JPS58183396A - Magnetic attitude control system of artificial satellite - Google Patents
Magnetic attitude control system of artificial satelliteInfo
- Publication number
- JPS58183396A JPS58183396A JP58056777A JP5677783A JPS58183396A JP S58183396 A JPS58183396 A JP S58183396A JP 58056777 A JP58056777 A JP 58056777A JP 5677783 A JP5677783 A JP 5677783A JP S58183396 A JPS58183396 A JP S58183396A
- Authority
- JP
- Japan
- Prior art keywords
- magnetic
- satellite
- magnetic moment
- earth
- attitude 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
- 238000000034 method Methods 0.000 claims description 9
- 238000009499 grossing Methods 0.000 claims description 8
- 230000003993 interaction Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 description 1
- 230000007274 generation of a signal involved in cell-cell signaling Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
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、人工衛星に磁気モーメント発生装置を塔載
し、地球磁場との相互作用により発生ずるトルクを用い
て人工衛星の姿勢制御を行う、磁気姿勢制御方式に関す
るものである。[Detailed Description of the Invention] This invention relates to a magnetic attitude control method in which a magnetic moment generator is mounted on an artificial satellite and the attitude of the artificial satellite is controlled using the torque generated by interaction with the earth's magnetic field. It is.
人工衛星に塔載された磁気モーメント発生装曹の発生す
る磁気モーメントを１とし、地球磁場をトとすると人工
衛星に作用するトルク下は、Ｔ＝Ｅ１ＸＩＢ ・・
・・・・・ （１）で表わせる そこで磁気モーメント
１に適桶な制御論理を用いて制御を行えば、人工衛星の
姿勢制御がｏＪ能である。If the magnetic moment generated by the magnetic moment generator mounted on the satellite is 1, and the earth's magnetic field is T, then the torque acting on the satellite is T = E1XIB...
... Expressed as (1) Then, if control is performed using an appropriate control logic for the magnetic moment 1, the attitude control of the artificial satellite will be OJ-effective.
ところで従来において、人工衛星に地球磁場を測定する
ための磁気センサを塔載し地球磁場の大きさと方向を知
って姿勢制御信号に対する発生磁気モーメントを連続的
に制御する方法が検討されていたが、この方法には磁気
センサを使用するため装置全体が複雑となる欠点がある
。By the way, in the past, a method was considered in which a magnetic sensor for measuring the earth's magnetic field was mounted on an artificial satellite to learn the magnitude and direction of the earth's magnetic field and continuously control the generated magnetic moment in response to attitude control signals. This method has the disadvantage that the entire device is complicated because it uses a magnetic sensor.
そこで前記従来の問題点を改善するために、人工衛星の
軌道上での地球磁場の推定を行い、その極性の情報だけ
を使用した制御方式が提案□されていた。しかしながら
この方法にも問題があった。すなわちこの方法では発生
磁気モーメントが矩形波あるいは階段波状に変化するた
め磁気モーメントの切替時に急激なトルク変化が人工衛
星に加わり衛星擾乱を引きおこすおそれがあった。Therefore, in order to improve the above-mentioned conventional problems, a control method has been proposed that estimates the earth's magnetic field on the orbit of an artificial satellite and uses only the information on its polarity. However, this method also had problems. In other words, in this method, the generated magnetic moment changes in a rectangular wave or step wave pattern, so when the magnetic moment is switched, a sudden torque change is applied to the satellite, which may cause satellite disturbance.
そこでこの発明においては簡単な方法で磁気モーメント
切替時のトルクの急変を防ぎ衛星擾乱をおさえるように
した磁気姿勢制御方式を提供するものである。Therefore, the present invention provides a magnetic attitude control system that uses a simple method to prevent sudden changes in torque during magnetic moment switching and to suppress satellite disturbance.
以下第１図に示すこの発明の一実施例について説明する
。An embodiment of the present invention shown in FIG. 1 will be described below.
