JPS5932599A - Control system of attitude of stationary orbit artificial satellite - Google Patents
Control system of attitude of stationary orbit artificial satelliteInfo
- Publication number
- JPS5932599A JPS5932599A JP57142423A JP14242382A JPS5932599A JP S5932599 A JPS5932599 A JP S5932599A JP 57142423 A JP57142423 A JP 57142423A JP 14242382 A JP14242382 A JP 14242382A JP S5932599 A JPS5932599 A JP S5932599A
- Authority
- JP
- Japan
- Prior art keywords
- axis
- sensor
- attitude
- around
- attitude angle
- 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
Landscapes
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (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】
この発明は訂正軌道上全飛翔する三軸安定型の静止軌道
人工衛星の姿勢制御方式に関するものである。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an attitude control system for a three-axis stable geostationary orbit artificial satellite that flies entirely on a corrected orbit.
従来、静止軌道上の三軸姿勢制@l衛星の擬勢誤差検出
器としてロール軸およびピッチ軸まわりの姿勢角誤差を
検出する地球センサがあり、バイアスモーメンタム万式
三軸姿勢制御衛星の険努センサとしては地球センサのみ
が使われ、一方ゼロモーメンタム方式三411費努制御
衛星の姿勢センサとしては地球センサに〃0えてヨーI
IjlIまわυの姿勢角誤走會検出するRFセンサが(
吏われるCとが多い。Conventionally, there has been an earth sensor that detects attitude angle errors around the roll and pitch axes as a pseudo error detector for a three-axis attitude control satellite in a geostationary orbit. Only the earth sensor is used as a sensor, while the attitude sensor for the zero-momentum type 3411 control satellite is the yaw I sensor instead of the earth sensor.
The RF sensor that detects the attitude angle error of IjlI rotation υ is (
There are many C who are scolded.
いずれの場合も殻勢制倶鞘曳は地球センサの姿勢角誤差
検出精度に依存することになるが、地球センサは地球の
赤外@躬エネルギー金検出することから太陽センサ、恒
星センサに比べて姿勢角誤差検出精度が患い。In either case, the shell control system depends on the attitude angle error detection accuracy of the earth sensor, but since the earth sensor detects the earth's infrared energy, it is more sensitive than solar and stellar sensors. Attitude angle error detection accuracy suffers.
この発明は地球センサの姿勢角誤差検出信号に依存する
三軸費努、vlJdll精度金より良くするため。This invention relies on the attitude angle error detection signal of the earth sensor to improve the three-axis cost effort and vljdll accuracy.
My止軌道上で衛星が日照にある時ピッチ軸まわりの姿
勢角誤差全太陽センサで検出し、ロール軸およびヨー軸
まわりの姿勢角誤差を恒星センサで検出し三軸姿勢制御
を行うようにしたもので、以下図面に従ってこの発明の
特徴とする姿勢制御方式會説明する。When the satellite is in sunlight on My geosynchronous orbit, the attitude angle error around the pitch axis is detected by the all-sun sensor, and the attitude angle error around the roll and yaw axes is detected by the fixed star sensor to perform three-axis attitude control. The attitude control system, which is a feature of the present invention, will be explained below with reference to the drawings.
第1図はこの発明の一実施例を示すもので1図において
(11はロール軸、(21はピッチ軸、(3jはヨー軸
・(4)は恒星センサ、(51〜(8+は太陽センサ、
(9)は地球センサ、Uαはロールホイール、 uiI
はピッチホイール、 (121はヨーホイール、 (1
31は演算器を含むデータ処理器である。第2図は第1
図に示した構成要素間の信号の流れを示すものである。Fig. 1 shows an embodiment of the present invention. ,
(9) is the earth sensor, Uα is the roll wheel, uiI
is the pitch wheel, (121 is the yaw wheel, (1
31 is a data processor including an arithmetic unit. Figure 2 is the first
It shows the flow of signals between the components shown in the figure.
