JPH0699899A - Attitude control device for spacecraft - Google Patents
Attitude control device for spacecraftInfo
- Publication number
- JPH0699899A JPH0699899A JP4276671A JP27667192A JPH0699899A JP H0699899 A JPH0699899 A JP H0699899A JP 4276671 A JP4276671 A JP 4276671A JP 27667192 A JP27667192 A JP 27667192A JP H0699899 A JPH0699899 A JP H0699899A
- Authority
- JP
- Japan
- Prior art keywords
- turbine
- gas
- spacecraft
- attitude control
- aerodynamic
- 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
- 239000002828 fuel tank Substances 0.000 claims abstract description 5
- 239000007788 liquid Substances 0.000 claims abstract description 5
- 239000000446 fuel Substances 0.000 claims abstract description 4
- 239000005437 stratosphere Substances 0.000 abstract description 11
- 239000003921 oil Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 239000010720 hydraulic oil Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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、大気圏内から成層圏、
或いはそれ以上の宇宙空間まで飛行して大気圏に再突入
する宇宙往還機や飛翔体等の宇宙機の姿勢制御装置に関
するものである。[Industrial field of application] The present invention relates to the atmosphere, the stratosphere,
Alternatively, the present invention relates to an attitude control device for a spacecraft such as a space shuttle and a flying vehicle that re-enters the atmosphere by flying to a larger space.
【０００２】[0002]
【従来の技術】例えば、スペースシャトルに代表される
宇宙往還機等では、大気圏から成層圏を経て宇宙空間に
到達し、該宇宙空間にて所定の作業を終えた後に大気圏
に再突入することになるが、斯かる再突入において成層
圏以下の空力域まで降下すると、補助動力装置（ＡＰ
Ｕ）によりフラップやラダー等の空力制御翼を油圧駆動
して姿勢制御を行いつつ滑空して地上に帰還するように
している。2. Description of the Related Art For example, in a space shuttle represented by a space shuttle, it reaches the outer space from the atmosphere through the stratosphere, and after completing a predetermined work in the outer space, reenters the atmosphere. However, when it descends to the aerodynamic range below the stratosphere during such re-entry, the auxiliary power unit (AP
By U), aerodynamic control blades such as flaps and rudders are hydraulically driven to control the attitude and glide to return to the ground.
【０００３】図２は上記補助動力装置の一例を示すもの
で、燃料タンク１からのヒドラジン等の液体燃料２をガ
ス発生器３で化学分解させることにより高圧の作動ガス
４とし、該作動ガス４を用いてタービン５を駆動するこ
とによりギアボックス６を介して油圧ポンプ７を駆動
し、該油圧ポンプ７により油タンク８から供給される圧
油９でフラップやラダー等の空力制御翼１０が駆動され
るようになっており、前記タービン５を駆動した作動ガ
ス４は排気ダクト１１を介して機体外へ投棄されるよう
になっている。FIG. 2 shows an example of the above-mentioned auxiliary power unit. A liquid fuel 2 such as hydrazine from a fuel tank 1 is chemically decomposed by a gas generator 3 into a high-pressure working gas 4, and the working gas 4 The hydraulic pump 7 is driven via the gearbox 6 by driving the turbine 5 using the hydraulic pump 7. The hydraulic pump 7 drives the aerodynamic control blades 10 such as flaps and ladders with the pressure oil 9 supplied from the oil tank 8. The working gas 4 that has driven the turbine 5 is dumped to the outside of the machine body through the exhaust duct 11.
【０００４】[0004]
【発明が解決しようとする課題】しかしながら、上記し
た如き補助動力装置により空力制御翼１０を駆動して姿
勢制御を行う方式では、再突入初期における空気の薄い
成層圏での姿勢制御能力が殆ど無い、即ち空気の薄い成
層圏ではフラップやラダー等の空力制御翼１０が有効に
作用しないという不具合があった。However, in the method of controlling the attitude by driving the aerodynamic control blade 10 by the auxiliary power unit as described above, there is almost no attitude control ability in the stratosphere where the air is thin at the initial stage of reentry. That is, in the stratosphere where air is thin, there is a problem that the aerodynamic control blade 10 such as a flap or a ladder does not work effectively.