第１図において、姿勢誤差信号等の磁気モーメント制御
信号（１）は、地球磁場の極性信号を発生するタイマ（
２）からの信号により切替回路（３）において極性信号
を付加され、−次遅れの系よりなる平滑回路（４）を通
じて磁気コイル（５）に加わり磁気モーメントを発生す
る。ここで＠１図の実施例を使用して、上記磁気コイル
（５）を人工衛星′ のロール軸すなわち飛しよ
う方向に塔載し、ピッチ軸すなわち軌道面垂直軸まわり
の姿勢制御を行う場合について説明する。第２図は各部
のる磁気モーメントと作用してピッチ軸回りにトルクを
発生するヨー軸すなわち地球方向の地球磁場が（イ）に
示す様に変化するとすれば、タイマ（２）Ｋより発生さ
れる極性信号は例えば（ロ）の様になる。ここで平滑回
路（４）を使用しないとすれば（ロ）と同様の波形の磁
気モーメントを発生するが、第１図のように平滑回路（
４）を用いる率により０・）で示す一次遅れの波形の磁
気モーメントが上記磁気コイル（５）により発生する。In Figure 1, a magnetic moment control signal (1) such as an attitude error signal is generated by a timer (1) that generates a polarity signal of the earth's magnetic field.
2), a polarity signal is added in the switching circuit (3), and is applied to the magnetic coil (5) through the smoothing circuit (4) consisting of a -order lag system to generate a magnetic moment. Here, using the embodiment shown in Figure @1, let us consider the case where the magnetic coil (5) is mounted on the satellite's roll axis, that is, in the flight direction, and the attitude is controlled around the pitch axis, that is, the axis perpendicular to the orbital surface. explain. Figure 2 shows that if the yaw axis, that is, the earth's magnetic field in the earth's direction, which interacts with the magnetic moment of each part to generate torque around the pitch axis, changes as shown in (a), the timer (2) K generates torque. For example, the polarity signal is as shown in (b). If the smoothing circuit (4) is not used here, a magnetic moment with a waveform similar to (b) will be generated, but as shown in Figure 1, the smoothing circuit (
4), the magnetic coil (5) generates a magnetic moment with a first-order lag waveform indicated by 0.).
したがって第２図Ｋ（イ）で示す地球磁場との相互作用
により人工衛星に作用するトルクＦｉ（ニ）の様に平滑
化され衛星の擾乱を防ぐ亭ができる。Therefore, due to the interaction with the earth's magnetic field shown in FIG. 2 K (a), the torque acting on the artificial satellite is smoothed as shown in Fig. 2 (d), thereby creating a bow that prevents the satellite from being disturbed.
なお、以上の説明においては人工衛星のピッチ軸磁気姿
勢制御について記述したが、この発明はピッチ軸の磁気
姿勢制御たけに限定されるものではなく、ロール軸およ
びヨ 軸の磁気姿勢制御に適用しても同様の効果が得ら
れる。Although the above explanation describes the pitch-axis magnetic attitude control of an artificial satellite, the present invention is not limited to pitch-axis magnetic attitude control, but can also be applied to roll-axis and yaw-axis magnetic attitude control. The same effect can be obtained.
また、第１図の平滑回路（４）についても、−次遅れの
系を使用した場合を不したが、平滑回路に多次の遅れ系
あるいは積分器等を使用してもよい。Further, although the smoothing circuit (4) in FIG. 1 uses a -order lag system, a multi-order lag system, an integrator, or the like may be used in the smoothing circuit.
以上のようにこの発明に係る人工衛星の磁気姿勢制御方
式によれば、きわめて簡単な構成で衛星擾乱の少ない磁
気姿勢制御方式を実現できるものである。As described above, according to the magnetic attitude control system for an artificial satellite according to the present invention, it is possible to realize a magnetic attitude control system that causes little satellite disturbance with an extremely simple configuration.
ント制御信号、（２）は極性信号発生回路、（３） Ｖ
ｉ極性切替回路、（４）は平滑回路、（５１Ｖｉ磁気コ
イル、（イ）Ｆｉ地球磁場パターン、（ロ）は地球磁場
極性信号、（ハ）は発生磁気モーメント、（ニ）Ｖｉ発
生トルクである。
代理人 葛 野 信 −
第 １１(2) is the polarity signal generation circuit, (3) V
i polarity switching circuit, (4) smoothing circuit, (51Vi magnetic coil, (a) Fi earth's magnetic field pattern, (b) earth's magnetic field polarity signal, (c) generated magnetic moment, (d) Vi generated torque . Agent Shin Kuzuno - 11th
Claims (1)
との相互作用によって人工衛星の姿勢を制御する方式に
おいて、姿勢誤差、信号等の磁気モーメント制御信号を
入力とし、かつ地球磁場の極性信号を発生するタイマか
らの信号によって極性信号を付加する切替回路と、上記
切替回路の出力を人力とする遅れ要素あるいｆ′ｉ積分
ｇ素からなる平滑回路と、上記平滑回路につながる磁気
モーメント発生手段を備え、上記構成要素の作用によっ
て発生トルクを平滑し磁気モーメント切換時の人工衛星
の擾乱を防ぐようにしたことを％微とする人工衛星の磁
気姿勢制御方式。In a method in which a magnetic moment generator is mounted on a satellite and the attitude of the satellite is controlled by interaction with the earth's magnetic field, magnetic moment control signals such as attitude errors and signals are input, and the polarity signal of the earth's magnetic field is input. A switching circuit that adds a polarity signal according to a signal from a generated timer, a smoothing circuit consisting of a delay element or an f'i integral g element using the output of the switching circuit as a human power, and a magnetic moment generating means connected to the smoothing circuit. A magnetic attitude control method for an artificial satellite, which is equipped with the above components and smoothes the generated torque to prevent disturbance of the satellite during magnetic moment switching.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19823214383 DE3214383A1 (en) | 1982-04-20 | 1982-04-20 | DEVICE FOR MAGNETIC POSITIONING OF A SATELLITE |
| DE32143834 | 1982-04-20 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS58183396A true JPS58183396A (en) | 1983-10-26 |
Family
ID=6161265
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP58056777A Pending JPS58183396A (en) | 1982-04-20 | 1983-03-31 | Magnetic attitude control system of artificial satellite |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JPS58183396A (en) |
| DE (1) | DE3214383A1 (en) |
| FR (1) | FR2525361A1 (en) |
| GB (1) | GB2121564A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IL202175A0 (en) | 2009-11-17 | 2010-06-16 | Anatoly Greiser Dr | Method of overcoming gravity and a flight vehicle for the implementation thereof |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS537720B1 (en) * | 1970-07-29 | 1978-03-20 | ||
| US3834653A (en) * | 1972-03-27 | 1974-09-10 | Rca Corp | Closed loop roll and yaw control for satellites |
| DE3128054C2 (en) * | 1981-07-16 | 1983-05-26 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | "Device for the roll / yaw control of a satellite" |
-
1982
- 1982-04-20 DE DE19823214383 patent/DE3214383A1/en not_active Ceased
-
1983
- 1983-03-31 JP JP58056777A patent/JPS58183396A/en active Pending
- 1983-04-15 GB GB08310294A patent/GB2121564A/en not_active Withdrawn
- 1983-04-20 FR FR8306425A patent/FR2525361A1/en not_active Withdrawn
Also Published As
| Publication number | Publication date |
|---|---|
| FR2525361A1 (en) | 1983-10-21 |
| DE3214383A1 (en) | 1983-10-27 |
| GB8310294D0 (en) | 1983-05-18 |
| GB2121564A (en) | 1983-12-21 |
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