JPS6328800A - Heat insulator for artificial satellite - Google Patents
Heat insulator for artificial satelliteInfo
- Publication number
- JPS6328800A JPS6328800A JP61173430A JP17343086A JPS6328800A JP S6328800 A JPS6328800 A JP S6328800A JP 61173430 A JP61173430 A JP 61173430A JP 17343086 A JP17343086 A JP 17343086A JP S6328800 A JPS6328800 A JP S6328800A
- Authority
- JP
- Japan
- Prior art keywords
- satellite
- artificial satellite
- heat
- radiation shield
- opening
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000012212 insulator Substances 0.000 title 1
- 230000005855 radiation Effects 0.000 claims description 21
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims description 9
- 238000001514 detection method Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 238000010438 heat treatment Methods 0.000 claims description 4
- 230000002457 bidirectional effect Effects 0.000 claims description 2
- 238000009413 insulation Methods 0.000 claims 1
- NMFHJNAPXOMSRX-PUPDPRJKSA-N [(1r)-3-(3,4-dimethoxyphenyl)-1-[3-(2-morpholin-4-ylethoxy)phenyl]propyl] (2s)-1-[(2s)-2-(3,4,5-trimethoxyphenyl)butanoyl]piperidine-2-carboxylate Chemical compound C([C@@H](OC(=O)[C@@H]1CCCCN1C(=O)[C@@H](CC)C=1C=C(OC)C(OC)=C(OC)C=1)C=1C=C(OCCN2CCOCC2)C=CC=1)CC1=CC=C(OC)C(OC)=C1 NMFHJNAPXOMSRX-PUPDPRJKSA-N 0.000 description 7
- 238000010521 absorption reaction Methods 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910052790 beryllium Inorganic materials 0.000 description 1
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000007740 vapor deposition Methods 0.000 description 1
Landscapes
- Insulating Bodies (AREA)
- Insulators (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Abstract] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明は、人工衛星の外部または外部構造の保温装置に
関する。DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a heating device for the exterior or exterior structure of an artificial satellite.
（従来の技術およびその問題点）
人工衛星の温度は、太陽熱と搭載した機器から発生する
熱によって犬さく変化するっ搭載した機器が正常に作動
するためには、人工衛星の温度を機器の許容温度範囲内
に保たなければならない。(Conventional technology and its problems) The temperature of a satellite changes rapidly due to solar heat and heat generated from onboard equipment.In order for the onboard equipment to operate normally, it is necessary to adjust the temperature of the satellite to the allowable range of the equipment. Must be kept within temperature range.
温度を制御する手段としては、従来第３図に示すよウニ
、サーマルルーバ６とサーマルブランケット５が用いら
れている。サーマルルーバ６は開閉可能なブレード６１
をもっており、人工衛星の壁１１ｆｉｌｉ（構体パネル
７）に取り付けて使用されるう人工衛星の内部の温度を
下げたいときはブレード６１を開いて熱を外部へ逃がし
、保温したいときはブレード６１を閉じて熱を内部に閉
じ込める。サーマルブランケット５は断熱材料で出来て
おり、人工衛星の内側に張り付けである６、サーマルブ
ランケット５は熱の出入りを遮断することにより、人工
衛星が太陽熱に暖められたときの急激な温度上昇と、地
球の陰に入ったときの急激な温度降下を緩和するもので
ある。しかし、これらの装置が温度ｔコントロールでき
るのは人工衛星の内部だけであって、人工衛星の外部表
面である構体パネルや太陽電池パネルのような人工衛星
の外部に取り付けられている機器はこれらの恩恵を受け
られない。その上、温度をコントロールする能力として
も、これらの装置だけでは充分ではない。Conventionally, as means for controlling the temperature, a thermal louver 6 and a thermal blanket 5 are used as shown in FIG. The thermal louver 6 has a blade 61 that can be opened and closed.