【０００５】本発明は上述の実情に鑑みてなしたもの
で、再突入初期における空気の薄い成層圏でも有効に宇
宙機の姿勢を制御し得る装置を提供することを目的とし
ている。The present invention has been made in view of the above situation, and an object of the present invention is to provide a device capable of effectively controlling the attitude of a spacecraft even in the stratosphere where the air is thin at the initial stage of reentry.
【０００６】[0006]
【課題を解決するための手段】本発明は、燃料タンクの
液体燃料をガス発生器により高圧の作動ガスとしてター
ビンを駆動し、該タービンにより油圧ポンプを駆動して
空力制御翼を油圧で駆動し、該空力制御翼により空力域
での姿勢制御を行い得るよう構成した宇宙機の姿勢制御
装置であって、宇宙機機体の所要位置に個別に開閉可能
な複数のガスジェットスラスタを配設し、該ガスジェッ
トスラスタに前記タービンから排気される作動ガスを導
く排気流路を接続し、前記ガス発生器から作動ガスをタ
ービンに導く給気流路と前記排気流路とをバイパス流路
により接続し、該バイパス流路と前記給気流路との分岐
部に切換弁を配設したことを特徴とするものである。According to the present invention, a liquid generator in a fuel tank is used as a high-pressure working gas by a gas generator to drive a turbine, and a hydraulic pump is driven by the turbine to hydraulically drive an aerodynamic control blade. , A spacecraft attitude control device configured to perform attitude control in the aerodynamic region by the aerodynamic control wing, wherein a plurality of gas jet thrusters that can be individually opened and closed are arranged at required positions of the spacecraft body, An exhaust passage for guiding the working gas exhausted from the turbine to the gas jet thruster is connected, and an air supply passage for guiding the working gas from the gas generator to the turbine and the exhaust passage are connected by a bypass passage, A switching valve is arranged at a branch portion between the bypass flow path and the air supply flow path.
【０００７】[0007]
【作用】従って本発明では、再突入初期における空気の
薄い成層圏において、切換弁によりタービンに向かう作
動ガスの流れを閉止してガス発生器からの作動ガスを全
てバイパス流路に導き、姿勢制御に必要な適宜のガスジ
ェットスラスタを開けて前記作動ガスを機外に噴射する
ことにより姿勢制御を行う。Therefore, according to the present invention, in the stratosphere where the air is thin at the initial stage of re-entry, the flow of the working gas toward the turbine is closed by the switching valve to guide all the working gas from the gas generator to the bypass flow path for attitude control. Attitude control is performed by opening a required gas jet thruster and injecting the working gas to the outside of the machine.
【０００８】更に、空気密度の高い大気圏まで降下して
空力制御翼による姿勢制御が望める状態になったら、切
換弁によりバイパス流路に向かう作動ガスの流れを閉止
してガス発生器からの作動ガスを全てタービンに導き、
該タービンを駆動することにより油圧ポンプを駆動し、
該油圧ポンプにより供給される圧油で空力制御翼を駆動
して姿勢制御を行う。Further, when the atmosphere descends to a high air density and the attitude control by the aerodynamic control blade is desired, the flow of the working gas toward the bypass passage is closed by the switching valve to stop the working gas from the gas generator. To the turbine,
Driving the hydraulic pump by driving the turbine,
The attitude control is performed by driving the aerodynamic control blades with the pressure oil supplied by the hydraulic pump.
【０００９】このとき、ガスジェットスラスタには、タ
ービンから排気される作動ガスが継続して供給されるこ
とになる為、前記空力制御翼による姿勢制御に対しガス
ジェットスラスタによる姿勢制御を併用し続ければ、空
力制御翼による姿勢制御が効き始める過渡期において、
ガスジェットスラスタによる姿勢制御を補助的に作用さ
せることが可能である。At this time, since the working gas exhausted from the turbine is continuously supplied to the gas jet thruster, the attitude control by the gas jet thruster can be continuously used together with the attitude control by the aerodynamic control blade. For example, in the transitional period when the attitude control by the aerodynamic control blade begins to take effect
The attitude control by the gas jet thruster can be made to act auxiliary.
