JPS62166200A - Method of neutralizing charging - Google Patents
Method of neutralizing chargingInfo
- Publication number
- JPS62166200A JPS62166200A JP728786A JP728786A JPS62166200A JP S62166200 A JPS62166200 A JP S62166200A JP 728786 A JP728786 A JP 728786A JP 728786 A JP728786 A JP 728786A JP S62166200 A JPS62166200 A JP S62166200A
- Authority
- JP
- Japan
- Prior art keywords
- charged
- spacecraft
- solar cell
- electron beam
- charging
- 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
- 238000000034 method Methods 0.000 title claims description 8
- 230000003472 neutralizing effect Effects 0.000 title description 2
- 230000005591 charge neutralization Effects 0.000 claims description 4
- 239000002245 particle Substances 0.000 claims description 4
- 238000010894 electron beam technology Methods 0.000 description 5
- 230000005611 electricity Effects 0.000 description 3
- 230000007257 malfunction Effects 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000004020 conductor Substances 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 239000006059 cover glass Substances 0.000 description 1
- 230000002542 deteriorative effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000012212 insulator Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002985 plastic film Substances 0.000 description 1
- 239000010453 quartz Substances 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- -1 tiles Substances 0.000 description 1
Landscapes
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
- Control Of Charge By Means Of Generators (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) [Summary] 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〕
本発明は人工衛星または宇宙飛行体の帯電を中和する方
法に関する。DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to a method for neutralizing electrical charges on an artificial satellite or spacecraft.
宇宙空間を飛行する人工衛星や宇宙飛行体は、長時間太
陽光が当っている部分の表面から光電子が飛び出して正
電位に帯電したり、宇宙空間の各種の荷電粒子が付着し
て帯電したりする。帯電による静電気の電圧は致方ボル
トから数１０万ボルトに達することも有り、放電して搭
載機器や素子を破壊または劣化させたり、誤動作させた
りする。Artificial satellites and space vehicles flying in outer space are charged with positive potential due to photoelectrons ejecting from the surface of parts that are exposed to sunlight for long periods of time, or charged with various charged particles in outer space that adhere to them. do. The voltage of static electricity caused by charging can reach anywhere from a single volt to several hundreds of thousands of volts, which can discharge and destroy or deteriorate installed equipment and elements, or cause them to malfunction.
従来、人工衛星または宇宙飛行体の帯電を中和する有効
な手段はなく、せいぜい各部の導電性を良くして帯電を
なるべく防止しようとする消極的手法がとられているＫ
すぎなかった。Until now, there has been no effective means to neutralize static electricity on artificial satellites or spacecraft, and passive methods have been taken to prevent static electricity as much as possible by improving the conductivity of each part.
It wasn't too much.
上述した従来の方法は、効果が不充分で、前述した放電
を防止できないという欠点が有る。特に人工衛星や宇宙
飛行体の表面は熱制御用の金属蒸着プラスチックシート
やタイル、石英のカバーガラスなど絶縁体でおおわれる
ことが多く、これらの表面を、それぞれの素材の特性を
損なわないで完全に導体化することは非常に難しい。The above-mentioned conventional methods have the disadvantage that they are insufficiently effective and cannot prevent the above-mentioned discharge. In particular, the surfaces of artificial satellites and spacecraft are often covered with insulating materials such as metal-deposited plastic sheets, tiles, and quartz cover glass for thermal control, and these surfaces can be completely covered without impairing the characteristics of each material. It is very difficult to make it into a conductor.
本発明の帯電中和方法は、人工衛星または宇宙飛行体の
帯電部分に帯’ｍ′Ｂｓ、位と逆極性の荷電粒子を与え
ることにより人工衛星または宇宙飛行体の帯電部分を中
和するものである。The charge neutralization method of the present invention neutralizes a charged portion of an artificial satellite or spacecraft by applying charged particles of opposite polarity to the charged portion of the artificial satellite or spacecraft. It is.
したがりて、絶縁体でおおわれた帯電部分でも中和する
ことができる。Therefore, even charged parts covered with an insulator can be neutralized.
本発明の実施例について図面を参照して説明する。 Embodiments of the present invention will be described with reference to the drawings.
第１図は本発明の帯電中和方法の一実施例を示す図であ
る。FIG. 1 is a diagram showing an embodiment of the charge neutralization method of the present invention.
スペースステーション１ ＆ｔ、太５ｉ＝７ ｖイ２を
有し、太陽電池アレイ２は太陽光３が連続して当るよう
に太陽を追って回転する。太陽光３が太陽電池アレイ２
に当ると光電子４を放出するので徐々に太陽電池アレイ
２は正電位に帯電する。この正電位に帯電した部分に電
子ビーム発生器５から発生した電子ビーム６を照射し、
電子を与えることにより中和する。The space station 1 &t has 5i=7vi2, and the solar cell array 2 rotates following the sun so that sunlight 3 hits it continuously. Sunlight 3 is solar cell array 2
When the solar cell array 2 is hit by a photoelectron 4, it emits photoelectrons 4, so that the solar cell array 2 is gradually charged to a positive potential. This positively charged part is irradiated with an electron beam 6 generated from an electron beam generator 5,
Neutralize by donating electrons.