When you want to lower the temperature inside the satellite, you open the blade 61 to release the heat to the outside, and when you want to keep it warm, you close the blade 61. to trap heat inside. The thermal blanket 5 is made of a heat insulating material and is attached to the inside of the satellite 6. By blocking heat in and out, the thermal blanket 5 prevents the sudden temperature rise when the satellite is warmed by solar heat. This is to alleviate the sudden drop in temperature when entering the Earth's shadow. However, these devices can only control the temperature inside the satellite, and devices attached to the outside of the satellite such as structure panels and solar panels, which are the external surfaces of the satellite, cannot be controlled by these devices. cannot receive benefits. Furthermore, these devices alone are not sufficient in their ability to control temperature.
太陽電池パネルは、外部ｔ（突き出したパドル形式のも
のであっても、構体パネルに取り付けられたものであっ
ても、質量が小ｇ （表面積が大きいから熱容量は極め
て小さい。また、太陽′１池パネルの大部分を占める太
ｌ′ａ電池の太陽光線吸収率と赤外線輻射率はともに０
．８前後であってかなり犬きい値である。太陽光線吸収
率とは文字通り照射された太陽光線を吸収する割合であ
り、赤外線輻射率とは熱エネルギーつまり赤外線を放出
する時間的な割合である。これらのことと熱容量が小さ
いことを考え合わせれば、太陽電池パネルの温度は太陽
光線が当ると急速に上昇し、日陰に入ると急速に降下す
ることが分る。上に述べたように人工衛星の内部と外部
はサーマルブランケットで熱的に絶縁されているから、
太陽電池パネルは温度が低下しても人工衛星の内部から
熱を補給してもらうことはできない。従って、日陰にい
る時間が長いと、つまり軌道のうち地球の陰にある部分
が長いと、太陽電池の温度は下がり続け、ついには許容
温度範囲の下限値を下回り回復不可能な損傷をこうむる
ことになる。Solar panels, whether they are external t (protruding paddle type or attached to a structural panel), have a mass of small g (due to their large surface area, their heat capacity is extremely small. The solar absorption rate and infrared radiation rate of the thick l'a battery, which makes up the majority of the pond panel, are both 0.
．． It is around 8, which is quite a dog threshold. The solar absorption rate is literally the rate at which sunlight is absorbed, and the infrared emissivity is the time rate at which thermal energy, or infrared rays, is emitted. Considering these facts and the small heat capacity, it can be seen that the temperature of a solar panel increases rapidly when exposed to sunlight, and decreases rapidly when it is in the shade. As mentioned above, the inside and outside of the satellite are thermally insulated by a thermal blanket, so
Solar panels cannot receive heat from inside the satellite even if the temperature drops. Therefore, if the solar cell is left in the shade for a long time, i.e. if the part of its orbit is in the shadow of the Earth for a long time, the temperature of the solar cell will continue to decrease until it falls below the lower limit of the permissible temperature range and suffers irreparable damage. become.
本発明の目的は、人工衛星の外側表面または外部に取り
付けられた機器に適用する保温装置を提供することにあ
る。SUMMARY OF THE INVENTION An object of the present invention is to provide a heat retention device that can be applied to equipment attached to the outer surface or outside of an artificial satellite.
（問題点を解決するための手段）
本発明の人工衛星の保温装ａけ、第１図および第２図に
示すように、人工衛星の外部の一部または全部に適用す
る保温装置であって、開閉自在の放射シールドと、この
放射シールドの開閉手段と、人工衛星が太陽光線に対し
て地球の陰の内にいるか外にいるかを検知する手段とか
らなり、放射シールドは熱の出入りを遮断する材料で作
られており、開閉手段は人工衛星が地球の陰に入ると放
射シールドを開いて広げ、地球の隘に入るとこれを閉じ
ることを特徴とする。(Means for Solving the Problems) As shown in FIGS. 1 and 2, the heat insulating device for an artificial satellite according to the present invention is a heat insulating device that is applied to a part or all of the outside of the artificial satellite. , consists of a radiation shield that can be opened and closed, a means for opening and closing this radiation shield, and a means for detecting whether the satellite is inside or outside the Earth's shadow relative to sunlight, and the radiation shield blocks heat in and out. The opening/closing means is characterized by opening and expanding the radiation shield when the satellite enters the Earth's shadow, and closing it when the satellite enters the Earth's depths.
