JPH116473A - Dc arc thrustor - Google Patents
Dc arc thrustorInfo
- Publication number
- JPH116473A JPH116473A JP9158523A JP15852397A JPH116473A JP H116473 A JPH116473 A JP H116473A JP 9158523 A JP9158523 A JP 9158523A JP 15852397 A JP15852397 A JP 15852397A JP H116473 A JPH116473 A JP H116473A
- Authority
- JP
- Japan
- Prior art keywords
- propellant
- flow rate
- pressure
- regulating valve
- arc
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0012—Means for supplying the propellant
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
Description
【0001】[0001]
【発明の属する技術分野】本発明は、直流アークスラス
タに関するものであり、より詳しくは、推進剤の供給圧
力の変動に拘らず十分な性能を発揮させ得るようにした
直流アークスラスタに関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a direct current arc thruster, and more particularly, to a direct current arc thruster capable of exhibiting sufficient performance irrespective of fluctuations in the supply pressure of a propellant. .
【0002】[0002]
【従来の技術】人工衛星などの軌道制御や姿勢制御を行
わせるために、直流アークスラスタが用いられる。2. Description of the Related Art DC arc thrusters are used to control the orbit and attitude of artificial satellites and the like.
【0003】上記直流アークスラスタは、図2に示すよ
うなものである。[0003] The DC arc thruster is as shown in FIG.
【0004】即ち、人工衛星本体1にブラケット2を介
してアークスラスタ本体3を取付けると共に、アークス
ラスタ本体3の一端側に推進剤4などを噴射するための
ノズル5を係止させ、アークスラスタ本体3とノズル5
とで陽極6を構成させるようにする。That is, the arc thruster main body 3 is attached to the artificial satellite main body 1 via the bracket 2, and a nozzle 5 for injecting a propellant 4 or the like is locked at one end of the arc thruster main body 3. 3 and nozzle 5
Thus, the anode 6 is constituted.
【0005】前記アークスラスタ本体3の内部軸心位置
に、その先端がノズル5内に形成される空間7に位置す
るように陰極棒8を配置し、陽極6であるアークスラス
タ本体3と陰極棒8との間に絶縁材9を配設する。A cathode rod 8 is disposed at the inner axial position of the arc thruster main body 3 so that the tip thereof is located in a space 7 formed in the nozzle 5. An insulating material 9 is disposed between the insulating material 9 and the insulating material 9.
【0006】そして、アークスラスタ本体3の他端側に
コネクタ10、及び、給電ケーブル11を介して陽極6
と陰極棒8へ給電を行わせるための主放電用電源装置1
2を接続する。The other end of the arc thruster main body 3 is connected to the anode 6 via a connector 10 and a power supply cable 11.
Discharge power supply 1 for supplying power to the cathode rod 8
2 is connected.
【0007】更に、アークスラスタ本体3の内部に、推
進剤4などを前記空間7へと案内する推進剤供給路13
を形成し、推進剤供給路13に、推進剤供給源14、多
段のオリフィスから成り、流量調整機構として機能する
流体抵抗器15、二段に設けられたON−OFFのため
の推薬弁16,17、熱バリヤ18、推進剤4を分解す
るための触媒層を収容したガスジェネレータ19などを
備えた推進剤供給流路部20を接続する。Further, a propellant supply passage 13 for guiding the propellant 4 and the like to the space 7 is provided inside the arc thruster main body 3.
And a propellant supply path 14, a propellant supply source 14, a fluid resistor 15 composed of multi-stage orifices and functioning as a flow rate adjusting mechanism, and a propellant valve 16 for ON-OFF provided in two stages. , 17, a thermal barrier 18, and a propellant supply channel section 20 including a gas generator 19 containing a catalyst layer for decomposing the propellant 4.
【0008】かかる構成によれば、主放電用電源装置1
2から給電ケーブル11及びコネクタ10を介して陽極
6と陰極棒8へ給電を行わせることにより、ノズル5と
陰極棒8先端との間にアーク放電を発生させる。According to this configuration, the main discharge power supply device 1
By supplying power to the anode 6 and the cathode rod 8 from the power supply 2 via the power supply cable 11 and the connector 10, an arc discharge is generated between the nozzle 5 and the tip of the cathode rod 8.