【００１０】[0010]
【実施例】以下本発明の実施例を図面を参照しつつ説明
する。Embodiments of the present invention will be described below with reference to the drawings.
【００１１】図１は本発明の一実施例を示すもので、図
２と同一の符号を付した部分は同一物を表わしている。FIG. 1 shows an embodiment of the present invention, in which the same reference numerals as those in FIG. 2 represent the same parts.
【００１２】図示するように、宇宙往還機等の宇宙機機
体１２の所要位置に個別に開閉可能な複数のガスジェッ
トスラスタ１３を配設し、該ガスジェットスラスタ１３
に調圧弁１４を介してタービン５から排気される作動ガ
ス４を導く排気流路１５を接続する。As shown in the figure, a plurality of gas jet thrusters 13 that can be individually opened and closed are arranged at required positions of a spacecraft body 12 such as a space shuttle, and the gas jet thrusters 13 are arranged.
An exhaust passage 15 for guiding the working gas 4 exhausted from the turbine 5 via the pressure regulating valve 14 is connected to the.
【００１３】ここで、前記ガスジェットスラスタ１３は
便宜上並列した状態で図示されているが、実際には宇宙
機機体１２の適当な位置に分散して配設されることは勿
論である。Here, the gas jet thrusters 13 are shown in a parallel state for the sake of convenience, but it is needless to say that the gas jet thrusters 13 are actually dispersed and arranged at appropriate positions of the spacecraft body 12.
【００１４】更に、前記ガス発生器３から作動ガス４を
タービン５に導く給気流路１６の中途部と前記排気流路
１５の中途部とを、前記タービン５を迂回するよう配設
したバイパス流路１７により接続し、該バイパス流路１
７と前記給気流路１６との分岐部には切換弁１８を配設
し、該切換弁１８によりバイパス流路１７に向かう作動
ガス４の流れを閉止してガス発生器３からの作動ガス４
を全てタービン５に導いたり、或いは逆にタービン５に
向かう作動ガス４の流れを閉止してガス発生器３からの
作動ガス４を全てバイパス流路１７に導いたりすること
ができるようにする。Further, a bypass flow in which a midway portion of the air supply passage 16 and a midway portion of the exhaust passage 15 for guiding the working gas 4 from the gas generator 3 to the turbine 5 is arranged so as to bypass the turbine 5. The bypass flow path 1 is connected by a path 17.
7 and the air supply flow path 16 are provided with a switching valve 18, and the switching valve 18 closes the flow of the working gas 4 toward the bypass flow path 17 to close the working gas 4 from the gas generator 3.
To the turbine 5, or conversely, the flow of the working gas 4 toward the turbine 5 is closed so that all the working gas 4 from the gas generator 3 can be guided to the bypass passage 17.
【００１５】而して、再突入初期における空気の薄い成
層圏においてはフラップやラダー等の空力制御翼１０が
有効に作用しないので、切換弁１８によりタービン５に
向かう作動ガス４の流れを閉止してガス発生器３からの
作動ガス４を全てバイパス流路１７に導き、該バイパス
流路１７に導いた作動ガス４を調圧弁１４を介して圧力
調整し、姿勢制御に必要な適宜のガスジェットスラスタ
１３を開けて前記作動ガス４を宇宙機機体１２外に噴射
することにより姿勢制御を行う。Since the aerodynamic control blades 10 such as flaps and ladders do not work effectively in the stratosphere where the air is thin at the initial stage of re-entry, the flow of the working gas 4 toward the turbine 5 is closed by the switching valve 18. All of the working gas 4 from the gas generator 3 is guided to the bypass flow passage 17, and the working gas 4 guided to the bypass flow passage 17 is pressure-adjusted via the pressure regulating valve 14, and an appropriate gas jet thruster necessary for attitude control is provided. Attitude control is performed by opening 13 and injecting the working gas 4 to the outside of the spacecraft body 12.
