JPS60110865A - Manufacture of thruster provided with heat radiating plate - Google Patents
Manufacture of thruster provided with heat radiating plateInfo
- Publication number
- JPS60110865A JPS60110865A JP58218782A JP21878283A JPS60110865A JP S60110865 A JPS60110865 A JP S60110865A JP 58218782 A JP58218782 A JP 58218782A JP 21878283 A JP21878283 A JP 21878283A JP S60110865 A JPS60110865 A JP S60110865A
- Authority
- JP
- Japan
- Prior art keywords
- plate
- thruster
- mandrel
- metal
- heat radiating
- 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.)
- Granted
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/18—After-treatment
- C23C4/185—Separation of the coating from the substrate
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
Description
【発明の詳細な説明】
本発明は、軒景かつ高性能の放熱板付スラスタ（ジェッ
トエンジン、ロケットエンジン等のように推進力を発生
させる装置、すなわち推進装置をいい、本発明では、燃
焼室とそれに続くノズルスカートとを併わせだもの、あ
るいは燃料、酸化剤を吹込む噴射器等も併わせてスラス
タと称する）の製造方法に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention refers to a thruster with an eaves and high performance heat sink (a device that generates propulsive force, such as a jet engine or a rocket engine, that is, a propulsion device), and in the present invention, a thruster with a combustion chamber and The present invention relates to a method of manufacturing a thruster, which includes a nozzle skirt that follows the nozzle skirt, or an injector that injects fuel and oxidizer.
人工衛星の姿勢制御等に使用する低推力ガスジェットス
ラスク構造体の溶射による金属成形体の従来例を第１図
に示す。本例は軽量、無冷却方式のスラスタであり、構
造体の材料として、高融点でしかも良好な熱伝導性を有
するモリブデン（ＭＯ）、ニオブ（Ｎｂ）等の金属を使
用している。FIG. 1 shows a conventional example of a thermally sprayed metal molded body for a low-thrust gas jet thrust structure used for attitude control of artificial satellites. This example is a lightweight, uncooled thruster, and uses metals such as molybdenum (MO) and niobium (Nb), which have a high melting point and good thermal conductivity, as the material of the structure.
当該スラスタは通常の使用においては問題ないが、連続
的な燃焼を特徴とする特殊な場合は、特にノズル部分が
高温となるだめ、高融点、高熱伝導特性を有する材料で
あっても使用条件が制限される場合が生じる。There is no problem with this thruster in normal use, but in special cases characterized by continuous combustion, the nozzle part in particular becomes high temperature, so even if the material has a high melting point and high thermal conductivity, the usage conditions may be different. There may be some restrictions.
本発明は、人工衛星用低推′カガスジェットスラスタ等
の製作において、軽量・無冷却方式のスラスタで、その
性能を向上させるだめになされたものである。The present invention was made in order to improve the performance of a lightweight, non-cooled thruster in the production of low thrust gas jet thrusters for artificial satellites.
すなわち本発明は、マンドレルの上に高融点・高熱伝導
性金属を溶射して被膜を形成し、これに板体を取シ付け
、該板体の上に上記高融点・高熱伝導性金属を溶射して
被膜を形成した後、該マンドレルと板体を化学的及び／
又は物理的に除去することを特徴とする放熱板付スラス
タの製造方法に関するものである。That is, the present invention sprays a high melting point, high thermal conductivity metal onto a mandrel to form a coating, attaches a plate to this, and sprays the high melting point, high thermal conductivity metal onto the plate. After forming the coating, the mandrel and plate are chemically and/or
Alternatively, the present invention relates to a method for manufacturing a thruster with a heat sink, characterized in that the heat sink is physically removed.
本発明は、人工術星アポジキツクモータスラスク、人工
衛星低推カスラスタばかりで永く、ロケットエンジン燃
焼室及びノズルスカート、その他放熱効果を上げたい航
空・宇宙用機器や一般産業用機器、部品等に適用するこ
とができる。The present invention has long been applied to artificial star apogee motor thrusters, artificial satellite low thrust thrusters, rocket engine combustion chambers and nozzle skirts, and other aerospace equipment and general industrial equipment and parts that want to improve heat dissipation effects. can do.
以下、添付図面等を参照して本発明の詳細な説明する。Hereinafter, the present invention will be described in detail with reference to the accompanying drawings and the like.
