JPH0660078B2 - Gas generating agent - Google Patents
Gas generating agentInfo
- Publication number
- JPH0660078B2 JPH0660078B2 JP59246885A JP24688584A JPH0660078B2 JP H0660078 B2 JPH0660078 B2 JP H0660078B2 JP 59246885 A JP59246885 A JP 59246885A JP 24688584 A JP24688584 A JP 24688584A JP H0660078 B2 JPH0660078 B2 JP H0660078B2
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- Japan
- Prior art keywords
- combustion chamber
- generating agent
- gas generating
- gas
- secondary combustion
- Prior art date
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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.
（従来技術） 固体ラムロケットは、通常、１次燃焼室で金属燃料分の
多いガス発生剤を燃焼させて、ガス化し、この生成ガス
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。(Prior Art) A solid ram rocket normally burns a gas generant containing a large amount of metallic fuel in a primary combustion chamber to gasify it, and then guides this generated gas to the secondary combustion chamber and takes it into the secondary combustion chamber. Since it is completely burned by the air, it is possible to obtain a high specific thrust as compared with an ordinary rocket.
しかしながら、この固体ラムロケットでは、１次燃焼室
から２次燃焼室へ供給される生成ガスが、空気によって
冷却されて、完全燃焼せず、そのままノズルから排出さ
れてしまい、所望の性能を得にくいという問題がある。
この問題を解消しようとして、ガス発生剤への酸化剤の
配合量を多くし、２次燃焼室へ供給される生成ガスの温
度を高めることも試みられているが、酸化剤の配合割合
を多くすると、必然的に金属燃料の割合が低下する。そ
の結果、大部分の金属燃料が１次燃焼室で燃焼してしま
い、２次燃焼室へは、燃料が少なく酸化物の多い生成ガ
スが流入し、ラムロケット本来の性能を発揮することが
できなくなってしまう。However, in this solid ram rocket, the produced gas supplied from the primary combustion chamber to the secondary combustion chamber is cooled by air, does not completely burn, and is discharged from the nozzle as it is, so that it is difficult to obtain desired performance. There is a problem.
In order to solve this problem, it has been attempted to increase the compounding amount of the oxidizer in the gas generating agent and raise the temperature of the produced gas supplied to the secondary combustion chamber, but increase the compounding ratio of the oxidizer in many cases. Then, the proportion of metal fuel inevitably decreases. As a result, most of the metallic fuel burns in the primary combustion chamber, and the produced gas with less fuel and a large amount of oxides flows into the secondary combustion chamber, and the original performance of the ram rocket can be exhibited. It's gone.
これらの欠点を補うようにしたガス発生剤として、例え
ば、Journal of Spacecraft ＆ Rocket １９８２年４
月号に示すように、発火温度が比較的低いマグナリウム
や燃焼熱の高いボロンを金属燃料に使用したものが用い
られている。As a gas generating agent for compensating for these drawbacks, for example, Journal of Spacecraft & Rocket 1982 4
As shown in the monthly issue, magnarium, which has a relatively low ignition temperature, and boron, which has a high combustion heat, are used as the metal fuel.
しかしながら、この従来のガス発生剤においても、１次
燃焼室での燃焼圧力をせいぜい30kg・ｆ／cm2程度にし
か設定できないことや、ガス発生剤がもともと酸化剤の
少ない配合になっていることなどから、ボロンの１次燃
焼室での燃焼が不十分で、２次燃焼室で完全燃焼するに
十分な温度にまで加熱されない。又、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が、金属燃料粒
子が比較的大きいこともあって（ボロン粒子の大きさは
１〜３μ、マグナリウム粒子の大きさは10〜20μが限度
で、通常、これより細かい粒子を製造するのは困難）、
その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、生成ガスが２次燃焼室に流入した時、温度が低下
し、空気を付加しても燃焼しなくなってしまう。又、１
次燃焼室で溶融した金属が互いに融着し、これが１次燃
焼室のノズルをチョークするという問題もある。However, even with this conventional gas generating agent, the combustion pressure in the primary combustion chamber can only be set to about 30 kgf / cm 2 at most, and the gas generating agent is originally composed of a small amount of oxidizing agent. Therefore, the combustion of boron in the primary combustion chamber is insufficient and the boron is not heated to a temperature sufficient for complete combustion in the secondary combustion chamber. Further, the energy generated by burning a part of the metal fuel in the primary combustion chamber is relatively large because the metal fuel particles are relatively large (the size of boron particles is 1 to 3 μ, and the size of magnarium particles is 10 μm). ~ 20μ is the limit, it is usually difficult to produce finer particles than this),
The metal fuel particles are consumed due to the temperature rise themselves, and when the produced gas flows into the secondary combustion chamber, the temperature drops, and even if air is added, it will not burn. Again 1
There is also the problem that the molten metals in the secondary combustion chamber fuse together and choke the nozzles of the primary combustion chamber.
（発明の目的） 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
するにある。(Object of the Invention) 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 is the most important in the performance of the solid ram rocket and has an excellent specific thrust. To provide.
（発明の構成） 本発明は、固体ラムロケットの１次燃焼室で燃焼してガ
ス化され２次燃焼室へ導かれ２次燃焼室内に取り入れた
空気によって完全燃焼される固体ラムロケット用のガス
発生剤であって、ボロン、マグナリウム又は両者の混合
物を金属燃料として含有するとともに、酸化剤の含有量
を40％以下とした固体ラムロケット用のガス発生剤にお
いて、平均粒径が０．１ミクロン以下のアルミニウム粉
末を１〜３重量％配合するとともに、前記ボロン、マグ
ナリウム又は両者の混合物からなる金属燃料の含有量を
30〜50重量％としたことを特徴とするガス発生剤であ
る。(Structure of the Invention) The present invention is a gas for a solid ram rocket that is combusted in a primary combustion chamber of a solid ram rocket, gasified, guided to a secondary combustion chamber, and completely combusted by air taken into the secondary combustion chamber. A gas generant for solid ram rockets that contains boron, magnalium, or a mixture of both as a metal fuel and has an oxidizer content of 40% or less. The following aluminum powder is blended in an amount of 1 to 3% by weight, and the content of the metal fuel composed of boron, magnalium or a mixture of the two is adjusted.
It is a gas generating agent characterized by being 30 to 50% by weight.
本発明のガス発生剤は、金属燃料として、ボロン、マグ
ナリウム、又は両者の混合物を含有する。ボロン、マグ
ナリウム、又は両者の混合物の含有量は30〜50重量％、
特に40重量％前後が好適である。The gas generating agent of the present invention contains boron, magnalium, or a mixture of both as a metal fuel. The content of boron, magnarium, or a mixture of both is 30 to 50% by weight,
About 40% by weight is particularly suitable.
更に、本発明においては、平均粒径が０．１ミクロン以
下のアルミニウム粉末を１〜３重量％配合する。アルミ
ニウム粉末の粒径が０．１ミクロンよりも大きくなる
と、１次燃焼室での燃焼効率が低下し、２次燃焼室へ流
入する生成ガス温度を高く保つことができず、本発明の
目的を達成することができない。平均粒径０．１ミクロ
ン以下のアルミニウム粉末は、ガス中蒸発法によって製
造することができる。ガス中蒸発法は、高真空中でアル
ミニウムを気化させ、その極めて稀薄なアルミニウムガ
ス粒子を固化するもので、固化の際にアルミニウム粒子
が会合して、粒子径が大きくなることが抑制され、極め
て微細なアルミニウム粉末が得られる。Further, in the present invention, 1 to 3% by weight of aluminum powder having an average particle size of 0.1 micron or less is blended. If the particle size of the aluminum powder is larger than 0.1 micron, the combustion efficiency in the primary combustion chamber is reduced, and the temperature of the produced gas flowing into the secondary combustion chamber cannot be kept high, which is an object of the present invention. Cannot be achieved. Aluminum powder having an average particle size of 0.1 micron or less can be produced by a gas evaporation method. The in-gas evaporation method vaporizes aluminum in a high vacuum to solidify the extremely dilute aluminum gas particles, and the aluminum particles are prevented from associating during solidification to increase the particle size, A fine aluminum powder is obtained.
アルミニウム粉末の配合量は１〜３重量％であることが
必要である。配合量が１重量％未満では、１次燃焼室で
の燃焼効率が低下し、２次燃焼室へ供給される生成ガス
温度を高く保つことができず、十分満足すべき比推力が
得られない。一方、配合量が３重量％を越えると、それ
にともない高発熱量を有する金属燃料の配合割合が低下
するため、燃料価が低下してしまい不適当である。The blending amount of the aluminum powder needs to be 1 to 3% by weight. If the blending amount is less than 1% by weight, the combustion efficiency in the primary combustion chamber is reduced, the temperature of the produced gas supplied to the secondary combustion chamber cannot be kept high, and a sufficiently satisfactory specific thrust cannot be obtained. . On the other hand, if the blending amount exceeds 3% by weight, the blending ratio of the metal fuel having a high calorific value is reduced accordingly, and the fuel value is lowered, which is not suitable.
更に、本発明のガス発生剤には、１次燃焼室での金属燃
料の燃焼を持続させるための酸化剤、及び、次燃焼室、
アルミニウム粉末、酸化剤などを結合させて一定の形状
で成型するバインダーが配合される。Further, the gas generating agent of the present invention includes an oxidant for maintaining the combustion of the metal fuel in the primary combustion chamber, a secondary combustion chamber,
A binder that mixes aluminum powder, an oxidizer, and the like and is molded into a fixed shape is blended.
酸化剤としては、過塩素酸アンモニウムの中粒品（平均
粒径200 ミクロン）と細粒品（平均粒径10ミクロン）と
を50対50に配合した２成分系のものなどが用いられる。As the oxidizer, a two-component system in which a medium-grain ammonium perchlorate product (average particle size 200 μm) and a fine grain product (average particle size 10 μm) are mixed in a ratio of 50:50 is used.
又、バインダーとしては、末端水酸基化ポリブタジエン
（以下ＨＴＰＢと云う）系バインダーや、末端カルボキ
シル基化ポリブタジエン（以下ＣＴＰＢと云う）系バイ
ンダーなどが用いられる。前者の例として、特開昭５２
−３２９９６号公報に記載されているようなポリジエン
グリコール（日本合成ゴム(株)製Ｋ−31）を主剤とする
ものや米国ＡＲＣＯ社製Ｓ−45ＨＴ、Ｒ−45Ｍを主剤と
するものなどを挙げることができる。後者の例として
は、日本合成ゴム(株)製Ｓ−21を主剤とするものや米国
モートン／サイオコール社製ＨＣ−434 を主剤とするも
のなどがある。バインダー組成の一例を次に示す。As the binder, a terminal hydroxyl group-containing polybutadiene (hereinafter referred to as HTPB) type binder, a terminal carboxyl group-containing polybutadiene (hereinafter referred to as CTPB) type binder, and the like are used. As an example of the former, JP-A-52
Those containing polydiene glycol (K-31 manufactured by Japan Synthetic Rubber Co., Ltd.) as a main component, those containing S-45HT and R-45M manufactured by US ARCO as the main components, and the like. Can be mentioned. Examples of the latter include those using S-21 manufactured by Nippon Synthetic Rubber Co., Ltd. as a main agent, and those using HC-434 manufactured by Morton / Siocor Co., USA as a main agent. An example of the binder composition is shown below.
酸化剤の配合量は、通常30〜50重量％、バインダーの配
合量は、20重量％前後が普通である。 The amount of the oxidizing agent is usually 30 to 50% by weight, and the amount of the binder is usually about 20% by weight.
（発明の作用・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
特性が変化すると云われている。アルミニウムの場合、
通常の融点は約700 ℃近辺にあるが、平均粒径が０．１
ミクロン以下の粉末になると、摩擦熱（約300 ℃前後）
程度で表面が溶けるようになる。アルミニウムは、この
溶融面近傍で発火燃焼するから、極めて低温で発火する
ことになる。このように、平均粒径０．１ミクロン以下
のアルミニウム粉末は発火温度が低く、熱を加えると瞬
間的に発火燃焼する。１次燃焼室でアルミニウム粉末を
発火燃焼させると、その際発生する燃焼熱によって、ボ
ロン、マグナリウム、あるいは両者の混合物からなる金
属燃料が効率よく燃焼し、高温の生成ガスを２次燃焼室
へ供給することができる。その結果、高発熱量を有する
金属燃料の配合割合を好適な範囲に設定しつつ、その金
属燃料を２次燃焼室内で完全燃焼させることができ、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を奏し得る。(Operation and Effect of the Invention) Generally, it is said that the physicochemical properties of metal particles change as the particle size decreases. For aluminum,
Usually the melting point is around 700 ℃, but the average particle size is 0.1
Friction heat (around 300 ℃) when the powder becomes less than micron
The surface will melt in a certain degree. Aluminum ignites and burns in the vicinity of this melting surface, and therefore ignites at an extremely low temperature. In this way, the aluminum powder having an average particle size of 0.1 micron or less has a low ignition temperature, and when heat is applied, it is instantly ignited and burned. When aluminum powder is ignited and burnt in the primary combustion chamber, the combustion heat generated at that time efficiently burns the metallic fuel consisting of boron, magnalium, or a mixture of both, and supplies the high-temperature generated gas to the secondary combustion chamber. can do. As a result, it is possible to completely burn the metallic fuel having a high calorific value in the secondary combustion chamber while setting the blending ratio of the metallic fuel to an appropriate range, thereby increasing the specific thrust of the ram rocket and improving its performance. The effect of being able to be made can be produced.
（実施例） 以下、実施例により本発明を更に詳細に説明する。尚、
比推力とは、推進剤（ガス発生剤）が毎秒、単位重量当
り出し得る推力の大きさのことであり、推力（kg・ｆ）
×燃焼時間（sec）／推進剤重量（kg）で表される。本
実施例における比推力は、第１図に示した実験装置によ
り測定した。(Examples) Hereinafter, the present invention will be described in more detail with reference to Examples. still,
Specific thrust is the amount of thrust that a propellant (gas generating agent) can output per unit weight per second. Thrust (kgf)
× Combustion time (sec) / propellant weight (kg) The specific thrust in this example was measured by the experimental apparatus shown in FIG.
この実験装置は、第１図に示すように１次燃焼室１を有
するガス発生器２と、このガス発生器２の先端が固定さ
れ、２次燃焼室３を有する円筒体４と、を備えている。
ガス発生器２はその内部に本発明に係る管状のガス発生
剤６を有し、ガス発生剤６は１次燃焼室１内にその先端
が突出するよう取付けられたイグナイタ７により着火す
るようになされている。ガス発生器２に近い円筒体４の
円周部には等間隔に空気取入口８が４個取付けられ、こ
の空気取入口８を囲むよう外筒９が固定されてプレナム
チャンバ10を形成している。ガス発生器２と円筒体４は
支柱11、11′により架台12に支持され、架台12はガス発
生器２と円筒体４の軸方向に移動できるようコロ13、1
3′を有する。架台12の前方の壁面にはロードセル14が
固定されガス発生剤２の燃焼中における架台12の移動荷
重を測定している。ＰＧ、Ｐｓはそれぞれ１次燃焼室１
および２次燃焼室３の燃焼圧を測定する圧力計である。This experimental apparatus includes a gas generator 2 having a primary combustion chamber 1 as shown in FIG. 1, and a cylindrical body 4 having a secondary combustion chamber 3 to which the tip of the gas generator 2 is fixed. ing.
The gas generator 2 has a tubular gas generant 6 according to the present invention therein, and the gas generant 6 is ignited by an igniter 7 mounted in the primary combustion chamber 1 so that its tip projects. Has been done. Four air intakes 8 are attached to the circumference of the cylindrical body 4 near the gas generator 2 at equal intervals, and an outer cylinder 9 is fixed so as to surround the air intakes 8 to form a plenum chamber 10. There is. The gas generator 2 and the cylindrical body 4 are supported by a pedestal 12 by struts 11 and 11 ', and the pedestal 12 is arranged so that it can move in the axial direction of the gas generator 2 and the cylindrical body 4.
Has 3 '. A load cell 14 is fixed to the front wall surface of the gantry 12 to measure the moving load of the gantry 12 during the combustion of the gas generating agent 2. P G and Ps are the primary combustion chamber 1 respectively
And a pressure gauge for measuring the combustion pressure in the secondary combustion chamber 3.
プレナムチャンバ10にはラムロケットの飛翔中と同一条
件で一定圧力および一定温度の空気が以下の空路を通っ
て送り込まれる。Air having a constant pressure and a constant temperature is sent to the plenum chamber 10 under the same conditions as when the ram rocket is flying through the following air passages.
すなわち、空気ボンベ15、15′には約150 kg／cm2の加
圧空気が充填されており、この加圧空気はバルブ16、1
6′、ストップバルブ17、フィルタ18、バルブ19、流量
計20、電動ボールバルブ21、バルブ22、22′および空気
加熱器23を通ってプレナムチャンバ10に送り込まれる。
この際、圧力調整レギュレータ24により約10kg／cm2に
減圧され、空気加熱器23によって加熱された一定圧力お
よび一定温度の空気がプレナムチャンバ10内に送られ
る。なお、電動ボール弁21は実験開始時に開口され、バ
ルブ22、22′は開閉によって空気加熱器23を通る空気と
通らない空気の量を調節している。That is, the air cylinders 15 and 15 'are filled with about 150 kg / cm 2 of pressurized air.
6 ', a stop valve 17, a filter 18, a valve 19, a flow meter 20, an electric ball valve 21, valves 22, 22' and an air heater 23 are fed into the plenum chamber 10.
At this time, the pressure of the pressure regulator 24 is reduced to about 10 kg / cm 2 , and the air having a constant pressure and a constant temperature heated by the air heater 23 is sent into the plenum chamber 10. The electric ball valve 21 is opened at the start of the experiment, and the valves 22 and 22 'are opened and closed to adjust the amount of air passing through the air heater 23 and the amount of air passing through the air heater 23.
ガス発生剤は、外径80mm、内径40mm、長さ140 mmに成型
され、その外周に合成ゴムシートのリストリクターを施
したものが実験に供された。又、本実施例におけるガス
発生剤の酸化剤としては、前述の過塩素酸アンモニウム
２成分系を、バインダーとしては、同じく先に例示した
組成の日本合成ゴム(株)製ＨＴＰＢ Ｋ−31系のものを
用いた。The gas generating agent was molded into an outer diameter of 80 mm, an inner diameter of 40 mm, and a length of 140 mm, and a synthetic rubber sheet restrictor was applied to the outer periphery of the gas generating agent for use in the experiment. In addition, as the oxidizing agent for the gas generating agent in this example, the above-mentioned two-component ammonium perchlorate system was used, and as the binder, the HTPB K-31 system manufactured by Japan Synthetic Rubber Co., Ltd. having the same composition as described above was used. I used one.
ガス発生剤の組成及びアルミニウム粉末の平均粒径を次
表に示すように種々変更したサンプルを作成し、前述の
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。測定結果は次表に示す通りであり、アルミニウム粉
末の平均粒径が０．１ミクロン以下であり、かつその配
合量が１〜３重量％の範囲内にある場合（NO.13、26）
に限って比推力が大幅に高まることがわかる。なお、こ
の表は１次燃焼室の燃焼圧を約30kg・ｆ／cm2、２次燃
焼室の燃焼圧を約6.5 kg・ｆ／cm2に、空気ガス発生剤
流量比を約２０にそれぞれ設定し、また２次燃焼室内に
流入する空気量、および２次燃焼室ノズルスロート径を
変化させて燃料した時の燃焼性能である。Samples were prepared in which the composition of the gas generating agent and the average particle diameter of the aluminum powder were variously changed as shown in the following table, and the specific thrust was measured by the load cell 14 using the above-mentioned experimental apparatus. The measurement results are as shown in the following table, when the average particle size of the aluminum powder is 0.1 micron or less and the compounding amount is within the range of 1 to 3% by weight (NO. 13, 26).
It can be seen that the specific thrust is significantly increased only for. This table shows that the combustion pressure in the primary combustion chamber is approximately 30 kg · f / cm 2 , the combustion pressure in the secondary combustion chamber is approximately 6.5 kg · f / cm 2 , and the air gas generant flow rate ratio is approximately 20. It is the combustion performance when the fuel is set by changing the amount of air flowing into the secondary combustion chamber and the diameter of the secondary combustion chamber nozzle throat.
尚、Ａはバインダー（％）、Ｂは酸化剤（％）、Ｃはボ
ロン（％）、Ｄはマグナリウム（％）、Ｅはアルミニウ
ム（％）、Ｆはアルミニウム平均粒径（μ）、Ｇは１次
燃焼圧（kg・ｆ／cm2）、Ｈは２次燃焼室圧（kg・ｆ／c
m2）、Ｉは空気ガス発生剤剤流量比、Ｊは比推力
（秒）、Ｋはアップ率を表わし、良否の判定はＫ＝1.00
を基準にして判定した。 In addition, A is a binder (%), B is an oxidizer (%), C is boron (%), D is magnarium (%), E is aluminum (%), F is an aluminum average particle size (μ), and G is the primary combustion pressure (kg · f / cm 2) , H is the secondary combustion chamber pressure (kg · f / c
m 2 ), I is the flow rate ratio of the air gas generating agent, J is the specific thrust (seconds), K is the up ratio, and K is 1.00.
It was judged based on.
図面は、ガス発生剤の比推力を測定するための実験装置
の概略図である。The drawing is a schematic diagram of an experimental apparatus for measuring the specific thrust of a gas generating agent.
───────────────────────────────────────────────────── フロントページの続き (56)参考文献 特開 昭55−62880（ＪＰ，Ａ) 特開 昭58−64297（ＪＰ，Ａ) 特開 昭59−92992（ＪＰ，Ａ) ─────────────────────────────────────────────────── ─── Continuation of front page (56) Reference JP-A-55-62880 (JP, A) JP-A-58-64297 (JP, A) JP-A-59-92992 (JP, A)
Claims (1)
ガス化され２次燃焼室へ導かれ２次燃焼室内に取り入れ
た空気によって完全燃焼される固体ラムロケット用のガ
ス発生剤であって、 ボロン、マグナリウム又は両者の混合物を金属燃料とし
て含有するとともに、酸化剤の含有量を40％以下とした
固体ラムロケット用のガス発生剤において、 平均粒径が０．１ミクロン以下のアルミニウム粉末を１
〜３重量％配合するとともに、 前記ボロン、マグナリウム又は両者の混合物からなる金
属燃料の含有量を30〜50重量％と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 which is combusted in a primary combustion chamber of a solid ram rocket, gasified, guided to a secondary combustion chamber, and completely combusted by air taken into the secondary combustion chamber. A gas generating agent for a solid ram rocket containing boron, magnalium or a mixture of both as a metal fuel and an oxidizer content of 40% or less, and an aluminum powder having an average particle size of 0.1 micron or less. 1
A gas generating agent, characterized in that the content of the metallic fuel comprising boron, magnalium or a mixture of both is set to 30 to 50% by weight, in addition to 3 to 3% by weight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP59246885A JPH0660078B2 (en) | 1984-11-20 | 1984-11-20 | Gas generating agent |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP59246885A JPH0660078B2 (en) | 1984-11-20 | 1984-11-20 | Gas generating agent |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS61127692A JPS61127692A (en) | 1986-06-14 |
| JPH0660078B2 true JPH0660078B2 (en) | 1994-08-10 |
Family
ID=17155189
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP59246885A Expired - Lifetime JPH0660078B2 (en) | 1984-11-20 | 1984-11-20 | Gas generating agent |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0660078B2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9224145B1 (en) | 2006-08-30 | 2015-12-29 | Qurio Holdings, Inc. | Venue based digital rights using capture device with digital watermarking capability |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2189618B1 (en) * | 2001-01-26 | 2004-09-16 | Universidad Carlos Iii Madrid | BORO BASE FUELS OBTAINED BY DUST TECHNOLOGY, FOR REACTORS AND ENGINES CIVIL AND MLITAR ROCKET CHARACTER. |
| JP5041467B2 (en) * | 2007-01-11 | 2012-10-03 | 防衛省技術研究本部長 | Composite propellant |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5562880A (en) * | 1978-11-06 | 1980-05-12 | Nissan Motor | Composite type gas generating agent |
| JPS5864297A (en) * | 1981-10-09 | 1983-04-16 | 日産自動車株式会社 | Composite propellant |
| JPS6012317B2 (en) * | 1982-11-15 | 1985-04-01 | 防衛庁技術研究本部長 | Solid propellant type high performance ram rocket fuel |
-
1984
- 1984-11-20 JP JP59246885A patent/JPH0660078B2/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9224145B1 (en) | 2006-08-30 | 2015-12-29 | Qurio Holdings, Inc. | Venue based digital rights using capture device with digital watermarking capability |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS61127692A (en) | 1986-06-14 |
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