（実施例）
２通りの実施例を挙げて本発明の人工衛星の保温装置の
説明をする。(Example) The artificial satellite heat retention device of the present invention will be explained using two examples.
第１の実施例を第１図に示す。この実施例では本発明の
保温装置を２組用意し、これらを人工衛星の構体パネル
７０対向する２面に取り付けられた太陽電池パネル４に
それぞれ適用した。その他ニ、サーマルルーバ６とサー
マルブランケット５も従来通りに取り付けである。放射
ンールドｌはフレキシブルで蛇腹状の断熱材の薄い層の
両側にアルミニウムを蒸着して作ったっ開閉手段はゼン
マイバネ２１とモータ（図示してない）を互いの力が反
対の方向を向くように組み合わせたものである。ゼンマ
イバネ２１はベリリウム鋼の帯で作った。モータを駆動
するとゼンマイバネ２１は力に逆らって帯状に引き出さ
れ、モータの電源を切るとゼンマイバネ２１はモータを
空回りさせて元のゼンマイ状に戻る。放射ンールド１の
一端はスカート３に固定され、他端はこのゼンマイバネ
２１の外側の端に取り付けた。検知手段（）ル１示して
ない）は内蔵している光検出素子で太陽光綴金検出し、
人工衛星が地球の陰の内にいるか外にいるかを検知する
。人工衛星が地球の陰に入って太陽光線が入射しなくな
ると検知手段はこれを検知し開閉手段が作動する。開閉
手段は放射シールド１を広けて第１図（ｂ）に示すよう
に太陽電池パネル４に覆いかぶせて温度が低下するのを
防止する。人工衛星が地球の陰から出ると検知手段はこ
れを検知シフ、開閉手段は放射シールド１をたたみ太陽
電池パネル４に太陽光線が入射する。A first embodiment is shown in FIG. In this example, two sets of heat retaining devices of the present invention were prepared, and these were respectively applied to the solar cell panels 4 attached to two opposing sides of the structure panel 70 of an artificial satellite. Other than that, the thermal louver 6 and the thermal blanket 5 are also attached in the conventional manner. The radiation shield l is made by vapor depositing aluminum on both sides of a thin layer of flexible, bellows-shaped insulation material.The opening/closing means is a combination of a spiral spring 21 and a motor (not shown) so that the forces are directed in opposite directions. It is something that The mainspring spring 21 was made from a band of beryllium steel. When the motor is driven, the spiral spring 21 is pulled out in a band shape against the force, and when the motor is turned off, the spiral spring 21 allows the motor to idle and returns to its original spiral shape. One end of the radiation coil 1 was fixed to the skirt 3, and the other end was attached to the outer end of the spiral spring 21. The detection means (1 not shown) detects sunlight with a built-in photodetection element,
Detects whether a satellite is inside or outside the Earth's shadow. When the satellite enters the shadow of the earth and no sunlight enters it, the detection means detects this and the opening/closing means is activated. The opening/closing means spreads the radiation shield 1 and covers the solar cell panel 4 as shown in FIG. 1(b) to prevent the temperature from decreasing. When the artificial satellite comes out from the shadow of the earth, the detection means detects this and shifts, and the opening/closing means folds the radiation shield 1 so that sunlight is incident on the solar battery panel 4.