第２図（１）〜（５）は、本発明方法の一実施態様例を
示す図で、プラズマ溶射によシノズル部に金属放熱板を
形成し、スラスタ構造体として一体化した人工衛星用紙
推力ガスジェットスラスタの製作例を工程順に示してい
る。Figures 2 (1) to (5) are diagrams showing an example of an embodiment of the method of the present invention, in which a metal heat sink is formed on the nozzle part by plasma spraying, and an artificial satellite paper thrust is integrated as a thruster structure. An example of manufacturing a gas jet thruster is shown in the order of steps.
まず第２図（１）のようにマンドレル１を作る。First, make mandrel 1 as shown in Figure 2 (1).
マンドレル材料は本例では最終段階にＮａ０ＩＩ水溶液
で溶出するためアルミニウムを用いたがマンドレル除去
の際、溶射金属に悪影響を与えなければ他の材料、例え
ばＭｇ１ 鋼、ＰＩ）合金、Ｏｕ 合金等でも良く、除
去方法もＮａＯＨに限らずＨＮＯ３−ＨＯＬ ｅ ＲＦ
−ＨＮＯＩ ＋ ＥＦ 混合液も使用でき、また物理
的、機械的な方法でも良い。In this example, aluminum was used as the mandrel material because it is eluted with Na0II aqueous solution in the final stage, but other materials such as Mg1 steel, PI) alloy, Ou alloy, etc. may be used as long as it does not adversely affect the sprayed metal when removing the mandrel. , the removal method is not limited to NaOH but also HNO3-HOL e RF
A mixed solution of -HNOI + EF can also be used, and physical or mechanical methods may also be used.
マンドレル１の外側形状及び寸法は最終的に必要とする
金属成形体の内側形状及び寸法と一致させである。The outer shape and dimensions of the mandrel 1 are made to match the inner shape and dimensions of the finally required metal molded body.
なお、後述するように金属放熱板を溶射で形成するため
に使用するマンドレルの一種である円板も本例ではアル
ミニウムを用いたが、これの材料及び除去方法もマンド
レルの場合と同様である。Note that, as will be described later, the disc, which is a type of mandrel used to form a metal heat sink by thermal spraying, was also made of aluminum in this example, but the material and removal method for this are also the same as for the mandrel.
次に第２図（２）で示すようにマンドレル１を矢印方向
に回転させ、溶射ガン２にて金属（例えば、Ｍｏ、Ｗｂ
、Ｔａ、Ｔｉ、Ｗ等、本例ではＭ。Next, as shown in FIG. 2 (2), the mandrel 1 is rotated in the direction of the arrow, and the thermal spray gun 2 is used to spray metal
, Ta, Ti, W, etc., M in this example.
又はｘｂ ） を必要寸法まで溶射する。or xb) to the required dimensions.
第２図（３）では溶射によ多金属成形体となったスラス
タ１′のノズル部に放熱板形成用アルミニウム製の円板
３を装着し、この円板上３に溶射ガン２によるプラズマ
溶射によ多金属（本例ではｎｏ、Ｎｂ）を所定寸法にま
で形成させる。第２図（３）Φ）社第２図（３）体）の
ムーＡ′線断面図で、プラズマ溶射が終了した状態を示
している。In Fig. 2 (3), an aluminum disc 3 for forming a heat sink is attached to the nozzle part of the thruster 1', which has become a multi-metal molded body by thermal spraying, and a plasma spraying gun 2 sprays the aluminum disc 3 onto the disc 3. A multi-metal (NO, Nb in this example) is formed to a predetermined size. FIG. 2 (3) Φ) is a cross-sectional view taken along the line A' of FIG.
その後、第２図（４）に示すようにＮａ０ＩＩ水溶液（
１０チ〜２０チ）に浸漬し、マンドレル及び放熱板用円
板を溶出する。After that, as shown in Figure 2 (4), the Na0II aqueous solution (
10 to 20 inches) to elute the mandrel and heat sink disk.
第２図（５）はノズル部に放熱板が一体化された金属成
形体の最終形態である。第２図（５） （Ｂ）は第２図
（５） （Ａ）のＡ−Ａ’線断面図である。FIG. 2 (5) shows the final form of the metal molded body in which the heat sink is integrated into the nozzle part. FIG. 2(5)(B) is a sectional view taken along line AA' of FIG. 2(5)(A).
