JPH01132500U - - Google Patents
Info
- Publication number
- JPH01132500U JPH01132500U JP2888788U JP2888788U JPH01132500U JP H01132500 U JPH01132500 U JP H01132500U JP 2888788 U JP2888788 U JP 2888788U JP 2888788 U JP2888788 U JP 2888788U JP H01132500 U JPH01132500 U JP H01132500U
- Authority
- JP
- Japan
- Prior art keywords
- orbit
- geostationary satellite
- geostationary
- original
- control
- 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
- 238000012423 maintenance Methods 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 3
- 230000000284 resting effect Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 4
Landscapes
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Description
第１図は本軌道保持制御機能の概観を説明する
ための図、第２図は本軌道保持制御機能に必要な
地上局を説明するための図、第３図は本軌道保持
制御機能に必要な静止衛星内部機器を説明するた
めの図、第４図は従来の軌道保持制御を説明する
ための図である。
図中、２ａ及び２ｂは地上の２つの特定地域に
設置された地上局から発信される２つの周波数の
無変調信号、１０は２つの周波数の無変調信号を
受信するビームアンテナ、１１は受信した２つの
無変調信号を基に静止衛星の本来の静止位置から
のずれを検出するＲＦセンサー、１２はＲＦセン
サーによつて検出されたずれから静止衛星の軌道
を推定し、静止衛星を本来の静止軌道へ遷移させ
るための制御量、制御方向、及び制御時刻を計算
するマイクロプロセツサ、１３は静止衛星を本来
の静止軌道へ遷移させる制御を行う推進系である
。尚、図中、同一あるいは相当部分には、同一符
号を付して示してある。
Figure 1 is a diagram to explain the overview of this orbit maintenance control function, Figure 2 is a diagram to explain the ground station required for this orbit maintenance control function, and Figure 3 is a diagram to explain the ground station required for this orbit maintenance control function. FIG. 4 is a diagram for explaining conventional orbit maintenance control. In the figure, 2a and 2b are unmodulated signals of two frequencies transmitted from ground stations installed in two specific areas on the ground, 10 is a beam antenna that receives unmodulated signals of two frequencies, and 11 is a receiving antenna. An RF sensor detects the deviation of a geostationary satellite from its original geostationary position based on two unmodulated signals, and 12 estimates the orbit of the geostationary satellite from the deviation detected by the RF sensor, and returns the geostationary satellite to its original geostationary position. A microprocessor 13 calculates a control amount, a control direction, and a control time for transitioning to an orbit, and a propulsion system 13 performs control to transition a geostationary satellite to its original geostationary orbit. In the drawings, the same or corresponding parts are designated by the same reference numerals.
Claims (1)
発信される２つの周波数の無変調信号を受信する
ビームアンテナと、受信した２つの無変調信号を
基に静止衛星の本来の静止位置からのずれを検出
するＲＦセンサーと、このＲＦセンサーによつて
検出されたずれから静止衛星の軌道を推定し、静
止衛星を本来の静止軌道へ遷移させるための制御
量、制御方向、及び制御時刻を計算するマイクロ
プロセツサと、マイクロプロセツサで計算された
制御量、制御方向、及び制御時刻に従つて静止衛
星を本来の静止軌道へ遷移させる制御を行う推進
系から成る静止衛星の軌道保持のための、２つの
周波数の無変調信号の受信、静止衛星の本来の静
止位置からのずれの検出、静止衛星の軌道推定、
静止衛星を本来の静止軌道へ遷移させるための制
御量、制御方向、及び制御時刻の計算、及び静止
衛星を本来の静止軌道へ遷移させる制御を静止衛
星内で自動的に行う軌道保持制御機能を備えた静
止衛星。 A beam antenna receives unmodulated signals of two frequencies emitted from ground stations installed in two specific areas on the ground, and detects the deviation of a geostationary satellite from its original resting position based on the two received unmodulated signals. The orbit of the geostationary satellite is estimated from the RF sensor that detects the RF sensor and the deviation detected by this RF sensor, and the control amount, control direction, and control time for transitioning the geostationary satellite to the original geostationary orbit are calculated. For maintaining the orbit of a geostationary satellite, it consists of a microprocessor and a propulsion system that controls the transition of the geostationary satellite to its original geostationary orbit according to the control amount, control direction, and control time calculated by the microprocessor. Receiving unmodulated signals of two frequencies, detecting the deviation of a geostationary satellite from its original geostationary position, estimating the orbit of a geostationary satellite,
An orbit maintenance control function that automatically calculates the control amount, control direction, and control time for transitioning a geostationary satellite to its original geosynchronous orbit, and automatically controls the transition of a geostationary satellite to its original geosynchronous orbit. geostationary satellite equipped with
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2888788U JPH01132500U (en) | 1988-03-04 | 1988-03-04 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2888788U JPH01132500U (en) | 1988-03-04 | 1988-03-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH01132500U true JPH01132500U (en) | 1989-09-08 |
Family
ID=31252616
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2888788U Pending JPH01132500U (en) | 1988-03-04 | 1988-03-04 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH01132500U (en) |
-
1988
- 1988-03-04 JP JP2888788U patent/JPH01132500U/ja active Pending
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