第２図に本発明の第２の実施例を示す。放射シ−ルド１
の開閉手段としては互いに反対向きの２方向に力を出せ
るものであればよいが、第２の実施例ではこれに２方向
性の形状記憶合金２２を用いた。この形状記憶合金２２
は、高温時には収縮し低温時には膨張するように処理し
である。形状記憶合金２２の一層はスカート３に固定さ
れ、他端は放射シールド１の自由端に取）付けられてい
る。その際、形状記憶合金２２は放射シールド１の外側
に配置した。人工衛星が地球の陰から出て、太陽熱に暖
められると形状記憶合金２２は収縮し放射シールド１は
たたまれる。人工衛星が地球の陰に入って温度が下がる
と形状記憶合金２２は膨張し、放射シールド１を太陽電
池パネル４の上に広げてこれを保温する。以上のように
、この実施例では形状記憶合金２２が検知手段を兼ねる
から第１の実施例で用いたような検知手段は不要になる
０
放射シールド１の保温効果を高めるために表面に形成す
る層の材質は、アルミニウムに限らない。FIG. 2 shows a second embodiment of the invention. Radiation shield 1
The opening/closing means may be any device that can generate force in two directions opposite to each other, but in the second embodiment, a bidirectional shape memory alloy 22 is used for this. This shape memory alloy 22
is treated so that it contracts at high temperatures and expands at low temperatures. One layer of the shape memory alloy 22 is fixed to the skirt 3 and the other end is attached to the free end of the radiation shield 1. At that time, the shape memory alloy 22 was placed outside the radiation shield 1. When the satellite comes out of the earth's shadow and is warmed by solar heat, the shape memory alloy 22 contracts and the radiation shield 1 folds. When the satellite enters the earth's shadow and its temperature drops, the shape memory alloy 22 expands and spreads the radiation shield 1 over the solar panel 4 to keep it warm. As described above, in this embodiment, the shape memory alloy 22 also serves as a detection means, so the detection means used in the first embodiment is unnecessary. The material of the layer is not limited to aluminum.
赤外線領域で熱輻射率が低い材質の中から使い易いもの
を選べばよい。層を形成する方法としては、蒸着の他に
例えば鍍金や塗装などでもよく、用いる材料に合った適
当な方法を選ぶ。It is sufficient to select an easy-to-use material from among materials with low thermal emissivity in the infrared region. In addition to vapor deposition, the layer may be formed by, for example, plating or painting, and an appropriate method suitable for the material used is selected.
（発明の効果）
本発明の人工衛星の保温装置を用いれば、従来の装置で
は不可能であった人工衛星の外部構造、特に、低温に弱
いが外部に配置せざるを得ない太陽電池パネルの保温を
行うことが可能となる。本発明の保温装置を両面に取り
付ければ、パドル形式の太陽電池パネルの保温も行える
。サーマルルーバを取り付けた面を除いたすべての外部
表面に本発明の保温装置を取り付けて、サーマルブラン
ケットを併用すれば人工衛星の内部の温度制御を一層効
果的に行うことができる。本発明によって、従来の装置
だけでは太陽電池パネルが過度の低温によって損傷する
ことから不可能であった地球の陰を長時間周行する軌道
を用いることが可能になった。(Effects of the Invention) By using the satellite heat retention device of the present invention, it is possible to improve the external structure of the satellite, which was impossible with conventional devices, especially the solar panel, which is sensitive to low temperatures and must be placed outside. It becomes possible to keep warm. By attaching the heat insulating device of the present invention to both sides, it is possible to insulate a paddle-type solar panel. By attaching the heat retaining device of the present invention to all external surfaces except for the surface on which the thermal louvers are attached, and using a thermal blanket in combination, the temperature inside the satellite can be controlled more effectively. The invention makes it possible to use long orbits in the Earth's shadow, which was not possible with conventional equipment alone because the solar panels would be damaged by excessively low temperatures.
