JPS63215861A - Catalyst type hydrazine thruster - Google Patents
Catalyst type hydrazine thrusterInfo
- Publication number
- JPS63215861A JPS63215861A JP5076787A JP5076787A JPS63215861A JP S63215861 A JPS63215861 A JP S63215861A JP 5076787 A JP5076787 A JP 5076787A JP 5076787 A JP5076787 A JP 5076787A JP S63215861 A JPS63215861 A JP S63215861A
- Authority
- JP
- Japan
- Prior art keywords
- hydrazine
- catalyst
- injectors
- tube
- thruster
- 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
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 title claims abstract description 102
- 239000003054 catalyst Substances 0.000 title claims abstract description 33
- 239000003380 propellant Substances 0.000 claims abstract description 12
- 238000000354 decomposition reaction Methods 0.000 claims description 14
- 230000003197 catalytic effect Effects 0.000 claims description 12
- 239000007921 spray Substances 0.000 claims description 5
- 238000007599 discharging Methods 0.000 claims description 3
- 239000007789 gas Substances 0.000 abstract description 7
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 abstract description 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 abstract description 6
- 229910021529 ammonia Inorganic materials 0.000 abstract description 3
- 229910052757 nitrogen Inorganic materials 0.000 abstract description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 abstract description 2
- 239000001257 hydrogen Substances 0.000 abstract description 2
- 229910052739 hydrogen Inorganic materials 0.000 abstract description 2
- 239000000203 mixture Substances 0.000 abstract 1
- 230000004044 response Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000004043 responsiveness Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 229910001868 water Inorganic materials 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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
-
- 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
- B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Exhaust Gas Treatment By Means Of Catalyst (AREA)
- Treatment Of Water By Oxidation Or Reduction (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
この発明は例えば９人工衛星用推進系の推力を発生する
スラスタに関するものである。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a thruster that generates thrust for a propulsion system for, for example, nine artificial satellites.
第３図は従来の人工衛星用触媒式ヒドラジンスラスタの
説明図である。第３図において、（１）は配管、（２）
は推薬弁、（３）はチューブ、（４）はフランジ。FIG. 3 is an explanatory diagram of a conventional catalytic hydrazine thruster for artificial satellites. In Figure 3, (1) is piping, (2)
is a propellant valve, (3) is a tube, and (4) is a flange.
（５）はサーマルシールド、（６）は固定ネジ、（７）
はワッシャ、（８）はノズル、（９）は分解チユンバ、
α〔はメツシュ、 ＋ｉｌｌは触媒、 ａＺはフィード
チューブ、 １３は推薬であるヒドラジンを噴舞するイ
ンジュクタである。(5) is a thermal shield, (6) is a fixing screw, (7)
is a washer, (8) is a nozzle, (9) is a disassembly chamber,
α[ is a mesh, +ill is a catalyst, aZ is a feed tube, and 13 is an injector that sprays hydrazine, which is a propellant.
従来の眉媒式ヒドラジンスラスタは、上記のように構成
され、推桑であるヒドラジンは加圧ガスで所定の圧力に
加圧されて、配管（１）に供給されており、推薬弁（２
）を駆動信号により開状態にすることにより、推薬弁（
２）からチューブ（３）を通りフィードチューブａ’ａ
Ｖｃ導かれる。フィードチューブに導かれたヒドラジン
は、インジュクタａ３により噴霧状態にされ９分解チユ
ンバ（９）の内部にふりまかれる。分解チユンバ（９）
内に噴霧されたヒドラジンは触媒αυに接触すると分解
発熱反応を起こし、アンモニア、窒素および水素の混合
ガス圧分解され。The conventional propellant-type hydrazine thruster is constructed as described above, and the propellant, hydrazine, is pressurized to a predetermined pressure with pressurized gas and supplied to the piping (1), and the propellant valve (2) is supplied to the piping (1).
) is opened by a drive signal, the propellant valve (
2) through tube (3) to feed tube a'a
Vc is guided. The hydrazine introduced into the feed tube is made into a spray state by the injector a3 and sprinkled inside the 9-decomposition chamber (9). Decomposition Chiyumba (9)
When the sprayed hydrazine comes into contact with the catalyst αυ, it undergoes a decomposition exothermic reaction and is decomposed under the pressure of a mixed gas of ammonia, nitrogen and hydrogen.