【００１６】更に、空気密度の高い大気圏まで降下して
空力制御翼１０による姿勢制御が望める状態になった
ら、切換弁１８によりバイパス流路１７に向かう作動ガ
ス４の流れを閉止してガス発生器３からの作動ガス４を
全てタービン５に導き、該タービン５を駆動することに
よりギアボックス６を介して油圧ポンプ７を駆動し、該
油圧ポンプ７により油タンク８から供給される圧油９で
空力制御翼１０を駆動して姿勢制御を行う。Further, when the attitude is lowered to the atmosphere with a high air density and the attitude control by the aerodynamic control blade 10 is desired, the flow of the working gas 4 toward the bypass passage 17 is closed by the switching valve 18 to close the gas generator. All of the working gas 4 from 3 is guided to the turbine 5, the hydraulic pump 7 is driven via the gearbox 6 by driving the turbine 5, and the hydraulic oil 7 supplied from the oil tank 8 is driven by the hydraulic pump 7. The attitude control is performed by driving the aerodynamic control blade 10.
【００１７】このとき、ガスジェットスラスタ１３に
は、タービン５から排気される作動ガス４が継続して供
給されることになる為、前記空力制御翼１０による姿勢
制御に対しガスジェットスラスタ１３による姿勢制御を
併用し続ければ、空力制御翼１０による姿勢制御が効き
始める過渡期において、ガスジェットスラスタ１３によ
る姿勢制御を補助的に作用させることが可能である。At this time, since the working gas 4 exhausted from the turbine 5 is continuously supplied to the gas jet thruster 13, the attitude of the gas jet thruster 13 is different from the attitude control of the aerodynamic control blade 10. If the control is continued to be used together, the attitude control by the gas jet thruster 13 can be made to act in an auxiliary manner during the transition period when the attitude control by the aerodynamic control blade 10 starts to work.
【００１８】尚、空力制御翼１０による姿勢制御が十分
に作用する高度まで降下して、ガスジェットスラスタ１
３による姿勢制御が特に必要なくなったときには、相反
する位置に配置されたガスジェットスラスタ１３同士を
開けて制御力を相殺させるよう作動ガス４を排出すれば
良い。It should be noted that the gas jet thruster 1 is lowered to an altitude at which the attitude control by the aerodynamic control blade 10 sufficiently operates.
When the attitude control by 3 becomes unnecessary, the working gas 4 may be discharged so as to cancel the control force by opening the gas jet thrusters 13 arranged at opposite positions.
【００１９】従って上記実施例によれば、ガスジェット
スラスタ１３による姿勢制御によって、再突入初期にお
ける空気の薄い成層圏でも有効に宇宙機の姿勢を制御す
ることができ、しかも空力制御翼１０による姿勢制御に
移行した後もガスジェットスラスタ１３による姿勢制御
を併用し続けることができるので、空力制御翼１０によ
る姿勢制御が効き始める過渡期において、ガスジェット
スラスタ１３による姿勢制御を補助的に作用させること
ができる。Therefore, according to the above embodiment, the attitude control of the gas jet thruster 13 can effectively control the attitude of the spacecraft even in the stratosphere where the air is thin at the initial stage of reentry, and the attitude control by the aerodynamic control wing 10 is also possible. Since the attitude control by the gas jet thruster 13 can be continued to be used together after the shift to, the attitude control by the gas jet thruster 13 can be supplementarily operated in the transition period when the attitude control by the aerodynamic control blade 10 starts to be effective. it can.
【００２０】尚、本発明の宇宙機の姿勢制御装置は、上
述の実施例にのみ限定されるものではなく、本発明の要
旨を逸脱しない範囲内において種々変更を加え得ること
は勿論である。The attitude control device for a spacecraft according to the present invention is not limited to the above-described embodiments, and it goes without saying that various modifications can be made without departing from the gist of the present invention.
【００２１】[0021]
【発明の効果】上記した本発明の宇宙機の姿勢制御装置
によれば、ガスジェットスラスタによる姿勢制御によっ
て、再突入初期における空気の薄い成層圏でも有効に宇
宙機の姿勢を制御することができ、しかも空力制御翼に
よる姿勢制御に移行した後もガスジェットスラスタによ
る姿勢制御を併用し続けることができるので、空力制御
翼による姿勢制御が効き始める過渡期において、ガスジ
ェットスラスタによる姿勢制御を補助的に作用させるこ
とができるという優れた効果を奏し得る。According to the attitude control device for a spacecraft of the present invention described above, the attitude control by the gas jet thruster can effectively control the attitude of the spacecraft even in the stratosphere where the air is thin in the initial stage of reentry. Moreover, since the attitude control by the gas jet thruster can be continued to be used together after the attitude control by the aerodynamic control blade, the attitude control by the gas jet thruster can be supplemented during the transition period when the attitude control by the aerodynamic control blade begins to take effect. The excellent effect of being able to act can be produced.
【図１】本発明の一実施例を示す概略図である。FIG. 1 is a schematic view showing an embodiment of the present invention.
【図２】従来例を示す概略図である。FIG. 2 is a schematic view showing a conventional example.
１ 燃料タンク ２ 液体燃料 ３ ガス発生器 ４ 作動ガス ５ タービン ７ 油圧ポンプ １０ 空力制御翼 １２ 宇宙機機体 １３ ガスジェットスラスタ １５ 排気流路 １６ 給気流路 １７ バイパス流路 １８ 切換弁 1 Fuel Tank 2 Liquid Fuel 3 Gas Generator 4 Working Gas 5 Turbine 7 Hydraulic Pump 10 Aerodynamic Control Blade 12 Spacecraft Body 13 Gas Jet Thruster 15 Exhaust Flow Path 16 Air Supply Flow Path 17 Bypass Flow Path 18 Switching Valve
Claims (1)
り高圧の作動ガスとしてタービンを駆動し、該タービン
により油圧ポンプを駆動して空力制御翼を油圧で駆動
し、該空力制御翼により空力域での姿勢制御を行い得る
よう構成した宇宙機の姿勢制御装置であって、宇宙機機
体の所要位置に個別に開閉可能な複数のガスジェットス
ラスタを配設し、該ガスジェットスラスタに前記タービ
ンから排気される作動ガスを導く排気流路を接続し、前
記ガス発生器から作動ガスをタービンに導く給気流路と
前記排気流路とをバイパス流路により接続し、該バイパ
ス流路と前記給気流路との分岐部に切換弁を配設したこ
とを特徴とする宇宙機の姿勢制御装置。1. A gas generator uses a liquid fuel in a fuel tank as a high-pressure working gas to drive a turbine, the turbine drives a hydraulic pump to hydraulically drive an aerodynamic control blade, and the aerodynamic control blade drives an aerodynamic region. In a spacecraft attitude control device configured to perform attitude control in, a plurality of individually openable and closable gas jet thrusters are arranged at required positions of the spacecraft body, and the gas jet thrusters are connected to the turbine from the turbine. An exhaust flow path for guiding the working gas to be exhausted is connected, and a supply flow path for guiding the working gas from the gas generator to the turbine and the exhaust flow path are connected by a bypass flow path, and the bypass flow path and the supply air flow. An attitude control device for a spacecraft, characterized in that a switching valve is provided at a branch portion from the road.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4276671A JPH0699899A (en) | 1992-09-21 | 1992-09-21 | Attitude control device for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4276671A JPH0699899A (en) | 1992-09-21 | 1992-09-21 | Attitude control device for spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0699899A true JPH0699899A (en) | 1994-04-12 |
Family
ID=17572698
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4276671A Pending JPH0699899A (en) | 1992-09-21 | 1992-09-21 | Attitude control device for spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0699899A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| CN113405407A (en) * | 2019-12-27 | 2021-09-17 | 北京星际荣耀空间科技股份有限公司 | Liquid rocket thrust control system and liquid rocket |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
-
1992
- 1992-09-21 JP JP4276671A patent/JPH0699899A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN113405407A (en) * | 2019-12-27 | 2021-09-17 | 北京星际荣耀空间科技股份有限公司 | Liquid rocket thrust control system and liquid rocket |
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