has and costs an arm and a leg and be easy to aging other shortcomings that waits under the effect of solar radiation.
In order to increase the heat-sinking capability of satellite, the solar cell panel itself that auxiliary shield may be housed is used in suggestion among European patent EP-A-0447049, so that their shade for good and all is incident upon on such plane of satellite, the location independent of it and the sun, thus make the drop in temperature on this plane and the heat-sinking capability on described plane is increased.But, such known embodiment make it must with described solar cell panel off-centre, thereby increased all difficulties relevant with adjustment, balance and the rotation of described solar cell panel.
The objective of the invention is to overcome these shortcomings.
For this reason, according to the present invention, this satellite (particularly geostationary satellite) comprising:
-at least one plane, this plane are used as a path that is used for the heat radiator of contained equipment on the described satellite and is set at solar radiation;
-at least one solar cell panel, this cell panel are electric generators, and it continuously points to the sun and stretches out from described plane; And
-one shield that is fixed on the described solar cell panel, this shield are arranged on the periphery of described satellite and stop to point to the solar radiation on described plane;
This satellite merits attention part and is:
-described solar cell panel is provided with along central authorities with respect to described plane, and
-described shield is fixed on the described solar cell panel by means of an arm.
Certainly, the distance between the height of described shield and width and it and the described day light generator can decide like this, makes it to be incident upon shade on the described plane heat-sinking capability with required is suitable at least.
This shield can have simple shape or best profile, and can be a single piece or made by several parts.It can be formed or be made of a simple covering with suitable external coating by multilayer material, this external coating can be used to limit sun effect thereon, thus also just limited the sun on radiating surface effect and strengthened its heat-sinking capability.At launching phase, this shield can be in its control position or folding position, and it can automatically or according to instruction launch in this case.
Obviously, the flat-bed shape of satellite can be chosen wantonly, and shield then can be aligned in its inside or outside with platform, and shield can stretch out or not stretch out from satellite in addition.
The such arm that connects shield and solar cell panel can be a specific component or the inside that can be assemblied in this electrical generator or shield.This arm can be fixed on any part of day light generator.But it preferably is fixed on the pole of described solar cell panel.
The described radiating surface of this satellite can be a plane and the coating that is coated with a high emissive capacity at least in part.
As mentioned above, be exposed to the north plane or of such radiator plane flat-bed that can be described satellite towards the Nan Ping face.
Each figure in the accompanying drawing will illustrate and can implement mode of the present invention.In these figure, identical label is represented identical parts.
Fig. 1 shows an artificial satellite on its geostationary orbit.
Fig. 2 and 3 schematically and partly shows an embodiment of artificial satellite of the present invention respectively with lateral plan and birds-eye view.
Schematically showing a geostationary satellite 1 among Fig. 1 centers on the track 2 of the earth 3 at it.The platform 4 of satellite 1 has for example parallelepiped shape, and this platform comprises be exposed to the north plane 5 and one towards Nan Ping face 6, and these planes all are perpendicular with the pole axis of the earth.
Be provided with two solar cell panels 7 and 8 that are used for to satellite 1 supply of electrical energy, these cell panels are continuously accepted radiation 9 towards the sun and from the sun. Solar cell panel 7 and 8 is arranged on middle position, respectively from being exposed to the north plane 5 and from stretching out by means of the described cell panel 7 of for example fixed platform 4 and 8 pole 10 and 11 towards facial plane 6.Described pole 10 and 11 forms articulated joint with a kind of known way, make described cell panel 7 and 8 can be in a stowed position folding during satellite 1 emission along platform 4 and when described satellite enters its track 2, be in an expanded position (as shown in fig. 1 the position and above explanation).
In addition, pole 10 and 11 can be exposed to the north and rotate towards the axis Z-Z (seeing the arrow 12 in Fig. 2 and 3) of Nan Ping face 5 and 6 perpendicular to described around one equally with a kind of known way, make and continuously to point to the sun (radiation 9) under the effect of the position servo control device (it also is known, not shown) of described solar cell panel 7 and 8 in being arranged on platform 4.
The temperature control of satellite 1 can be by being exposed to the north this and realizing as heat radiator towards facial plane 5 and 6, and as above illustrated mistake is such.For this reason, carry a radiation coating 13 (seeing Fig. 2 and 3) that covers thereon and form the radiating surface on described these planes at least in part on these faces.
According to the present invention, for on the plane 5 that is exposed to the north shown in Fig. 2 and 3, be provided with a shield 14 at the periphery of the platform 4 of satellite and along the path direction of solar radiation 9, make this shield live this towards north in that the projection on north 5 is fully topped, perhaps topped at least its width of cloth of living is penetrated coating 13.