ノズル（８）から宇宙空間にこの分解ガス′ｆ排出する
ことにより推力を得るものであった。Thrust was obtained by discharging this decomposed gas 'f into space from a nozzle (8).
触媒式ヒドラジンスラスタの応答性は、ヒドラジンの供
給圧力、ヒドラジンと触媒の初期温度等によって影響を
受けるが、初期温度および圧力を同じとすると推薬であ
るヒドラジンが川Ｉυに速く、万遇無く接触することに
より良くなる。The response of the catalytic hydrazine thruster is affected by the supply pressure of hydrazine, the initial temperature of hydrazine and the catalyst, etc., but if the initial temperature and pressure are the same, the hydrazine propellant will come into contact with the river Iυ quickly and without any chance. It gets better by doing.
すでに述べた従来の触媒式ヒドラジンスラスタでは、イ
ンジュクタ０３でヒドラジンヲ噴霧させても、触媒ａυ
の片寄りのため、触媒に万遇無くヒドラジンが接触せず
、ヒドラジンの分解が遅くなり。In the conventional catalytic hydrazine thruster mentioned above, even if hydrazine is sprayed by the injector 03, the catalyst aυ
Due to the unevenness of the hydrazine, hydrazine does not come into contact with the catalyst, which slows down the decomposition of hydrazine.
振力を発生する応答性が悪くなるとともに、応答性のバ
ラツキが大きくなる間趙があった。There was a problem in which the responsiveness of generating vibration force deteriorated and the variation in responsiveness increased.
この発明は、かかる問題点を解決するためになされたも
ので、従来の触媒式ヒドラジンスラスタと比較して応答
性を良くすることができるとともに応答性のバラツキを
小さく抑えることができる触媒式ヒドラジンスラスタを
得ることを目的としたものである。This invention was made to solve these problems, and is a catalytic hydrazine thruster that can improve responsiveness and suppress variations in response compared to conventional catalytic hydrazine thrusters. The purpose is to obtain.
Ｃ問題点を解決するための手段〕 この発明に係わる触媒式ヒドラジンスラスタは。Measures to solve problem C] The catalytic hydrazine thruster according to this invention is:
フィードチューブの数を増加して、インジュクタを多重
化させ、さらに分解チユンバ内の触媒室をインジュクタ
の数に対応させて分割して、その分割された触媒室に触
媒をつめて、速く、万遍無くヒドラジンを触媒に接触す
るようにしたものである。By increasing the number of feed tubes and multiplexing injectors, by dividing the catalyst chamber in the decomposition chamber according to the number of injectors, and by filling the divided catalyst chambers with catalyst, it can be distributed quickly and universally. In this case, hydrazine is brought into contact with the catalyst.
この発明におけるインジュクタは、多重化され。 The injector in this invention is multiplexed.
ヒドラジンを万遇無＜噴霧する。また２分解チユンバ内
の触媒室は、従来通り上流と下流に分け。Spray hydrazine. In addition, the catalyst chamber in the bicomponent chamber is divided into upstream and downstream sections as before.
さらに上流の７！ＩＬｉｘ内にインジュクタに対応した
複数の触媒室をもうけることにより、 ｌ’ｊｊ＆され
たヒドラジンを触媒にすばやく接触させ分解する。7 further upstream! By providing a plurality of catalyst chambers corresponding to the injectors in ILix, the l'jj& hydrazine is quickly brought into contact with the catalyst and decomposed.
第１図は、この発明の一実施例を示す説明図である。（
１１〜ａｎは、上記従来装置と全く同一のものである。FIG. 1 is an explanatory diagram showing an embodiment of the present invention. (
11 to an are completely the same as the conventional device described above.
ｒｌりはフィードチューブ、 ＋１３はインジュクタ、
（１４１は細い触媒、［１９は細い触媒Ｉをとじこめ
る細いメツシュである。rl is the feed tube, +13 is the injector,
(141 is a thin catalyst, [19 is a thin mesh that confines the thin catalyst I.
