JPS62228183A - Method for detecting attitude and orbit of revolving artificial satellite - Google Patents
Method for detecting attitude and orbit of revolving artificial satelliteInfo
- Publication number
- JPS62228183A JPS62228183A JP61072231A JP7223186A JPS62228183A JP S62228183 A JPS62228183 A JP S62228183A JP 61072231 A JP61072231 A JP 61072231A JP 7223186 A JP7223186 A JP 7223186A JP S62228183 A JPS62228183 A JP S62228183A
- Authority
- JP
- Japan
- Prior art keywords
- satellite
- orbit
- attitude
- artificial satellite
- beacon
- 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 15
- 238000001514 detection method Methods 0.000 abstract description 2
- 230000000007 visual effect Effects 0.000 abstract 1
- 230000005856 abnormality Effects 0.000 description 2
- 235000006693 Cassia laevigata Nutrition 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 241000522641 Senna Species 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 229940124513 senna glycoside Drugs 0.000 description 1
Landscapes
- Navigation (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
Description
【発明の詳細な説明】
（産業上の利用分野〕
本発明は、周回人工衛星の姿勢および軌道を検知する方
法に関する。DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a method for detecting the attitude and orbit of an orbiting artificial satellite.
（従来の技術およびその問題点）
よく知られているように、地球を周回する人工衛星はそ
れぞれの目的に応じた軌道および姿勢つまり向きを与え
られている。(Prior Art and its Problems) As is well known, artificial satellites orbiting the earth are given orbits and attitudes, or directions, depending on their respective purposes.
ランドサットのような地形観測用の人工衛星を例にとれ
ば、衛星は観測を行うためには観測地点の上空を通らな
ければならない。また、観測に際しては、例えば望遠鏡
のような観測手段が観測地点に、また、データの回収に
際しては送信アンテナが地上局の方向にそれぞれ正しく
向い−Ｃいなければならない。また、打上げに際しては
、高度がわずか数キロメートル不足しても衛星の寿命は
著しく縮まる。このように姿勢および軌道に狂いが生じ
ると衛星は所定の性能が発揮できない。そこで、衛星の
軌道修正と姿勢制御が行われる。そのためには、先ず、
衛星の軌道と姿勢を精密に検知することが必要である。For example, in the case of a topographical observation satellite such as Landsat, the satellite must pass over an observation point in order to conduct an observation. Furthermore, during observation, the observation means such as a telescope must be properly oriented at the observation point, and when collecting data, the transmitting antenna must be properly oriented toward the ground station. Furthermore, when launching a satellite, even a shortfall of just a few kilometers in altitude will significantly shorten the lifespan of the satellite. If the attitude and orbit become erroneous as described above, the satellite will not be able to exhibit its desired performance. There, the satellite's orbit is corrected and its attitude is controlled. To do so, first of all,
It is necessary to precisely detect the orbit and attitude of the satellite.
人工衛星の姿勢を知る方法としては、従来、衛星の向き
を知る基準として太陽を用いる太陽センサおよび地球を
用いる地球センサをともに衛星に搭載し衛星の姿勢を検
知する方法がある。この方法では、衛星が太陽に照′ら
されている間（日照中）は太陽センサを用い、衛星が地
球の影に入ると（日食中）地球センサを用いる。ところ
が太陽に較べて、地球の見かけの角度ははるかに大きい
だけでなく、地平線の輪郭も空気層の影響で明瞭ではな
いから地球センナの精度は太陽センナより本質的に劣る
。A conventional method for determining the attitude of an artificial satellite is to detect the attitude of the satellite by mounting both a sun sensor using the sun and an earth sensor using the earth as a reference for determining the orientation of the satellite. This method uses a sun sensor while the satellite is illuminated by the sun (during sunshine) and uses an earth sensor when the satellite enters the Earth's shadow (during a solar eclipse). However, the Earth's apparent angle is much larger than that of the Sun, and the outline of the horizon is not clear due to the influence of the air layer, so the accuracy of the Earth Senna is essentially inferior to that of the Sun Senna.
また、軌道を検知する方法としては、地上局から衛星に
向けて発射し衛星が中継した電波を地上局が受信するこ
とにより衛星の位置を知る方法がある。この方法では、
低軌道の衛星の場合は特に、１個所の地上局がカバーで
きる軌道上の範囲が狭いから、軌道全域にわたって監視
する必要があれば、軌道に沿って多数の地上局を配置し
なければならない。実際には、地上局の数は限られてい
るから、衛星が地上局から見通しの効く位置にいる時間
より、ブラインドつまり見通しの効かない位置にいる時
間の方が長い。ブラインドにいる間は、衛星に指令を送
ることも、また、衛星に異変が起きた場合これを探知す
ることも従ってコントロールすることもできない。Further, as a method for detecting the orbit, there is a method in which the position of the satellite is known by the ground station receiving radio waves that are emitted from a ground station toward the satellite and relayed by the satellite. in this way,
Particularly in the case of low-orbit satellites, a single ground station can only cover a narrow range in orbit, so if it is necessary to monitor the entire orbit, many ground stations must be placed along the orbit. In reality, because there are only a limited number of ground stations, the satellite spends more time in a blind position than in a line-of-sight position from a ground station. While blind, you cannot send commands to the satellite, nor can you detect or control any abnormalities that occur to the satellite.