【0009】この状態で、動作を確実化するため二段に
設けられた推薬弁16,17を開けることにより、推進
剤供給源14の推進剤4を、推進剤供給流路部20、及
び、推進剤供給路13を介して空間7へ供給させる。In this state, the propellant 4 of the propellant supply source 14 is opened by opening the propellant valves 16 and 17 provided in two stages to ensure the operation, so that the propellant supply flow path 20 and Is supplied to the space 7 via the propellant supply path 13.
【0010】この際、多段のオリフィスから成る流体抵
抗器15で、推進剤4の流量が調整され、ガスジェネレ
ータ19で触媒層によって推進剤4が分解され、分解に
よって気化され、体積が膨張された推進剤4が推進剤供
給路13を介してアークスラスタ本体3のノズル5へと
送られる。At this time, the flow rate of the propellant 4 is adjusted by the fluid resistor 15 composed of multi-stage orifices, and the propellant 4 is decomposed by the catalyst layer in the gas generator 19, and is vaporized by decomposition and expanded in volume. The propellant 4 is sent to the nozzle 5 of the arc thruster main body 3 via the propellant supply path 13.
【0011】この際、ガスジェネレータ19での推進剤
4の分解は発熱反応であるため、分解により発生した熱
が推薬弁16,17や流体抵抗器15などへ伝わること
のないように、熱バリヤ18が熱を遮断する。At this time, since the decomposition of the propellant 4 in the gas generator 19 is an exothermic reaction, the heat generated by the decomposition is not so transmitted to the propellant valves 16 and 17 and the fluid resistor 15 that the heat is generated. Barrier 18 blocks heat.
【0012】すると、アーク放電のエネルギーで空間7
内の推進剤4が加熱され、こうして加熱された推進剤4
がノズル5から噴射されることにより、少ない推進剤4
で効率的に人工衛星などの軌道制御や姿勢制御を行わせ
ることができる。Then, the energy of the arc discharge causes the space 7
The propellant 4 inside is heated, and the propellant 4 thus heated
Is sprayed from the nozzle 5 to reduce the amount of propellant 4
Thus, orbit control and attitude control of an artificial satellite or the like can be efficiently performed.
【0013】[0013]
【発明が解決しようとする課題】しかしながら、上記従
来の直流アークスラスタには、以下のような問題があっ
た。However, the above-mentioned conventional DC arc thruster has the following problems.
【0014】即ち、直流アークスラスタは、少ない推進
剤4によって稼働するようになっているため、推進剤4
の流量に対する許容範囲が狭い。That is, since the DC arc thruster is operated by a small amount of the propellant 4,
The allowable range for the flow rate is narrow.
【0015】一方、推進剤4を供給する推進剤供給源1
4は、推進剤4を使用するに従って内部の推進剤4の圧
力が次第に減少されて行くこととなるが、推進剤供給源
14の容量が大きい場合には、推進剤4の使用による推
進剤供給源14の圧力の減少の度合いは小さいものとな
り、反対に、推進剤供給源14の容量が小さい場合に
は、推進剤4の使用による推進剤供給源14の圧力の減
少度合いは大きなものとなる傾向にある。On the other hand, a propellant supply source 1 for supplying a propellant 4
4, the pressure of the internal propellant 4 is gradually reduced as the propellant 4 is used, but when the capacity of the propellant supply source 14 is large, the propellant supply by using the propellant 4 is performed. The decrease in the pressure of the propellant supply 14 due to the use of the propellant 4 is large when the volume of the propellant supply 14 is small. There is a tendency.
【0016】ところが、人工衛星などでは、厳しい重量
制限があることから、推進剤供給源14として余り容量
の大きなタンクを搭載することができず、むしろ、必要
最小限の容量を有する小さなタンクを搭載することが望
ましいこととなる。However, due to strict weight restrictions in artificial satellites and the like, a tank with an excessively large capacity cannot be mounted as the propellant supply source 14, but rather a small tank having a necessary minimum capacity is mounted. Would be desirable.