第２図は、この発明の特徴である上記触媒式ヒドラジン
スラスタの分解チユンバ（９）の−実施例の基本構造を
示す断面図である。α３は多重化したインジュクタ、ａ
！９は触媒を分割する細いメツシュである。FIG. 2 is a sectional view showing the basic structure of an embodiment of the decomposition chamber (9) of the catalytic hydrazine thruster, which is a feature of the present invention. α3 is a multiplexed injector, a
! 9 is a thin mesh that divides the catalyst.
上記のように構成された触媒式ヒドラジンスラスタにお
いては、４つのインジュクタＯは推薬弁（２）を開状態
にし、配管（１）からチューブ（３）を通過して、フィ
ードチューブα２に供給されたヒドラジンを噴霧状態に
する。また、インジュクタａ３で噴霧状態になったヒド
ラジンが細いメツシュα９で分割されたｐＢｌｔｓ呈内
の細い触媒に接触するとヒドラジンは分解発熱反応を起
こし、アンモニア、窒素および水系の混合ガスに分解す
る。このヒドラジンの分解ガスをノズル（８）より宇宙
空間に排出することにより推力を得ることができる。In the catalytic hydrazine thruster configured as described above, the four injectors O open the propellant valves (2), and the propellant is supplied from the piping (1) through the tube (3) to the feed tube α2. Make the hydrazine into a spray state. Further, when the hydrazine sprayed by the injector a3 comes into contact with the thin catalyst in the pBlts divided by the thin mesh α9, the hydrazine undergoes a decomposition exothermic reaction and is decomposed into a mixed gas of ammonia, nitrogen and water. Thrust can be obtained by discharging this decomposed gas of hydrazine into space from the nozzle (8).
この実施例では４つのインジュクタ０によりヒドラジン
が分解チユンバ（９）内に万遍無り噴霧され。In this embodiment, hydrazine is evenly sprayed into the decomposition chamber (9) by four injectors 0.
その＠霧されたヒドラジンが細いメツシュα９で分解さ
れた細い触媒に速く万遇無く接触するので。Because the atomized hydrazine quickly and without incident comes into contact with the thin catalyst decomposed by the thin mesh α9.
ヒドラジンの分解を速くできる。このため、従来Ω触媒
式ヒドラジンスラスタよりも初期温度、圧力等を同じ条
件とすれば応答性を良くすることができる。また、細い
メツシュで細い触媒を分割し。It can speed up the decomposition of hydrazine. Therefore, if the initial temperature, pressure, etc. are set to the same conditions as in the conventional Ω catalyst type hydrazine thruster, the response can be improved. In addition, the thin catalyst can be divided with a thin mesh.
触媒の片寄りをなくすことにより、ヒドラジンの分解の
再現性が良くなり、応答性のバラツキを小さくおさえる
ことができる。By eliminating the unevenness of the catalyst, the reproducibility of hydrazine decomposition can be improved and variations in response can be suppressed.
ところで、上記実施例ではフィードチューブｆｉＸ５゜
インジュクタα３および細いメツシュαりで分割された
触媒室は４つの場合で説明したが２つ以上で良いことは
いうまでもない。Incidentally, in the above embodiment, the case was explained in which there were four catalyst chambers divided by the feed tube fiX5° injector α3 and the thin mesh α, but it goes without saying that two or more catalyst chambers may be used.
この発明は以上説明したとおり、フィードチューブ、イ
ンジュクタおよび細いメツシュで分割された７！！！媒
呈を多重化した簡単な構造によってＩｐ！ＪＬ媒式ヒド
ラジンスラスタの応答性を良くすることができ９人工衛
星の姿勢制御性能を向上できるという効果がある。As explained above, this invention consists of 7 tubes divided by a feed tube, an injector, and a thin mesh. ! ! Ip! with a simple structure that multiplexes media. This has the effect of improving the response of the JL medium type hydrazine thruster and improving the attitude control performance of the 9 satellites.
また、この発明は、ヒドラジンと触媒の接触の再現性が
良くなり、ヒドラジンの分解の再現性が良くなるため、
触媒式ヒドラジンスラスタの推力。In addition, this invention improves the reproducibility of the contact between hydrazine and the catalyst, and improves the reproducibility of the decomposition of hydrazine.
Thrust from a catalytic hydrazine thruster.
インパルスの再現性が良くなるという効果がある。This has the effect of improving impulse reproducibility.