本発明の目的は、上に記したような欠点のない、周回人
工衛星の姿勢および軌道の検知を高い精度で行う方法を
提供することにある。An object of the present invention is to provide a method for detecting the attitude and orbit of an orbiting artificial satellite with high accuracy, without the above-mentioned drawbacks.
（問題点を解決するための手段）
本発明の方法は、第１図の一実施例が示すように、地球
を周回する人工衛星の姿勢および軌道を検知する方法で
あって、複数個の静止衛星（２Ａ。(Means for Solving the Problems) As shown in an embodiment in FIG. 1, the method of the present invention is a method for detecting the attitude and orbit of an artificial satellite orbiting the earth. Satellite (2A.
２”１２Ｃ）に互いに異なったビーコン波の発信器を搭
載するとともに、検知する対象である周回人工衛星１に
、前記ビーコン波のＲＦセンナを搭載することにより、
前記周回人工衛星ｌが軌道上を移動しながら、前記静止
衛星（２人１２Ｂ１２Ｇ）から発信されるビーコン波を
順次に受信し、そのビーコン波を発信した静止衛星の高
度と位置を基準として自らの姿勢および軌道を知ること
を特徴とする。By mounting different beacon wave transmitters on the 2"12C) and mounting an RF sensor for the beacon waves on the orbiting artificial satellite 1 which is the object to be detected,
While moving in orbit, the orbiting artificial satellite 1 sequentially receives beacon waves transmitted from the geostationary satellites (2 people 12B12G), and determines its own position based on the altitude and position of the geostationary satellite that transmitted the beacon waves. It is characterized by knowing the attitude and trajectory.
（実絶ρす９ 第１図に従って、本発明の詳細な説明する。(Jitsutsu ρsu 9 The present invention will be described in detail with reference to FIG.
ここに挙げた実施例において、用意された静止衛星の数
は３個（２Ａ、 ２Ｂｔ ２Ｃ）であり、それ等は
軌道２１上等間隔に配置されている。検知対象の人工衛
星１は地球３を周回する軌道１１に乗っている。また、
静止衛星にはそれぞれ異なったビーコン波の発信器が積
んであり、衛星１にはそれら３植類のビーコン波の専用
ＲＦセ／すが１個ずつ計３個積んである。衛星１は静止
衛星２人から発射されるビーコン波を受信し、受信した
ビーコン波の種類からそのビーコン波を発射した静止衛
星が２人であることを知る。予め分っている静止衛星２
Ａの位置と高度から自らの姿勢と軌道を検知する。衛星
１は軌道上を移動し次々と視界に現れる静止衛星２Ｂ、
２ｃからのビーコン波を受信し同様に姿勢および軌
道を検知しながら地球を周回する。In the embodiment mentioned here, the number of prepared geostationary satellites is three (2A, 2Bt, 2C), and they are arranged at equal intervals on the orbit 21. An artificial satellite 1 to be detected is in an orbit 11 orbiting the earth 3. Also,
Each of the geostationary satellites is equipped with a different beacon wave transmitter, and the satellite 1 is equipped with a total of three RF transmitters for each of the three types of beacon waves. Satellite 1 receives beacon waves emitted from two geostationary satellites, and learns from the type of the received beacon waves that the two geostationary satellites emitted the beacon waves. Geostationary satellite 2 known in advance
Detects its own attitude and trajectory from A's position and altitude. Satellite 1 moves in orbit, and geostationary satellite 2B appears one after another in view.
It orbits the earth while receiving beacon waves from 2c and similarly detecting its attitude and orbit.
この際、衛星１の視界の中に、常に少くとも１個の静止
衛星が有るように、幾つかの静止衛星を配置しておけば
、姿勢の制御と軌道の修正とを連続的に行うことができ
る。衛星１に搭載したＲＦセ／すで姿勢と軌道両方の検
知を行うので、それらの狂いを衛星内で知ることができ
る。従って、搭載したコンピュータをそのようにプログ
ラムしておけば、地上局からの指令によらずに、液体ロ
ケットなどの制御手段を作動させて自ら姿勢制御と軌道
修正をすることができる。At this time, if several geostationary satellites are placed so that at least one geostationary satellite is always within the field of view of satellite 1, attitude control and orbit correction can be performed continuously. I can do it. Since the RF unit installed on Satellite 1 detects both the attitude and orbit, it is possible to detect any deviations within the satellite. Therefore, if the onboard computer is programmed in this way, it can operate control means such as liquid rockets and perform attitude control and orbit correction by itself without receiving commands from a ground station.