【0017】すると、上記したように、小容量の推進剤
供給源14は、圧力の減少度合いが大きいため、即ち、
圧力変動が大きいため、図2のような機構では、直流ア
ークスラスタにおける推進剤流量の許容範囲に合った圧
力範囲からすぐに外れてしまうこととなり、直流アーク
スラスタが十分な性能を発揮できなくなってしまう。Then, as described above, the small-capacity propellant supply source 14 has a large pressure reduction degree, that is,
Since the pressure fluctuation is large, in the mechanism as shown in FIG. 2, the DC arc thruster immediately deviates from the pressure range that matches the allowable range of the propellant flow rate, and the DC arc thruster cannot exhibit sufficient performance. I will.
【0018】本発明は、上述の実情に鑑み、推進剤の供
給圧力の変動に拘らず十分な性能を発揮させ得るように
した直流アークスラスタを提供することを目的とするも
のである。The present invention has been made in view of the above circumstances, and has as its object to provide a DC arc thruster capable of exhibiting sufficient performance irrespective of fluctuations in the propellant supply pressure.
【0019】[0019]
【課題を解決するための手段】本発明は、推進剤供給源
14からアークスラスタ本体3へ推進剤4を送給する推
進剤供給流路部20の途中に流量調整弁22を設け、流
量調整弁22の出側に推進剤4の流れを均一化可能な流
体抵抗器21を設けたことを特徴とする直流アークスラ
スタにかかるものである。According to the present invention, a flow rate adjusting valve 22 is provided in the middle of a propellant supply flow path section 20 for feeding a propellant 4 from a propellant supply source 14 to an arc thruster main body 3. According to a DC arc thruster, a fluid resistor 21 capable of equalizing the flow of the propellant 4 is provided on the outlet side of the valve 22.
【0020】この場合において、推進剤供給源14に圧
力検出器23を設け、圧力検出器23からの圧力検出信
号24に基づき、流量調整弁22へ開閉指令信号25を
送る制御装置26を設けるようにしても良い。In this case, a pressure detector 23 is provided in the propellant supply source 14, and a control device 26 for sending an opening / closing command signal 25 to the flow regulating valve 22 based on a pressure detection signal 24 from the pressure detector 23 is provided. You may do it.
【0021】上記手段によれば、以下のような作用が得
られる。According to the above means, the following effects can be obtained.
【0022】推進剤供給源14に設けた圧力検出器23
が推進剤供給源14の圧力を検出し、圧力検出器23か
らの圧力検出信号24が制御装置26へ送られ、制御装
置26が圧力検出器23からの圧力検出信号24に基づ
き、流量調整弁22へ開閉指令信号25を送り、流量調
整弁22を開閉させる。Pressure detector 23 provided in propellant supply source 14
Detects the pressure of the propellant supply source 14, a pressure detection signal 24 from the pressure detector 23 is sent to the control device 26, and based on the pressure detection signal 24 from the pressure detector 23, the control device 26 An opening / closing command signal 25 is sent to 22 to open and close the flow control valve 22.
【0023】その結果、推進剤供給源14の圧力が高い
場合には、流量調整弁22の開時間が短くなるように調
整され、又、推進剤供給源14の圧力が低くなった場合
には、流量調整弁22の開時間が長くなるように調整さ
れる。As a result, when the pressure of the propellant supply source 14 is high, the opening time of the flow control valve 22 is adjusted to be short, and when the pressure of the propellant supply source 14 becomes low, The opening time of the flow control valve 22 is adjusted to be long.
【0024】これにより、推進剤供給源14の圧力に拘
らず、推進剤4の流量を所望の流量とすることが可能と
なり、圧力変動の大きい小容量の推進剤供給源14を使
用しても、直流アークスラスタの性能を十分発揮させる
ことが可能となる。Thus, the flow rate of the propellant 4 can be set to a desired flow rate irrespective of the pressure of the propellant supply source 14, and even if a small-capacity propellant supply source 14 having a large pressure fluctuation is used. Thus, the performance of the DC arc thruster can be sufficiently exhibited.
【0025】そして、流量調整弁22を通った推進剤4
は、流体抵抗器21で、僅かな抵抗によって流量を均一
化されることとなり、流量調整弁22の間欠動作による
変動が解消される。The propellant 4 passing through the flow control valve 22
The flow resistance of the fluid resistor 21 is made uniform by a slight resistance, and the fluctuation caused by the intermittent operation of the flow control valve 22 is eliminated.