この電子ビーム発生器５は、陰極線管などに用いられる
電子ビーム発生器と同じ原理のもので、電子銃や加速電
極、制御格子、偏向板などから構成され、ビームの強さ
や照射方向などを制御することができ、太陽電池プレイ
全面を走査したり、一部のみ照射することが可能である
。This electron beam generator 5 has the same principle as the electron beam generator used in cathode ray tubes, etc., and is composed of an electron gun, accelerating electrodes, control grids, deflection plates, etc., and controls the beam intensity, irradiation direction, etc. It is possible to scan the entire surface of the solar cell play or to irradiate only a part of it.
以上説明したように本発叫は、人工衛星または宇宙飛行
体の帯電部分に帯電電位と逆極性の荷電粒子を与えて帯
電を中和することにより、搭載機器や素子が静電気放電
で破壊または劣化したり、誤動作することを防止できる
効果がある。As explained above, this method applies charged particles of opposite polarity to the charged potential of the charged parts of an artificial satellite or spacecraft to neutralize the charge, thereby destroying or deteriorating the onboard equipment and elements due to electrostatic discharge. This has the effect of preventing malfunctions or malfunctions.
第１図は本発明の帯電中和方法の一実施例を示す図であ
る。
１・・・・・・・・・スペース・ステーション、２・・
・・・・・・・・太陽電池プレイ・３・・・・・・・・
・太 陽 光１４・・・・・・・・・光 電
子、５・・・・・・・・・電子ビーム発生器、６・
・・・・・・・・電 子 ビ − ム。FIG. 1 is a diagram showing an embodiment of the charge neutralization method of the present invention. 1... Space Station, 2...
・・・・・・・・・Solar battery play・３・・・・・・・・・
・Solar light 14・・・・・・Photoelectron, 5・・・・・・Electron beam generator, 6・
......electronic beam.
Claims (1)
性の荷電粒子を与えることにより、人工衛星または宇宙
飛行体の帯電部分を中和する帯電中和方法。A charge neutralization method that neutralizes a charged part of an artificial satellite or spacecraft by applying charged particles of opposite polarity to the charged potential to the charged part of the satellite or spacecraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP728786A JPS62166200A (en) | 1986-01-16 | 1986-01-16 | Method of neutralizing charging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP728786A JPS62166200A (en) | 1986-01-16 | 1986-01-16 | Method of neutralizing charging |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62166200A true JPS62166200A (en) | 1987-07-22 |
Family
ID=11661818
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP728786A Pending JPS62166200A (en) | 1986-01-16 | 1986-01-16 | Method of neutralizing charging |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62166200A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021117681A1 (en) * | 2019-12-12 | 2021-06-17 | 弘樹 渋谷 | Static electricity eliminating device |
-
1986
- 1986-01-16 JP JP728786A patent/JPS62166200A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021117681A1 (en) * | 2019-12-12 | 2021-06-17 | 弘樹 渋谷 | Static electricity eliminating device |
| US11839012B2 (en) | 2019-12-12 | 2023-12-05 | Hiroki Shibuya | Static eliminator |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP3169875B2 (en) | Ion thruster with long-lived ion-optical system | |
| GB1280305A (en) | Ion implantation apparatus | |
| US8511616B2 (en) | Solar powered excess electron emission device | |
| Rosen | Spacecraft charging: Environment-induced anomalies | |
| JP3362525B2 (en) | Ion implanter | |
| US2520603A (en) | Method of and means for utilizing charged-particle radiation | |
| JPS62166200A (en) | Method of neutralizing charging | |
| JPS6212625B2 (en) | ||
| US3714439A (en) | Image comparison device and method | |
| EP0637900A1 (en) | Method and device for the extraction of electrons from a space vehicle | |
| US3778623A (en) | Charging method of electrophotographic materials | |
| Levy et al. | Simulation of in-flight ESD anomalies triggered by photoemission, micrometeoroid impact and pressure pulse | |
| US3240988A (en) | Storage tube with signal multiplication adjustment | |
| US4005438A (en) | Device with control grid for electrostatographic reproduction of an optical image | |
| ES359265A1 (en) | Image amplification in ionography by avalanche method | |
| US3461340A (en) | Image-translating device | |
| Takahashi et al. | ETS-VIII solar PDL plasma interaction problem approach | |
| Stevens et al. | Voltage gradients in solar array cavities as possible beeakdown sites in spacecraft-charging-induced discharges | |
| US3715640A (en) | Corona charging process and apparatus in electrophotography | |
| JP2663564B2 (en) | Ion beam irradiation equipment | |
| TOYODA | High‐Voltage Power Generation on Spacecraft | |
| GB1530031A (en) | Charged particle beam scanning device | |
| Olsen | Electron beam experiments at high altitudes | |
| JPS6147048A (en) | Device for preventing electrification of target of ion implantation device | |
| Taylor | Implications of possible shuttle charging |