第１図は、この発明の一実施例を示す触媒式ヒドラジン
スラスタの説明図、第２図は、この発明のＭ媒呈の一実
施例を示す断面図、第３図は、従来の触媒式ヒドラジン
スラスタの説明図である。
図において、（１）は配管、（２）は推桑弁、（３）は
チューブ、（４）はフランジ、（５）はサーマルシール
ド、（６）は固定ネジ、（７）はワッシャ、（８）はノ
ズル、（９）は分解チユンバ、 （１ＣＩはメツシュ
、Ｌｌｌｌは触媒、σ２はフィードチューブ、α３はイ
ンジュクタ、（Ｉ４は細い触媒。
αりは細いメツシュである。
なお２図中同一符号は同一または相当部分を示す。FIG. 1 is an explanatory diagram of a catalytic hydrazine thruster showing one embodiment of the present invention, FIG. 2 is a sectional view showing an embodiment of the M medium of the present invention, and FIG. 3 is a conventional catalytic hydrazine thruster. It is an explanatory view of a hydrazine thruster. In the figure, (1) is piping, (2) is a push valve, (3) is a tube, (4) is a flange, (5) is a thermal shield, (6) is a fixing screw, (7) is a washer, ( 8) is the nozzle, (9) is the decomposition chamber, (1CI is the mesh, Lllll is the catalyst, σ2 is the feed tube, α3 is the injector, (I4 is the thin catalyst. indicate the same or equivalent part.
Claims (1)
流れを開閉制御する推薬弁と、上記推薬弁からのヒドラ
ジンを導くチューブおよび多重化されたフィードチュー
ブと、上記チューブとフィードチューブにより導かれた
ヒドラジンを噴霧状態にする多重化されたインジュクタ
と、噴霧されたヒドラジンを分解する触媒および細い触
媒と、触媒を塞き止めるメッシュおよび細いメッシュと
、上記のフィードチューブ、メッシュを保持する分解チ
ユンバと、上記の分解チユンバ内のヒドラジン分解ガス
を宇宙空間に排出するノズルとを備えたことを特徴とす
る触媒式ヒドラジンスラスタ。A pipe that supplies hydrazine as a propellant, a propellant valve that controls the opening and closing of the flow of hydrazine, a tube that guides hydrazine from the propellant valve, a multiplexed feed tube, and a tube that is guided by the above tube and the feed tube. a multiplexed injector that brings the sprayed hydrazine into a spray state; a catalyst and thin catalyst that decomposes the sprayed hydrazine; a mesh and thin mesh that blocks the catalyst; and a decomposition chamber that holds the feed tube and the mesh. A catalytic hydrazine thruster comprising: a nozzle for discharging the hydrazine decomposed gas in the decomposition chamber into space.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5076787A JPS63215861A (en) | 1987-03-05 | 1987-03-05 | Catalyst type hydrazine thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5076787A JPS63215861A (en) | 1987-03-05 | 1987-03-05 | Catalyst type hydrazine thruster |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS63215861A true JPS63215861A (en) | 1988-09-08 |
Family
ID=12867984
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5076787A Pending JPS63215861A (en) | 1987-03-05 | 1987-03-05 | Catalyst type hydrazine thruster |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63215861A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009257155A (en) * | 2008-04-15 | 2009-11-05 | Ihi Aerospace Co Ltd | Monopropellant thruster |
| JP2015517621A (en) * | 2012-05-09 | 2015-06-22 | イーシーエイピーエス・アクチボラグ | Improved reactor for ammonium dinitramide based liquid monopropellant and a thruster including such a reactor |
| CN110043391A (en) * | 2019-04-17 | 2019-07-23 | 上海空间推进研究所 | Cellular-type catalytic bed and engine propulsion method |
-
1987
- 1987-03-05 JP JP5076787A patent/JPS63215861A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009257155A (en) * | 2008-04-15 | 2009-11-05 | Ihi Aerospace Co Ltd | Monopropellant thruster |
| JP2015517621A (en) * | 2012-05-09 | 2015-06-22 | イーシーエイピーエス・アクチボラグ | Improved reactor for ammonium dinitramide based liquid monopropellant and a thruster including such a reactor |
| CN110043391A (en) * | 2019-04-17 | 2019-07-23 | 上海空间推进研究所 | Cellular-type catalytic bed and engine propulsion method |
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