JPH0751470B2 - Gas generating agent - Google Patents
Gas generating agentInfo
- Publication number
- JPH0751470B2 JPH0751470B2 JP1581388A JP1581388A JPH0751470B2 JP H0751470 B2 JPH0751470 B2 JP H0751470B2 JP 1581388 A JP1581388 A JP 1581388A JP 1581388 A JP1581388 A JP 1581388A JP H0751470 B2 JPH0751470 B2 JP H0751470B2
- Authority
- JP
- Japan
- Prior art keywords
- gas generating
- generating agent
- combustion chamber
- particle size
- weight
- 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.)
- Expired - Lifetime
Links
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- Solid Fuels And Fuel-Associated Substances (AREA)
- Air Bags (AREA)
Description
【発明の詳細な説明】 （産業上の利用分野） この発明は、固体ラムロケット用のガス発生剤に関す
る。TECHNICAL FIELD The present invention relates to a gas generating agent for a solid ram rocket.
（従来の技術） 固体ラムロケットは、通常、１次燃料室で金属燃料分の
多いガス発生剤を燃焼させて、その燃焼生成物を２次燃
焼室へ導いて、２次燃焼室内に取り入れた空気によって
完全燃焼させるものであり、普通のロケットに比較し
て、高比推力を得ることができる。このガス発生剤とし
ては、例えば、ジャーナル・オプ・スペースクラフト・
アンド・ロケット（Journa of Spacecraft＆Rocket）19
82年No.4に示されるように、発火温度が比較的低いマグ
ナリウムや燃焼熱の高い硼素を金属燃料に使用し、その
含有量を30〜50％としたものが用いられている。ただし
硼素の粒径は、ガス発生剤製造上の観点から、一般に１
ミクロン以上の粒径のものが用いられている。(Prior Art) A solid ram rocket normally burns a gas generating agent rich in metallic fuel in a primary fuel chamber, guides the combustion product to a secondary combustion chamber, and takes it into the secondary combustion chamber. Since it is completely burned by air, it is possible to obtain a high specific thrust as compared with a normal rocket. Examples of this gas generating agent include, for example, Journal Op Spacecraft
And Rocket (Journa of Spacecraft & Rocket) 19
As shown in No.4 in 1982, magnalium having a relatively low ignition temperature and boron having a high combustion heat are used as a metal fuel, and the content thereof is 30 to 50%. However, the particle size of boron is generally 1 from the viewpoint of manufacturing the gas generating agent.
It has a particle size of micron or more.
（発明が解決しようとする問題点） しかしながら、この従来のガス発生剤においては、もと
もとマグナリウムの燃焼熱が比較的低いために、発生す
る比推力に限界がある。また、この欠点を補うために硼
素を使用することが考えられるが、硼素の粒径が比較的
大きいために、１次燃焼室で金属燃料の一部が燃焼して
発生したエネルギーが金属燃料粒子自身の温度上昇のた
めに消費されてしまい、２次燃焼室における燃焼効率が
低下し、やはり比推力が低下してしまうという問題点が
ある。(Problems to be Solved by the Invention) However, in this conventional gas generating agent, since the combustion heat of magnalium is originally relatively low, the specific thrust generated is limited. Further, it is possible to use boron to make up for this drawback. However, since the particle size of boron is relatively large, the energy generated by burning a part of the metal fuel in the primary combustion chamber is the metal fuel particle. There is a problem that it is consumed due to its own temperature rise, the combustion efficiency in the secondary combustion chamber decreases, and the specific thrust also decreases.
本発明の目的は、かかる従来のガス発生剤の欠点を解消
し、固体ラムロケットの性能の中で最も重要視されてい
る比推力の優れた固体ラムロケット用ガス発生剤を提供
することにある。An object of the present invention is to solve the drawbacks of the conventional gas generating agent and to provide a gas generating agent for a solid ram rocket, which has the highest specific thrust, which is regarded as the most important performance of the solid ram rocket. .
（問題点を解決するための手段） 本発明は、マグナリウムを金属燃料として含有する固体
ラムロケット用のガス発生剤において、平均粒径が0.3
ミクロン以下の硼素粉末を１〜５重量％配合したことを
特徴とするガス発生剤である。(Means for Solving Problems) The present invention provides a gas generating agent for a solid ram rocket containing magnalium as a metal fuel, having an average particle size of 0.3.
It is a gas generating agent characterized by containing 1 to 5% by weight of a boron powder of not more than micron.