三軸姿勢制御#星の姿勢側[lI41の目的はヨー軸+
31會地球中心に指間させ、ピッチ@(21を軌迫面に
垂直にさせることである。従って今、恒星センサ(4)
の中心方向がピッチ軸(2)の反対方向を向き北直星を
観測している場合、恒星センサ(41の2次元画面iC
吠った北憔星の像の中心からのずれのうちロール軸方向
のずれはヨー媚まわりの姿勢角誤差となり、ヨー軸方向
のずれはロール@1まわpの姿勢角誤差となる。4個の
太陽センサ(51〜(81はその視野金すべて合わせる
と衛星のピッチ軸“よりりをすべておおい衛星が日照で
ある限り太陽センサ(51〜(81のいずれかが太陽方
向を測定する。ぞしてデータ処理器(131によってつ
ねに軌迫上の衛星の位置と太陽の位置全演算器を用いて
計算するようにしておけばピッチ軸まわりの姿勢角誤差
が無い場合の太陽センサ(51〜(81の61す定する
太陽方向全計算で求めることが出来る。よって実際に測
定した太陽方向と演算器の中で計算されたピッチ軸まわ
りの姿勢角−差が無い場合の太陽方向との差がピッチ軸
まわりの姿勢角誤差となる。衛星が日1裟にある礪含は
地球センサのピッチ軸まわりの姿勢角誤差をそのまま用
いる。Three-axis attitude control # Star attitude side [lI41 purpose is yaw axis +
31 point to the center of the earth and make the pitch @ (21 perpendicular to the orbital plane. Therefore, now the star sensor (4)
When the center direction of the star sensor (41's two-dimensional screen iC
Among the deviations from the center of the image of the roaring North Star, the deviation in the roll axis direction becomes an attitude angle error around the yaw axis, and the deviation in the yaw axis direction becomes an attitude angle error in the roll @1 turn p. The four solar sensors (51-(81) together cover the pitch axis of the satellite, and as long as the satellite is exposed to sunlight, any one of the solar sensors (51-(81) measures the direction of the sun. If the data processor (131) always calculates the position of the satellite on orbit and the position of the sun using all the calculators, the sun sensor (51 to (It can be determined by the total sun direction calculation set in 81-61. Therefore, the difference between the actually measured sun direction and the attitude angle around the pitch axis calculated in the calculator - the sun direction when there is no difference. is the attitude angle error around the pitch axis.The attitude angle error around the pitch axis of the earth sensor is used as it is to determine the position of the satellite during the day.
以上のようにして、恒星センサ(4)、太陽センサ(り
1〜(8)、地球センナ(9)を用いてロール軸、ピッ
チ軸及びヨー軸まわりの姿勢角誤差をデータ処理器uJ
O中で計峰して求めることが出来1便ってこの姿勢角誤
差を除去するようにロールホイールl+u 。As described above, the attitude angle errors around the roll axis, pitch axis, and yaw axis are measured by the data processor uJ using the star sensor (4), the sun sensor (ri1 to (8)), and the earth sensor (9).
The roll wheel l+u can be calculated by measuring the angle in the air and removing this attitude angle error.
ピッチホイール(IIL ヨーホイールOzヲ駆動する
信号音データ処理器+13の中で計算出来る。このよう
に計算で求められた駆動信号でホイールを回転しトルク
を発生させることにより三軸姿勢制御が可能になる。The pitch wheel (IIL) can be calculated in the signal sound data processor +13 that drives the yaw wheel.By rotating the wheel and generating torque using the drive signal calculated in this way, three-axis attitude control is possible. Become.
以上述べたようにこの発明によれば、恒星センサ(4)
と太陽センサ(51〜(81と演算器を含むデータ処理
器+131 ’に用いることにより、衛星が日照の場合
三軸まわりの姿勢角誤差を検出するCとが口」籠でめり
、地球センサ(9)に比べて狙星センサ(4)、太陽セ
ンナ(51〜(81の姿勢角誤差検出相反が良いため、
従来の地球上ンサ全用いた三軸姿勢制御衛星より尚い姿
勢制−精反を得ることが可能になる。As described above, according to the present invention, the stellar sensor (4)
and a solar sensor (51 to 81 and a data processor including an arithmetic unit + 131') to detect attitude angle errors around the three axes when the satellite is in sunlight. Compared to (9), the target sensor (4) and the sun sensor (51 to (81) have better attitude angle error detection compatibility, so
It is possible to obtain even more attitude control than the conventional three-axis attitude control satellite that uses all terrestrial sensors.