なお、上記のようにして製造されたスラスタの効果を確
認するために、該スラスタに異種２点衝突式噴射器を取
付け、推薬としてモノメチルヒドラジン、酸化剤として
Ｎ２Ｏ４を使用して実験を行ったととる、燃焼室内燃焼
ガス温度は約２５００℃、ノズル部内壁温度は約１５０
０℃となり、推力的０．５ユ〜１． ｏ ｋｇを得るこ
とができだ。In order to confirm the effectiveness of the thruster manufactured as described above, a heterogeneous two-point impingement injector was attached to the thruster, and an experiment was conducted using monomethylhydrazine as the propellant and N2O4 as the oxidizing agent. The combustion gas temperature in the combustion chamber is approximately 2500℃, and the nozzle inner wall temperature is approximately 150℃.
The temperature reached 0°C, and the thrust was 0.5 to 1. I can't get 0 kg.
以上詳述したように、本発明によれば、高性能の放熱板
付スラスタを得ることができ、しかもその重量もかなシ
軽量化することができ、工業上有益である。As described in detail above, according to the present invention, a high-performance thruster with a heat sink can be obtained, and its weight can also be significantly reduced, which is industrially useful.
第１図は通常の低推カガスジェットスラスタを示す図、
第２図（１）〜（５）は本発明方法の一実施態様例を工
程順に示す図である。
復代理人 内 １） 明
復代理人 萩 原 亮 −
も１図
県２図
２寸 −トクへ°−又
（４）Figure 1 shows a normal low-thrust gas jet thruster.
FIGS. 2(1) to 2(5) are diagrams showing an embodiment of the method of the present invention in order of steps. Sub-agent 1) Meifuku agent Ryo Hagiwara - 1 map prefecture 2 map 2 sun -Tokuhe°-Mata (4)
Claims (1)
膜を形成し、これに板体を取シ付け、該板体の上に上記
高融点・高熱−伝導性金属を溶射して被膜を形成した後
、該マンドレルと板体を化学的及び／又は物理的に除去
することを特徴とする放熱板付スラスタの製造方法。A high melting point, high thermal conductivity metal is thermally sprayed onto the mandrel to form a coating, a plate is attached to this, and the high melting point, high thermal conductivity metal is thermally sprayed onto the plate to form a coating. A method for manufacturing a thruster with a heat sink, which comprises chemically and/or physically removing the mandrel and plate after forming.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP58218782A JPS60110865A (en) | 1983-11-22 | 1983-11-22 | Manufacture of thruster provided with heat radiating plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP58218782A JPS60110865A (en) | 1983-11-22 | 1983-11-22 | Manufacture of thruster provided with heat radiating plate |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS60110865A true JPS60110865A (en) | 1985-06-17 |
| JPH0447026B2 JPH0447026B2 (en) | 1992-07-31 |
Family
ID=16725288
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP58218782A Granted JPS60110865A (en) | 1983-11-22 | 1983-11-22 | Manufacture of thruster provided with heat radiating plate |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS60110865A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5141847A (en) * | 1974-10-04 | 1976-04-08 | Matsushita Electric Ind Co Ltd | DENGENSOCHI |
| JPS522364A (en) * | 1975-06-23 | 1977-01-10 | Ibm | Power amplifier means improper operation detector |
| JPS531310A (en) * | 1976-06-28 | 1978-01-09 | Hitachi Ltd | Motor-driven compressor of totally sealed type |
| JPS5347416A (en) * | 1976-10-13 | 1978-04-27 | Sumitomo Chemical Co | Manufacture of betaaalumina thin films |
-
1983
- 1983-11-22 JP JP58218782A patent/JPS60110865A/en active Granted
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5141847A (en) * | 1974-10-04 | 1976-04-08 | Matsushita Electric Ind Co Ltd | DENGENSOCHI |
| JPS522364A (en) * | 1975-06-23 | 1977-01-10 | Ibm | Power amplifier means improper operation detector |
| JPS531310A (en) * | 1976-06-28 | 1978-01-09 | Hitachi Ltd | Motor-driven compressor of totally sealed type |
| JPS5347416A (en) * | 1976-10-13 | 1978-04-27 | Sumitomo Chemical Co | Manufacture of betaaalumina thin films |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0447026B2 (en) | 1992-07-31 |
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