硼素粉末の配合量は、製造上の観点から５重量％以下で
あることが必要であり、１重量％未満では顕著な効果が
得られないので１〜５重量％とする。From the viewpoint of production, the content of the boron powder needs to be 5% by weight or less, and if it is less than 1% by weight, a remarkable effect cannot be obtained.
本発明のガス発生剤には、１次燃焼室での金属燃料の燃
焼を持続するための酸化剤、及び、金属燃料と酸化剤を
結合させて一定の形状で成形するバインダーが配合され
る。The gas generating agent of the present invention contains an oxidant for sustaining the combustion of the metal fuel in the primary combustion chamber, and a binder for combining the metal fuel and the oxidant to form a certain shape.
酸化剤としては、過塩素酸アンモニウムなどが用いられ
る。酸化剤の配合量は、通常30〜50重量％である。Ammonium perchlorate or the like is used as the oxidizing agent. The compounding amount of the oxidizing agent is usually 30 to 50% by weight.
また、バインダーとしては、末端カルボキシル基化ポリ
ブタジェン（CTPB）や、末端水酸基化ポリブタジェン
（HTPB）などが用いられる。バインダーの配合量は通常
15〜30重量％とする。Moreover, as the binder, a terminal carboxyl group-containing polybutadiene (CTPB), a terminal hydroxyl group-containing polybutadiene (HTPB), or the like is used. Binder content is usually
15 to 30% by weight.
（発明の効果） 一般に、金属粒子は、その粒径が小さくなると、物理化
学特性が変化するといわれている。粒径0.3ミクロン以
下の硼素粉末を１〜５重量％添加することによって、硼
素粒子の２次燃焼室における燃焼を促進して燃焼効率を
マグナリウムのみのガス発生剤のそれと同等に維持しな
がら、ラムロケットの比推力を高め、その性能を向上さ
せることができるという効果が得られる。(Effect of the Invention) Generally, it is said that the physicochemical properties of metal particles change as the particle size decreases. By adding 1 to 5% by weight of boron powder having a particle size of 0.3 micron or less, the combustion of boron particles in the secondary combustion chamber is promoted and the combustion efficiency is maintained at the same level as that of the gas generating agent containing only magnalium. This has the effect of increasing the specific thrust of the rocket and improving its performance.
（実施例） 以下本発明を実施例および比較例により説明する。(Examples) The present invention will be described below with reference to Examples and Comparative Examples.
実施例１〜6,比較例１〜６ マグナリウム50重量部および酸化剤として過塩素酸アン
モニウム30重量部、バインダーとしてポリブタジェン
（CTPB）20重量部を用い、硼素を第１表に示す粒径およ
び配合量として配合し、外径80mm、内径40mm、長さ140m
mに成形し、その外周に合成ゴムシートのレストリクタ
を施し、実施例１〜６および比較例２〜６のガス発生剤
試料を作製した。また硼素を添加しないこと以外は、同
様にしてガス発生剤試料を作製し、比較例１の試料とし
た。これらの試料につき第１図に示す実験装置を用い比
推力を測定した。Examples 1 to 6 and Comparative Examples 1 to 6 Using 50 parts by weight of magnarium, 30 parts by weight of ammonium perchlorate as an oxidizing agent, and 20 parts by weight of polybutadiene (CTPB) as a binder, boron was used in a particle size and composition shown in Table 1. Blended as a quantity, outer diameter 80mm, inner diameter 40mm, length 140m
The gas generating agent samples of Examples 1 to 6 and Comparative Examples 2 to 6 were produced by molding the material into m and applying a synthetic rubber sheet restrictor on the outer periphery thereof. A gas generant sample was prepared in the same manner as in Comparative Example 1 except that boron was not added. The specific thrust of these samples was measured using the experimental apparatus shown in FIG.
第１図に示す実験装置各部の名称を以下に示す。The names of each part of the experimental apparatus shown in FIG. 1 are shown below.
1;1次燃焼室 2;ガス発生器 3;2次燃焼室 2;同筒体 5;レストリクタ 6;ガス発生剤 7;イグナイタ 8;空気取入口 9;外筒 10;プレナムチャンバ 11;支柱 12;架台 13;コロ 14;ロードセル 15;空気ボンベ 16;バルブ 17;ストップバルブ 18;フィルタ 19;バルブ、20;流量計 21;電動ボールバルブ 22;バルブ 23;空気加熱器 24;レギュレータ ＰＧ;1次燃焼室圧力計 ＰＳ;2次燃焼室圧力計 前記の実験装置を用いて比推力をロードセル14により測
定した。測定結果は第１表に示す通りであり、平均粒径
が0.3ミクロン以下であり、かつ配合量が１〜５重量％
の範囲内にある場合に限って高い比推力が得られること
が明らかである。なお、この表は１次燃焼室の燃焼圧を
30kgf/cm2、２次燃焼室の燃焼圧を約6.5kgf/cm2にそれ
ぞれ設定し、温度約250℃、流量約2.6kg/sの空気を流入
してガス発生剤を燃焼した時の燃焼性能の実験結果であ
る。1; Primary combustion chamber 2; Gas generator 3; Secondary combustion chamber 2; Same cylinder 5; Restrictor 6; Gas generator 7; Igniter 8; Air intake 9; Outer cylinder 10; Plenum chamber 11; Strut 12 ; cradle 13; roller 14; the load cell 15; air cylinder 16; valve 17; stop valve 18; filter 19; valve 20; flowmeter 21; electric ball valve 22; valve 23; the air heater 24; regulator P G; 1 next combustion chamber pressure gauge P S; specific impulse with secondary combustion chamber pressure gauge the experimental apparatus were measured by the load cell 14. The measurement results are shown in Table 1, the average particle size is 0.3 micron or less, and the compounding amount is 1 to 5% by weight.
It is clear that a high specific impulse can be obtained only when it is within the range. This table shows the combustion pressure in the primary combustion chamber.
30 kgf / cm 2, a secondary combustion chamber of the combustion pressure is set to about 6.5 kgf / cm 2, respectively, a temperature of about 250 ° C., a flow rate of about 2.6 kg / s of air inflow to the combustion when the combustion of the gas generating agent It is an experimental result of performance.
第１図は実施例および比較例においてガス発生剤の比推
力を測定するのに用いた装置の配置図である。 １……１次燃焼室、２……ガス発生器 ３……２次燃焼室、４……同筒体 ５……レストリクタ、６……ガス発生剤 ７……イグナイタ、８……空気取入口 ９……外筒、10……プレナムチャンバ 11……支柱、14……ロードセル 15……空気ボンベ、18……フィルタ 20……流量計、21……電動ボールバルブ 23……空気加熱器、24……レギュレータFIG. 1 is a layout drawing of an apparatus used for measuring the specific thrust of a gas generating agent in Examples and Comparative Examples. 1 ... Primary combustion chamber, 2 ... Gas generator 3 ... Secondary combustion chamber, 4 ... Same cylinder 5 ... Restrictor, 6 ... Gas generating agent 7 ... Igniter, 8 ... Air intake 9 ... Outer cylinder, 10 ... Plenum chamber 11 ... Struts, 14 ... Load cell 15 ... Air cylinder, 18 ... Filter 20 ... Flow meter, 21 ... Electric ball valve 23 ... Air heater, 24 ……regulator
Claims (1)
体ラムロケット用のガス発生剤において、平均粒径が0.
3ミクロン以下の硼素粉末を１〜５重量％配合したこと
を特徴とするガス発生剤。1. A gas generating agent for a solid ram rocket containing magnalium as a metal fuel, having an average particle size of 0.
A gas generating agent comprising 1 to 5% by weight of boron powder having a particle size of 3 microns or less.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1581388A JPH0751470B2 (en) | 1988-01-28 | 1988-01-28 | Gas generating agent |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1581388A JPH0751470B2 (en) | 1988-01-28 | 1988-01-28 | Gas generating agent |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH01192787A JPH01192787A (en) | 1989-08-02 |
| JPH0751470B2 true JPH0751470B2 (en) | 1995-06-05 |
Family
ID=11899285
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1581388A Expired - Lifetime JPH0751470B2 (en) | 1988-01-28 | 1988-01-28 | Gas generating agent |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0751470B2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5834680A (en) * | 1995-09-22 | 1998-11-10 | Cordant Technologies Inc. | Black body decoy flare compositions for thrusted applications and methods of use |
| JP2012180259A (en) * | 2010-03-19 | 2012-09-20 | Toyoda Gosei Co Ltd | Heat-generating composition and method for manufacturing the same |
-
1988
- 1988-01-28 JP JP1581388A patent/JPH0751470B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH01192787A (en) | 1989-08-02 |
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