なお実施例において、ホイール構成は直交する3個のホ
イールからなるが、4個以上のホイールからなる構成お
よび複数ホイールのうち1個がバイアス角運動量をもつ
ホイール構成の場合も同(求に優勢制御ができるもので
ある。In the example, the wheel configuration consists of three orthogonal wheels, but the same applies to configurations consisting of four or more wheels and wheel configurations in which one of the wheels has bias angular momentum (especially when the dominant control is used). It is something that can be done.
第1図はこの発明による静止軌道人工密層の蟻努、vj
IJ御方式を説明するために土けた三軸咬勢、’bl+
御衛星金示す図、第2図は第1図にボーC構成機器間の
接続および信号の流れを説明するための図でりり、(1
1はロールta、 (2+はピッチ軸、(31はヨー軸
。
(4)は恒星センサ、(5)から(81は太陽センサ、
(9)¥i地球センサ、 QUIはロールホイール、
tillはビフチj;イール、 U21はヨーホイール
、(lj中は演#、器會言むデータ処理器である。
なお図中同一あるいは相当部分には同−符g−5z付し
て示してめる。
代理人 葛 野 信 −Figure 1 shows the artificial dense layer of geostationary orbit according to the present invention, vj
In order to explain the IJ method, I used three-axis bite, 'bl+
Figure 2 is a diagram for explaining the connections and signal flow between the components of the Baud C in Figure 1.
1 is the roll ta, (2+ is the pitch axis, (31 is the yaw axis. (4) is the star sensor, (5) to (81 is the sun sensor,
(9) ¥i earth sensor, QUI is a roll wheel,
till is bifuchi j; eel, U21 is yaw wheel, Agent: Shin Kuzuno −
Claims (1)
角誤差を検出する恒星センサと、太陽を観測してピッチ
軸まわりの姿勢角誤差を検出する太陽センサと、地球全
観測してピッチ軸まわりの姿勢角誤差を検出する地球セ
ンサと、ロール軸、ピッチ軸およびヨー軸のまわりに回
転トルク奮発生するモーメンタムホイールとを用いて三
晩姿勢制−を行う静止軌道人工衛星の姿勢制御方式にお
いて。 上記恒星センサのロール軸およびヨー軸まわりの姿勢角
誤差検出信号と、上記太陽センサのピッチ軸まわ9の姿
勢角誤差検出信号と2人工#星が6隙にある場合上記地
球センサのピッチ軸まわりの姿勢角誤差検出信号とをデ
ータ処理器に入力し。 データ処理器の出力に従い上記モーメンタムホイール全
躯動して人工衛星のロール軸、ピッチ軸およびヨー軸ま
わりの姿勢誤差を除去できるようにしたことを特徴とす
る静止軌道人工衛星の姿勢制御方式。[Scope of Claims] A stellar sensor that observes a star 'fc and detects an attitude angle error around the roll axis and yaw axis υ; a sun sensor that observes the sun and detects an attitude angle error around the pitch axis; A geostationary orbit that performs three-night attitude control using an earth sensor that observes the entire earth and detects attitude angle errors around the pitch axis, and a momentum wheel that generates rotational torque around the roll, pitch, and yaw axes. In the attitude control system of artificial satellites. Attitude angle error detection signal around the roll axis and yaw axis of the above-mentioned star sensor, attitude angle error detection signal around the pitch axis 9 of the above-mentioned sun sensor, and 2 When the artificial # star is in the 6th gap, around the pitch axis of the above-mentioned earth sensor. and the attitude angle error detection signal are input to the data processor. An attitude control system for a geostationary orbit artificial satellite, characterized in that the entire momentum wheel moves according to the output of a data processor to remove attitude errors around the roll axis, pitch axis, and yaw axis of the artificial satellite.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP57142423A JPS5932599A (en) | 1982-08-17 | 1982-08-17 | Control system of attitude of stationary orbit artificial satellite |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP57142423A JPS5932599A (en) | 1982-08-17 | 1982-08-17 | Control system of attitude of stationary orbit artificial satellite |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS5932599A true JPS5932599A (en) | 1984-02-22 |
Family
ID=15314978
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP57142423A Pending JPS5932599A (en) | 1982-08-17 | 1982-08-17 | Control system of attitude of stationary orbit artificial satellite |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS5932599A (en) |
-
1982
- 1982-08-17 JP JP57142423A patent/JPS5932599A/en active Pending
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