第１図は本発明の第１の実施例の保温装置を取り付けた
人工衛星の断面図であり、本図（ａ）は放射シールドを
閉じた状態を、本図（ｂ）は開いた状態をそれぞれ示す
。第２図は本発明の第２の実施例の保温装置を取り付け
た人工衛星の断面図であり、本図（ａ）は放射ンールド
を閉じた状態を、本図（ｂ）は開いた状態をそれぞれ示
す。第３図は従来の温度制御装置だけを取り付けた人工
衛星の断面図である０
１・・・放射シールド、２１・・・ゼンマイバネ、２２
・・・形状記憶合金、３・・・スカート、４・・・太陽
電池パネル、５・・・サーマルブランケット、６・・・
サーマルルーバ、７・・・構体ハ不ル。
代理人 弁理士 本 庄 伸 介
（ａ）
（ｂ）
第１図Figure 1 is a cross-sectional view of an artificial satellite equipped with a heat-retaining device according to the first embodiment of the present invention. Figure (a) shows the radiation shield in a closed state, and Figure (b) shows it in an open state. Each is shown below. Figure 2 is a cross-sectional view of a satellite equipped with a heat-retaining device according to a second embodiment of the present invention. Figure (a) shows the radiation shield in a closed state, and Figure (b) shows it in an open state. Each is shown below. Figure 3 is a cross-sectional view of an artificial satellite equipped with only a conventional temperature control device. 0 1... Radiation shield, 21... Wind-up spring, 22
... Shape memory alloy, 3... Skirt, 4... Solar panel, 5... Thermal blanket, 6...
Thermal louver, 7...The structure is inadequate. Agent Patent Attorney Shinsuke Honjo (a) (b) Figure 1
Claims (4)
装置であつて、開閉自在の放射シールドと、この放射シ
ールドの開閉手段と、人工衛星が太陽光線に対して地球
の陰の内にいるか外にいるかを検知する手段とからなり
、放射シールドは熱の出入りを遮断する材料で作られて
おり、開閉手段は人工衛星が地球の陰に入ると放射シー
ルドを広げ、地球の陰に入るとこれを閉じることを特徴
とする人工衛星の保温装置。(1) A heat insulation device applied to part or all of the exterior of an artificial satellite, which includes a radiation shield that can be opened and closed, a means for opening and closing this radiation shield, and a heating device that protects the satellite from sunlight in the shadow of the earth. The radiation shield is made of a material that blocks heat in and out, and the opening/closing means expands the radiation shield when the satellite enters the earth's shadow. A heating device for an artificial satellite, which is characterized by closing this.
ある特許請求の範囲第１項に記載の人工衛星の保温装置
。(2) The heating device for an artificial satellite according to claim 1, wherein the opening/closing means is a combination of a spring and a motor.
合金を用いた特許請求の範囲第１項に記載の人工衛星の
保温装置。(3) A heat-retaining device for an artificial satellite according to claim 1, which uses a bidirectional shape memory alloy as the opening/closing means and the detection means.
パネルに適用した特許請求の範囲第１項に記載の人工衛
星の保温装置。(4) A heat-retaining device for an artificial satellite according to claim 1, which is applied to a solar panel provided as a part of the outside of the artificial satellite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61173430A JPS6328800A (en) | 1986-07-23 | 1986-07-23 | Heat insulator for artificial satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61173430A JPS6328800A (en) | 1986-07-23 | 1986-07-23 | Heat insulator for artificial satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6328800A true JPS6328800A (en) | 1988-02-06 |
Family
ID=15960308
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP61173430A Pending JPS6328800A (en) | 1986-07-23 | 1986-07-23 | Heat insulator for artificial satellite |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6328800A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0392400A (en) * | 1989-09-05 | 1991-04-17 | Mitsui Eng & Shipbuild Co Ltd | Method for forming ice shape |
-
1986
- 1986-07-23 JP JP61173430A patent/JPS6328800A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0392400A (en) * | 1989-09-05 | 1991-04-17 | Mitsui Eng & Shipbuild Co Ltd | Method for forming ice shape |
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