JPH02117497A - Controlling method for satellite orbit - Google Patents
Controlling method for satellite orbitInfo
- Publication number
- JPH02117497A JPH02117497A JP63269714A JP26971488A JPH02117497A JP H02117497 A JPH02117497 A JP H02117497A JP 63269714 A JP63269714 A JP 63269714A JP 26971488 A JP26971488 A JP 26971488A JP H02117497 A JPH02117497 A JP H02117497A
- Authority
- JP
- Japan
- Prior art keywords
- satellite
- orbit
- alleys
- cell
- solar cell
- 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 4
- 238000002347 injection Methods 0.000 claims abstract description 4
- 239000007924 injection Substances 0.000 claims abstract description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000003491 array Methods 0.000 description 2
- 239000012535 impurity Substances 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
Landscapes
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は衛星の軌道制御方式に関し、特に太陽電池アレ
イを搭載した衛星の姿勢外乱を最小化する衛星の軌道制
御方式に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a satellite orbit control system, and more particularly to a satellite orbit control system that minimizes attitude disturbance of a satellite carrying a solar cell array.
通常、衛星に搭載された太陽電池アレイは軌道上で展開
すると、そのままの状態で運行するのが一般である。従
来、この種の衛星の軌道制御方式は、太陽電池アレイを
展開した衛星がスラスタの噴射、たとえば、ガスジェッ
トのプルーム（ｐｌｕｍｅ）を用いて軌道修正を行った
場合、スラスタのプルームが太陽電池アレイに衝突する
現象、いわゆるブルームインピジメントにより南北と東
西方向の結合が生じ所定の姿勢制御ができないことがあ
る。Normally, once a solar array mounted on a satellite is deployed in orbit, it is generally operated as is. Conventionally, in the orbit control method of this type of satellite, when a satellite with a solar array deployed makes orbit correction using thruster injection, for example, a gas jet plume, the thruster plume Due to the so-called bloom impingement phenomenon, the north-south and east-west directions may be coupled, making it impossible to maintain the desired attitude control.
上述した従来の衛星の軌道制御方式は、このようなブル
ームインビジメントにより南北と東西方向の結合が生ず
るので、衛星の所定の軌道修正ができないのみならず、
太陽電池アレイが大きく振動する等の衛星の外乱が発生
する欠点があった。The above-mentioned conventional satellite orbit control method not only cannot correct the satellite's orbit, but also cannot correct the satellite's orbit as the north-south and east-west directions are coupled due to such bloom impurities.
This had the disadvantage of causing disturbances to the satellite, such as large vibrations in the solar array.
本発明の衛星の軌道制御方式は、衛星に搭載される展開
と収納が可能な太陽電池アレイと、前記太陽電池アレイ
を支持し、かつ、駆動する駆動用支持体とを備え、前記
衛星のスラスタの噴射による軌道修正中は前記太陽電池
アレイを収納することを特徴とする。A satellite orbit control system according to the present invention includes a solar cell array mounted on a satellite that can be expanded and retracted, and a drive support that supports and drives the solar cell array, and a thruster of the satellite. It is characterized in that the solar cell array is retracted during orbit correction by injection of.
次に、本発明について図面を参照して説明する。 Next, the present invention will be explained with reference to the drawings.
第１図は本発明の一実施例の構成図であり、太陽電池ア
レイが展開された状態を示している。また、第２図は第
１図の実施例において太陽電池アレイが衛星本体に収納
された状態図を示している。第１図の実施例は北側の太
陽電池アレイ１、南側の太陽電池アレイ２、衛星本体３
、スラスタ４．５、駆動用支持体６．７から構成されて
いる。FIG. 1 is a block diagram of an embodiment of the present invention, showing a solar cell array in an expanded state. Further, FIG. 2 shows a state diagram in which the solar cell array is housed in the satellite body in the embodiment of FIG. 1. The embodiment shown in Figure 1 is a solar cell array 1 on the north side, a solar cell array 2 on the south side, and a satellite main body 3.
, a thruster 4.5, and a driving support 6.7.
今、展開と収納が可能な太陽電池アレイ１，２を搭載し
た衛星本体３が、スラスタ４．５により軌道修正を行う
場合、軌道上で展開された太陽電池アレイ１，３を駆動
用支持体６．７により第２図のように収納状態にする。Now, when the satellite main body 3 carrying the solar cell arrays 1 and 2 that can be deployed and stowed makes orbit correction using the thrusters 4.5, the solar cell arrays 1 and 3 that have been deployed in orbit are moved to a driving support. Step 6.7 brings it into the storage state as shown in Figure 2.
なお、太陽電池アレイ収納時には衛星本体３に搭載され
たバッテリから衛星本体の装置に電力を供給する。第２
図のような収納状態とすることにより、スラスタのブル
ームが太陽電池アレイに衝突しない軌道制御を実現する
ことができる。Note that when the solar cell array is stored, power is supplied from the battery mounted on the satellite main body 3 to the equipment in the satellite main body. Second
By storing the spacer as shown in the figure, it is possible to achieve orbit control in which the bloom of the thruster does not collide with the solar cell array.
以上説明したように本発明は、衛星の軌道修正を行う際
に事前に太陽電池アレイを収納しておくことにより、衛
星の軌道制御を正常に行い、さらに、衛星の姿勢外乱等
を最小化できる効果がある。As explained above, by storing the solar cell array in advance when correcting the orbit of the satellite, the present invention can normally control the orbit of the satellite and further minimize the attitude disturbance of the satellite. effective.
第１図は本発明の一実施例の構成図、第２図は第１図の
実施例における太陽電池アレイを収納した状態図である
。
１．２・・・太陽電池アレイ、３・・・衛星本体、４５
・・・スラスタ、６．７・・・駆動用支持体。FIG. 1 is a block diagram of an embodiment of the present invention, and FIG. 2 is a diagram showing a state in which the solar cell array in the embodiment of FIG. 1 is housed. 1.2...Solar cell array, 3...Satellite body, 45
... Thruster, 6.7... Drive support.
Claims (1)
、前記太陽電池アレイを支持し、かつ、駆動する駆動用
支持体とを備え、前記衛星のスラスタの噴射による軌道
修正中は前記太陽電池アレイを収納することを特徴とす
る衛星の軌道制御方式。A solar cell array mounted on a satellite that can be expanded and retracted, and a driving support that supports and drives the solar cell array, and the solar cell array is mounted on a satellite during orbit correction by injection of thrusters of the satellite. A satellite orbit control method characterized by housing an array.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63269714A JPH02117497A (en) | 1988-10-25 | 1988-10-25 | Controlling method for satellite orbit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63269714A JPH02117497A (en) | 1988-10-25 | 1988-10-25 | Controlling method for satellite orbit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH02117497A true JPH02117497A (en) | 1990-05-01 |
Family
ID=17476150
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP63269714A Pending JPH02117497A (en) | 1988-10-25 | 1988-10-25 | Controlling method for satellite orbit |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH02117497A (en) |
-
1988
- 1988-10-25 JP JP63269714A patent/JPH02117497A/en active Pending
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