また、衛星ｌが地上局のブラインドにいる間も、その時
衛星１を視界に捕えている静止衛星を中継すれば、衛星
ｌに指令を送ることも異変を探知しこれをコントロール
することもできる。Furthermore, even while satellite 1 is in the blind position of the ground station, if the geostationary satellite that has satellite 1 in its field of view is relayed, it is possible to send commands to satellite 1 and to detect and control abnormalities.
（発明の効果）
本発明の方法は、太陽を基準とする太陽センナや地球を
基準とし精度の劣る地球センサを用いない。従って、日
照や日食の影響を受けないばかりでなく、静止衛星その
ものの位置の制御は別途精密に行われるから、これを基
準として用いる本発明の方法の検知精度は極めて高い。(Effects of the Invention) The method of the present invention does not use a solar sensor that uses the sun as a reference or an earth sensor that uses the earth as a reference and has poor accuracy. Therefore, not only is it not affected by sunlight or solar eclipse, but also the position of the geostationary satellite itself is precisely controlled separately, so the detection accuracy of the method of the present invention using this as a reference is extremely high.
また、本発明の方法によれば、検知対象の周回人工衛星
を軌道上の大部分または総ての位置で、地上局のコノト
ロール下に置くことができる。Further, according to the method of the present invention, the orbiting artificial satellite to be detected can be placed under control of the ground station at most or all positions on the orbit.
第１図は、本発明の方法の一実施例を示す配置図である
。
■・・・周回人工衛星、２人、２Ｂ、２Ｃ・・・静止衛
星、３・・・地球、１１・・・周回軌道、２１・・・静
止軌道。
代理人 弁理士 本 庄 伸 介
第１図FIG. 1 is a layout diagram showing an embodiment of the method of the present invention. ■...Orbiting satellite, 2 people, 2B, 2C...Geostationary satellite, 3...Earth, 11...Orbiting orbit, 21...Geostationary orbit. Agent Patent Attorney Shinsuke Honjo Figure 1
Claims (2)
する方法において、複数個の静止衛星に互いに異なつた
ビーコン波の発信器を搭載するとともに、前記周回人工
衛星に前記ビーコン波のＲＦセンサを搭載することによ
り、前記周回人工衛星が軌道上を移動しながら、前記静
止衛星から発信されるビーコン波を受信し、そのビーコ
ン波を発信した静止衛星の高度と位置を基準として自ら
の姿勢および軌道を知ることを特徴とする周回人工衛星
の姿勢および軌道の検知方法。(1) In a method for detecting the attitude and orbit of an artificial satellite orbiting the earth, a plurality of geostationary satellites are equipped with different beacon wave transmitters, and the orbiting artificial satellite is equipped with an RF sensor for the beacon waves. By installing this onboard, the orbiting artificial satellite receives beacon waves transmitted from the geostationary satellite while moving in orbit, and adjusts its own attitude and orbit based on the altitude and position of the geostationary satellite that transmitted the beacon wave. A method for detecting the attitude and orbit of an orbiting artificial satellite, which is characterized by knowing the attitude and orbit of an orbiting artificial satellite.
うちの少なくとも１つが検知対象の周回人工衛星の視界
内に常に存在するように前記静止衛星の相対位置が定め
てあることを特徴とする特許請求の範囲第１項記載の周
回人工衛星の姿勢および軌道の検知方法。(2) A plurality of geostationary satellites are arranged, and the relative positions of the geostationary satellites are determined so that at least one of the geostationary satellites is always within the field of view of the orbiting artificial satellite to be detected. A method for detecting the attitude and orbit of an orbiting artificial satellite according to claim 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61072231A JPS62228183A (en) | 1986-03-28 | 1986-03-28 | Method for detecting attitude and orbit of revolving artificial satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61072231A JPS62228183A (en) | 1986-03-28 | 1986-03-28 | Method for detecting attitude and orbit of revolving artificial satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62228183A true JPS62228183A (en) | 1987-10-07 |
Family
ID=13483287
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP61072231A Pending JPS62228183A (en) | 1986-03-28 | 1986-03-28 | Method for detecting attitude and orbit of revolving artificial satellite |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62228183A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008292480A (en) * | 2007-05-18 | 2008-12-04 | Astrium Sas | Satellite positioning method and facility of the same |
-
1986
- 1986-03-28 JP JP61072231A patent/JPS62228183A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008292480A (en) * | 2007-05-18 | 2008-12-04 | Astrium Sas | Satellite positioning method and facility of the same |
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