【0026】[0026]
【発明の実施の形態】以下、本発明の実施の形態を、図
示例と共に説明する。Embodiments of the present invention will be described below with reference to the drawings.
【0027】図1は、本発明の実施の形態の一例であ
る。FIG. 1 shows an embodiment of the present invention.
【0028】直流アークスラスタの基本的な構造につい
ては、図2と同様であるため、同一の部分については同
一の符号を付すことにより説明を省略する。Since the basic structure of the DC arc thruster is the same as that of FIG. 2, the same parts are denoted by the same reference numerals and description thereof will be omitted.
【0029】本発明では、推進剤供給流路部20を開閉
するため、二段に設けられた推薬弁16,17の上流側
の流体抵抗器21を、推進剤4の流量を均一化させ得る
程度の抵抗の小さなものとすると共に、流体抵抗器21
の上流側に間欠的に開閉可能な流量調整弁22を設け
る。In the present invention, in order to open and close the propellant supply flow path section 20, the fluid resistor 21 upstream of the propellant valves 16 and 17 provided in two stages is used to make the flow rate of the propellant 4 uniform. And the fluid resistance 21
A flow control valve 22 that can be opened and closed intermittently is provided on the upstream side.
【0030】そして、推進剤供給源14に圧力検出器2
3を設け、該圧力検出器23からの圧力検出信号24に
基づき、流量調整弁22へ開閉指令信号25を送る制御
装置26を設ける。Then, the pressure detector 2 is connected to the propellant supply source 14.
3 and a control device 26 for sending an open / close command signal 25 to the flow control valve 22 based on the pressure detection signal 24 from the pressure detector 23.
【0031】次に、作動について説明する。Next, the operation will be described.
【0032】直流アークスラスタの基本的な作動につい
ては図2の場合と同様なので説明を省略する。The basic operation of the DC arc thruster is the same as that shown in FIG.
【0033】本発明では、推進剤供給源14に設けた圧
力検出器23が推進剤供給源14の圧力を検出し、圧力
検出器23からの圧力検出信号24が制御装置26へ送
られ、制御装置26が圧力検出器23からの圧力検出信
号24に基づき、流量調整弁22へ開閉指令信号25を
送り、流量調整弁22を間欠的に開閉させる。According to the present invention, the pressure detector 23 provided in the propellant supply source 14 detects the pressure of the propellant supply source 14, and the pressure detection signal 24 from the pressure detector 23 is sent to the control device 26. The device 26 sends an open / close command signal 25 to the flow control valve 22 based on the pressure detection signal 24 from the pressure detector 23 to open and close the flow control valve 22 intermittently.
【0034】その結果、推進剤供給源14の圧力が高い
場合には、流量調整弁22の開時間が短く、閉時間が長
くなるように調整され、又、推進剤供給源14の圧力が
低くなった場合には、流量調整弁22の開時間が長く、
閉時間が短くなるように調整される。As a result, when the pressure of the propellant supply source 14 is high, the flow control valve 22 is adjusted so that the open time and the close time of the flow control valve 22 are short, and the pressure of the propellant supply source 14 is low. If it becomes, the open time of the flow control valve 22 is long,
It is adjusted to shorten the closing time.
【0035】これにより、推進剤供給源14の圧力に拘
らず、推進剤4の流量を所望の流量とすることが可能と
なり、圧力変動の大きい小容量の推進剤供給源14を使
用しても、直流アークスラスタの性能を十分発揮させる
ことが可能となる。Thus, the flow rate of the propellant 4 can be set to a desired flow rate irrespective of the pressure of the propellant supply source 14, and even if a small-capacity propellant supply source 14 having a large pressure fluctuation is used. Thus, the performance of the DC arc thruster can be sufficiently exhibited.
【0036】そして、流量調整弁22を通った推進剤4
は、流体抵抗器21で、僅かな抵抗によって流量を均一
化されることとなり、流量調整弁22の間欠動作による
流量の変動が解消される。The propellant 4 passing through the flow control valve 22
The flow rate is made uniform by a slight resistance in the fluid resistor 21, and the fluctuation of the flow rate due to the intermittent operation of the flow rate adjusting valve 22 is eliminated.