The setting that the position of shield 14 and shape are such, make this shield to rotate in company with described solar cell panel 7 around axis Z-Z, as the function in the orientation of solar radiation 9, thereby shield can continuously be incident upon its shade on described 5, perhaps at least on this coating 13.
Claims (5)
1. satellite, particularly a kind of geostationary satellite comprises:
-at least one plane (5), this plane are used as one and are used for the path that described satellite (1) is gone up the heat radiator of contained equipment and is set at solar radiation (9);
-at least one solar cell panel (7), this cell panel are electric generators, and it continuously points to the sun and stretches out from described plane (5); And
-one shield (14) that is fixed on the described solar cell panel (7), this shield are arranged on the periphery place of described satellite and stop this solar radiation (9) towards described plane (5); Wherein:
-described solar cell panel (7) is arranged on the central authorities of described plane (5); And
-described shield (14) is fixed on the described solar cell panel (7) by means of an arm (15).
2. satellite as claimed in claim 1 is characterized in that, described arm (15) is fixed on the pole (10) of described solar cell panel (7).
3. satellite as claimed in claim 1 is characterized in that, described plane (5) are covered by a coating (13) with higher infrared emittance at least partly.
4. satellite as claimed in claim 1 is characterized in that, described plane (5) are the planes that is exposed to the north on the plane (4) of described satellite.
5. satellite as claimed in claim 1 is characterized in that, described plane (6) be described satellite plane (4) towards the Nan Ping face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 98115607 CN1205960A (en) | 1997-06-26 | 1998-06-26 | Satellite with improved heat sinkage |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR08007/97 | 1997-06-26 | ||
| CN 98115607 CN1205960A (en) | 1997-06-26 | 1998-06-26 | Satellite with improved heat sinkage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1205960A true CN1205960A (en) | 1999-01-27 |
Family
ID=5224642
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 98115607 Pending CN1205960A (en) | 1997-06-26 | 1998-06-26 | Satellite with improved heat sinkage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1205960A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101451968B (en) * | 2007-12-04 | 2011-05-11 | 北京卫星环境工程研究所 | High precision in-situ measurement equipment for calorific radiation performance of satellite surface |
| CN102944256A (en) * | 2012-11-26 | 2013-02-27 | 中国科学院长春光学精密机械与物理研究所 | Radiator suitable for space optical remote sensor in sun-synchronous orbit |
| CN103448924A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Mechanical and thermal integrated device of high-power-consumption solar array drive mechanism for satellite |
| CN104049643A (en) * | 2014-06-04 | 2014-09-17 | 北京空间飞行器总体设计部 | Adjustable vacuum thermal-insulation multilayer sunshading and cooling method |
| CN107922058A (en) * | 2015-08-10 | 2018-04-17 | 空客防务与空间有限公司 | Artificial satellite |
-
1998
- 1998-06-26 CN CN 98115607 patent/CN1205960A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101451968B (en) * | 2007-12-04 | 2011-05-11 | 北京卫星环境工程研究所 | High precision in-situ measurement equipment for calorific radiation performance of satellite surface |
| CN102944256A (en) * | 2012-11-26 | 2013-02-27 | 中国科学院长春光学精密机械与物理研究所 | Radiator suitable for space optical remote sensor in sun-synchronous orbit |
| CN103448924A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Mechanical and thermal integrated device of high-power-consumption solar array drive mechanism for satellite |
| CN103448924B (en) * | 2013-08-08 | 2016-04-20 | 上海卫星工程研究所 | A kind of satellite heating integrated device of machine of large power consumption solar array driver train |
| CN104049643A (en) * | 2014-06-04 | 2014-09-17 | 北京空间飞行器总体设计部 | Adjustable vacuum thermal-insulation multilayer sunshading and cooling method |
| CN104049643B (en) * | 2014-06-04 | 2015-09-23 | 北京空间飞行器总体设计部 | A kind of adjustable vacuum heat-insulation multilayer sunshading and temperature reducing method |
| CN107922058A (en) * | 2015-08-10 | 2018-04-17 | 空客防务与空间有限公司 | Artificial satellite |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C53 | Correction of patent for invention or patent application | ||
| CB02 | Change of applicant information |
Applicant after: Matela astronautics S. A. Applicant before: Aerospatiale Societe Nationale Industrielle |
|
| COR | Change of bibliographic data |
Free format text: CORRECT: APPLICANT; FROM: AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE TO: MATELA ASTRONAUTICS S. A. |
|
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C53 | Correction of patent for invention or patent application | ||
| CB02 | Change of applicant information |
Applicant after: Alkater Corp. Applicant before: Matela astronautics S. A. |
|
| COR | Change of bibliographic data |
Free format text: CORRECT: APPLICANT; FROM: MATELA ASTRONAUTICS S. A. TO: ALKAERS CORP. |
|
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |