JPH0524595A - Aerobrake system with attitude control function - Google Patents
Aerobrake system with attitude control functionInfo
- Publication number
- JPH0524595A JPH0524595A JP3178571A JP17857191A JPH0524595A JP H0524595 A JPH0524595 A JP H0524595A JP 3178571 A JP3178571 A JP 3178571A JP 17857191 A JP17857191 A JP 17857191A JP H0524595 A JPH0524595 A JP H0524595A
- Authority
- JP
- Japan
- Prior art keywords
- attitude
- air resistance
- spacecraft
- angle
- aerobrake
- 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
Description
【０００１】[0001]
【産業上の利用分野】本発明は軌道間輸送機（ＯＴＶ）
等の宇宙機が高々度軌道から地球周回低高度軌道へ帰還
する際に、軌道遷移用の燃料を大幅に節減することを目
的として空気抵抗を発生させることにより、宇宙機を減
速させる姿勢制御機能つきエアロブレーキシステムに関
する。BACKGROUND OF THE INVENTION The present invention relates to an inter-orbit transport aircraft (OTV).
Attitude control function that slows down the spacecraft by generating air resistance for the purpose of significantly reducing the fuel for orbit transition when the spacecraft such as returns from the high altitude orbit to the low earth orbit Aero brake system.
【０００２】[0002]
【従来の技術】従来、この種のエアロブレーキシステム
は、固定の空気抵抗板又は風船型のバリュートを用いた
ものが考えられていた。2. Description of the Related Art Conventionally, an aero brake system of this type has been considered to use a fixed air resistance plate or a balloon type value.
【０００３】[0003]
【発明が解決しようとする課題】上述した従来のエアロ
ブレーキは、固定の空気抵抗板又は風船型のバリュート
を用いたものであるため、空力中心と機軸がずれている
と姿勢誤差が生じ、これによりエアロブレーキが受ける
空気抵抗力がずれてしまうと云う欠点がある。又、固定
であることから宇宙機の姿勢が常に進行方向に対して一
定の角度になってしまうため、宇宙機の運用に対して制
約を課すことになると云う欠点がある。又、姿勢制御を
ガスジェットにより行う場合には、多量の推薬を必要と
すると云う欠点もある。Since the above-mentioned conventional aero brake uses a fixed air resistance plate or a balloon type value, if the aerodynamic center and the machine axis are deviated, an attitude error occurs. Due to this, there is a drawback that the air resistance force received by the aerobrake is displaced. Further, since it is fixed, the attitude of the spacecraft is always at a constant angle with respect to the traveling direction, which imposes restrictions on the operation of the spacecraft. Further, when the attitude control is performed by a gas jet, there is a drawback that a large amount of propellant is required.
【０００４】[0004]
【課題を解決するための手段】本発明の姿勢制御機能つ
きエアロブレーキシステムは、軌道間輸送機（ＯＴＶ）
等の宇宙機が低高度地球周回軌道に帰還する際に軌道遷
移用燃料の消費を大幅に節約することを目的として使用
されるエアロブレーキにおいて、前記宇宙機の姿勢誤差
角を検出する姿勢センサと、４象限に分割して設けられ
空気抵抗を受ける各象限の面積が可変自在である空気抵
抗板と、前記姿勢センサの検出結果に基づき前記空気抵
抗板を駆動制御するアクチュエータ及び制御エレクトロ
ニクスとを備えている。The aerobrake system with attitude control function of the present invention is an inter-orbit vehicle (OTV).
In the aero brake used for the purpose of significantly saving the consumption of fuel for orbit transition when the spacecraft such as returns to the low earth orbit, the attitude sensor that detects the attitude error angle of the spacecraft An air resistance plate, which is divided into four quadrants and in which the area of each quadrant that receives air resistance is variable, and an actuator and control electronics that drive-control the air resistance plate based on the detection result of the attitude sensor. ing.
【０００５】[0005]
【実施例】次に、本発明について図面を参照して説明す
る。DESCRIPTION OF THE PREFERRED EMBODIMENTS Next, the present invention will be described with reference to the drawings.
【０００６】図１（ａ）及び（ｂ）は本発明の一実施例
の正面図及び側面図である。FIGS. 1A and 1B are a front view and a side view of an embodiment of the present invention.
【０００７】本実施例は宇宙機１の姿勢誤差角を検出す
る姿勢センサ４と、４象限に分割して設けられ空気抵抗
を受ける各象限の面積が可変自在である空気抵抗板２
と、この空気抵抗板２の開き角を駆動制御するＸ軸まわ
りのアクチュエータ６，７及びＹ軸まわりのアクチュエ
ータ８，９と、制御エレクトロニクス５とを有してな
る。In this embodiment, an attitude sensor 4 for detecting an attitude error angle of a spacecraft 1 and an air resistance plate 2 which is divided into four quadrants and in which each quadrant receiving an air resistance has a variable area.
The actuators 6 and 7 around the X axis and the actuators 8 and 9 around the Y axis for driving and controlling the opening angle of the air resistance plate 2, and the control electronics 5.
【０００８】このような本実施例において、姿勢センサ
４は宇宙機１のＸ軸及び（又は）Ｙ軸の姿勢角を検出
し、これを制御エレクトロニクス５へ出力する。制御エ
レクトロニクス５では入力された姿勢角より目標姿勢角
からの誤差角を生成し、これに比例してＸ軸まわりに正
の誤差角があればアクチュエータ（−Ｘ）６を増加さ
せ、アクチュエータ（＋Ｘ）７を減少させ、また負の誤
差角があればアクチュエータ（−Ｘ）６を減少させ、ア
クチュエータ（＋Ｘ）７を増加させる。同様にＹ軸まわ
りに正の誤差角があればアクチュエータ（−Ｙ）９を増
加させ、アクチュエータ（＋Ｙ）８を減少させ、また負
の誤差角があればアクチュエータ（−Ｙ）９を減少さ
せ、アクチュエータ（＋Ｙ）８を増加させる。このよう
な制御によって、空気抵抗板の各象限の開き角を可変し
てノミナル状態３から姿勢制御状態２へ制御することに
より、空力抵抗によるＸ軸及び（又は）Ｙ軸まわりの制
御トルクを生成し、宇宙機１の姿勢が目標姿勢と一致す
るように制御する。これによって正確な空気抵抗力を得
ることができる。In this embodiment, the attitude sensor 4 detects the attitude angle of the X-axis and / or the Y-axis of the spacecraft 1 and outputs it to the control electronics 5. The control electronics 5 generates an error angle from the target attitude angle from the input attitude angle, and if there is a positive error angle around the X axis in proportion to this, increases the actuator (-X) 6 to increase the actuator (+ X ) 7, and if there is a negative error angle, actuator (-X) 6 is decreased and actuator (+ X) 7 is increased. Similarly, if there is a positive error angle around the Y-axis, the actuator (−Y) 9 is increased and the actuator (+ Y) 8 is decreased, and if there is a negative error angle, the actuator (−Y) 9 is decreased, The actuator (+ Y) 8 is increased. By such control, the opening angle of each quadrant of the air resistance plate is changed to control from the nominal state 3 to the attitude control state 2, thereby generating a control torque about the X axis and / or the Y axis by aerodynamic resistance. Then, the attitude of the spacecraft 1 is controlled so as to match the desired attitude. This makes it possible to obtain accurate air resistance.
【０００９】[0009]
【発明の効果】以上説明したように本発明は、宇宙機の
姿勢誤差角に応じて４象限に分割された空気抵抗板の各
象限の面積を制御することにより、宇宙機の姿勢を目標
に一致させるので正確な空気抵抗力を得ることができる
とともに、これをガスジェットにより行った場合に必要
になると考られる多量の推薬を節約でき、またエアロブ
レーキング中の宇宙機の姿勢を所望の方向に制御するこ
とができるため、運用に対する制約を大幅に緩和するこ
とができると云う効果がある。As described above, the present invention aims at the attitude of the spacecraft by controlling the area of each quadrant of the air resistance plate divided into four quadrants according to the attitude error angle of the spacecraft. Since they match, it is possible to obtain accurate air resistance, save a large amount of propellant that would be necessary if this was done with a gas jet, and to adjust the attitude of the spacecraft during aerobraking to the desired level. Since it can be controlled in the direction, there is an effect that restrictions on operation can be significantly relaxed.
【図１】本発明の一実施例を示し、同図（ａ）は正面
図、同図（ｂ）は側面図である。FIG. 1 shows an embodiment of the present invention, in which FIG. 1 (a) is a front view and FIG. 1 (b) is a side view.
１ 宇宙機 ２ 姿勢制御状態の空気抵抗板 ３ ノミナル状態の空気抵抗板 ４ 姿勢センサ ５ 制御エレクトロニクス ６ アクチュエータ（−Ｘ） ７ アクチュエータ（＋Ｘ） ８ アクチュエータ（＋Ｙ） ９ アクチュエータ（−Ｙ） 1 Spacecraft 2 Air resistance plate in attitude control 3 Nominal air resistance plate 4 Attitude sensor 5 Control electronics 6 Actuator (-X) 7 Actuator (+ X) 8 actuators (+ Y) 9 Actuator (-Y)
Claims (2)
高度地球周回軌道に帰還する際に軌道遷移用燃料の消費
を大幅に節約することを目的として使用されるエアロブ
レーキにおいて、前記宇宙機の姿勢誤差角を検出する姿
勢センサと、４象限に分割して設けられ空気抵抗を受け
る各象限の面積が可変自在である空気抵抗板と、前記姿
勢センサの検出結果に基づき前記空気抵抗板を駆動制御
するアクチュエータ及び制御エレクトロニクスとを備え
ることを特徴とする姿勢制御機能つきエアロブレーキシ
ステム。1. An aerobrake used for the purpose of significantly saving the consumption of fuel for orbit transition when a spacecraft such as an inter-orbital vehicle (OTV) returns to a low earth orbit. An attitude sensor that detects the attitude error angle of the spacecraft, an air resistance plate that is divided into four quadrants, and the area of each quadrant that receives air resistance is variable, and the air resistance based on the detection result of the attitude sensor. An aerobrake system with a posture control function, comprising an actuator for driving and controlling a plate and control electronics.
より開き角が駆動制御されることを特徴とする請求項１
記載の姿勢制御機能つきエアロブレーキシステム。2. The opening angle of the air resistance plate is drive-controlled by the actuator.
Aerobrake system with described attitude control function.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3178571A JPH0524595A (en) | 1991-07-19 | 1991-07-19 | Aerobrake system with attitude control function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3178571A JPH0524595A (en) | 1991-07-19 | 1991-07-19 | Aerobrake system with attitude control function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0524595A true JPH0524595A (en) | 1993-02-02 |
Family
ID=16050811
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3178571A Pending JPH0524595A (en) | 1991-07-19 | 1991-07-19 | Aerobrake system with attitude control function |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0524595A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2573695C1 (en) * | 2014-09-16 | 2016-01-27 | Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт машиностроения" (ФГУП ЦНИИмаш) | Control over spacecraft at its ascent to earth artificial satellite orbit |
-
1991
- 1991-07-19 JP JP3178571A patent/JPH0524595A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2573695C1 (en) * | 2014-09-16 | 2016-01-27 | Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт машиностроения" (ФГУП ЦНИИмаш) | Control over spacecraft at its ascent to earth artificial satellite orbit |
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