【0037】尚、本発明は、上述の実施の形態にのみ限
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。It should be noted that the present invention is not limited only to the above-described embodiment, and it is needless to say that various changes can be made without departing from the scope of the present invention.
【0038】[0038]
【発明の効果】以上説明したように、本発明の直流アー
クスラスタによれば、推進剤の供給圧力の変動に拘らず
十分な性能を発揮させることができるという優れた効果
を奏し得る。As described above, according to the DC arc thruster of the present invention, an excellent effect that sufficient performance can be exhibited irrespective of fluctuations in the supply pressure of the propellant can be obtained.
【図1】本発明の実施の形態の一例の概略側方断面図で
ある。FIG. 1 is a schematic side sectional view of an example of an embodiment of the present invention.
【図2】従来例の概略側方断面図である。FIG. 2 is a schematic side sectional view of a conventional example.
3 アークスラスタ本体 4 推進剤 14 推進剤供給源 20 推進剤供給流路部 21 流体抵抗器 22 流量調整弁 23 圧力検出器 24 圧力検出信号 25 開閉指令信号 26 制御装置 DESCRIPTION OF SYMBOLS 3 Arc thruster main body 4 Propellant 14 Propellant supply source 20 Propellant supply flow path 21 Fluid resistor 22 Flow rate regulating valve 23 Pressure detector 24 Pressure detection signal 25 Opening / closing command signal 26 Control device
Claims (2)
タ本体(3)へ推進剤(4)を送給する推進剤供給流路
部(20)の途中に流量調整弁(22)を設け、流量調
整弁(22)の出側に推進剤(4)の流れを均一化可能
な流体抵抗器(21)を設けたことを特徴とする直流ア
ークスラスタ。1. A flow control valve (22) is provided in the middle of a propellant supply passage (20) for supplying a propellant (4) from a propellant supply source (14) to an arc thruster body (3). A DC arc thruster comprising a fluid resistor (21) capable of equalizing the flow of a propellant (4) at an outlet side of a flow control valve (22).
3)を設け、圧力検出器(23)からの圧力検出信号
(24)に基づき、流量調整弁(22)へ開閉指令信号
(25)を送る制御装置(26)を設けた請求項1記載
の直流アークスラスタ。2. A pressure sensor (2) connected to a propellant supply source (14).
3. The control device according to claim 1, further comprising a control device for transmitting an open / close command signal to the flow control valve based on the pressure detection signal from the pressure detector. DC arc thruster.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP9158523A JPH116473A (en) | 1997-06-16 | 1997-06-16 | Dc arc thrustor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP9158523A JPH116473A (en) | 1997-06-16 | 1997-06-16 | Dc arc thrustor |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH116473A true JPH116473A (en) | 1999-01-12 |
Family
ID=15673607
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP9158523A Pending JPH116473A (en) | 1997-06-16 | 1997-06-16 | Dc arc thrustor |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH116473A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2016500787A (en) * | 2012-10-30 | 2016-01-14 | スネクマ | Propellant gas supply for ion propulsion unit |
CN104295462B (en) * | 2014-09-05 | 2017-02-15 | 兰州空间技术物理研究所 | Choke for adjusting flow rate of electric thrustor propellant and adjusting method |
CN113819023A (en) * | 2021-08-31 | 2021-12-21 | 北京控制工程研究所 | Propellant supply device of magnetic plasma power propulsion system |
-
1997
- 1997-06-16 JP JP9158523A patent/JPH116473A/en active Pending
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2016500787A (en) * | 2012-10-30 | 2016-01-14 | スネクマ | Propellant gas supply for ion propulsion unit |
CN104295462B (en) * | 2014-09-05 | 2017-02-15 | 兰州空间技术物理研究所 | Choke for adjusting flow rate of electric thrustor propellant and adjusting method |
CN113819023A (en) * | 2021-08-31 | 2021-12-21 | 北京控制工程研究所 | Propellant supply device of magnetic plasma power propulsion system |
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