JPS609998B2 - propellant composition - Google Patents
propellant compositionInfo
- Publication number
- JPS609998B2 JPS609998B2 JP7537182A JP7537182A JPS609998B2 JP S609998 B2 JPS609998 B2 JP S609998B2 JP 7537182 A JP7537182 A JP 7537182A JP 7537182 A JP7537182 A JP 7537182A JP S609998 B2 JPS609998 B2 JP S609998B2
- Authority
- JP
- Japan
- Prior art keywords
- propellant
- combustion
- lead
- weight
- pressure
- 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
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B25/00—Compositions containing a nitrated organic compound
- C06B25/18—Compositions containing a nitrated organic compound the compound being nitrocellulose present as 10% or more by weight of the total composition
- C06B25/24—Compositions containing a nitrated organic compound the compound being nitrocellulose present as 10% or more by weight of the total composition with nitroglycerine
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
- C06B23/007—Ballistic modifiers, burning rate catalysts, burning rate depressing agents, e.g. for gas generating
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Health & Medical Sciences (AREA)
- Emergency Medicine (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
- Catalysts (AREA)
- Heterocyclic Carbon Compounds Containing A Hetero Ring Having Oxygen Or Sulfur (AREA)
Description
【発明の詳細な説明】
本発明は圧力指数を低下させた推進薬組成物に関し、特
に圧力指数を低下させた高比推力型の推進薬組成物に関
する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a propellant composition with a reduced pressure index, and particularly to a high specific impulse type propellant composition with a reduced pressure index.
従来から無煙性が要求されるロケット推進薬の分野では
、ニトロセルロース（以下ＮＣと称す）とニトログリセ
リン（以下ＮＧと称す）とを主成分とするダブルベース
推進薬（以下ＤＢ推進薬と称す）が用いられてきた。In the field of rocket propellants, which traditionally require smokeless properties, double-base propellants (hereinafter referred to as DB propellants) whose main components are nitrocellulose (hereinafter referred to as NC) and nitroglycerin (hereinafter referred to as NG) are used. has been used.
近年、要求性能の高度化に伴い、高比推力型の推進薬、
即ち前記主成分に更に過塩素酸アンモニウム（以下ＡＰ
と称す）やシクロトリメチレントリニトラミン（以下Ｒ
ＤＸと称す）等の酸化剤やアルミニウム等の金属粉を主
として含有させたコンポジットモデフアィドダブルベー
ス推進薬（以下ＣＭＤＢ推進薬と称す）が開発され、更
にＤＢ椎進薬あるいはＣＭＤ母推進薬に燃料兼結合剤を
含有させたコンポジツトダブルベース推進薬（以下ＣＤ
Ｂ推進薬と称す）が開発された。In recent years, as the required performance has become more sophisticated, high specific impulse propellants,
That is, ammonium perchlorate (hereinafter referred to as AP) is added to the main component.
) and cyclotrimethylenetrinitramine (hereinafter referred to as R
Composite modified double base propellants (hereinafter referred to as CMDB propellants), which mainly contain oxidizing agents such as DX (referred to as DX) and metal powders such as aluminum, have been developed. Composite double base propellant (CD) contains fuel and binder.
B propellant) was developed.
これら推進薬の燃焼速度と燃焼圧力との関係は、一般に
次式で表わされることが知られている。It is known that the relationship between the combustion speed and combustion pressure of these propellants is generally expressed by the following equation.
・ｒ＝ａｐｎ
（ここでｒは燃料速度を、ｐは燃焼圧力を、ｎは０圧力
指数を、ａは個々の推進薬における定数を示す）ロケッ
ト推進薬においては、一般にロケットモータの設計や燃
料安定性の面から前記圧力指数ｎは小さいことが望まし
く、特にｎニｏの場合をプタラトー燃焼特性と、またｎ
＜０の場合をメサ燃焼特性と呼び、これらは共に好まし
い特性である。・r=apn (where r is the fuel velocity, p is the combustion pressure, n is the 0 pressure index, and a is the constant for each propellant) Regarding rocket propellants, it generally depends on the rocket motor design and the fuel From the viewpoint of stability, it is desirable that the pressure index n is small, and in particular, in the case of n, the pressure index n is
The case where <0 is called mesa combustion characteristics, and both of these characteristics are desirable characteristics.
このような特性を与える燃料触媒として前記ＤＢ推進薬
においては、サリチル酸鉛やステアリン酸鉛等の有機鉛
塩、酸化鉛及び金属鉛を単独０で、若しくは前記の鉛化
合物や金属鉛とサリチル酸銅やステアリン酸鋼等の有機
鋼塩、酸化鋼等の銅化合物や金属鋼等との混合物系で用
いることが知られている（特公昭４９−４９２８号公報
）。このような公知の燃焼触媒は、ＮＣ含有量が多５く
かつ比較的ェネルギ発生量の少ないＤＢ推進薬において
前記の好ましい特性を与える。しかしながらＮＧ含有量
が多いＤＢ推進薬や、前記ＣＭＤＢ椎進薬やＣＤＢ推進
楽のような高比推力型の推進薬においては、前記公知の
燃焼触媒は圧力指数ｎを低下させる効果がないか又は非
常に少なかった。近年、このような高比推力型の推進薬
においても有効に作用して圧力指数ｎを大幅に低下させ
うる燃料触媒が強く求められるようになってきたことか
ら、本発明者等は鋭意研究した結果、特定の有機鋼塩及
び有機鉛塩若しくは無機鉛からなる新規な燃料触媒が前
記要求に合致することを見し、出し本発明を完成した。
Ｚ則ち、本発明は、少なくと
もＮＣとＮＧとを含有する推進薬組成物において、燃料
触媒として安息香酸銅及び有機鉛塩若しくは無機鉛を含
有してなることを特徴とする推進薬組成物である。本発
明に用いられる燃料触媒のうち、有機鉛塩Ｚとしては、
サリチル酸鉛、ステアリン酸鉛、レゾルシン酸鉛、２エ
チルヘキシル酸鉛等を例示することができ、又無機鉛と
してはスズ酸鉛、酸化鉛、金属鉛等を例示することがで
きる。In the DB propellant, as a fuel catalyst that provides such characteristics, organic lead salts such as lead salicylate and lead stearate, lead oxide, and metallic lead are used singly or in combination with the above-mentioned lead compounds or metallic lead and copper salicylate. It is known to be used in a mixture system with organic steel salts such as stearic acid steel, copper compounds such as oxidized steel, metallic steel, etc. (Japanese Patent Publication No. 49-4928). Such known combustion catalysts provide the aforementioned favorable properties in DB propellants with high NC content and relatively low energy production. However, in DB propellants with a high NG content and high specific impulse type propellants such as the CMDB Shishinyaku and CDB Juryaku, the above-mentioned known combustion catalysts are either ineffective in reducing the pressure index n or There were very few. In recent years, there has been a strong demand for fuel catalysts that can act effectively even in such high specific impulse type propellants and can significantly reduce the pressure index n, so the present inventors have conducted extensive research. As a result, we found that a new fuel catalyst consisting of a specific organic steel salt and organic lead salt or inorganic lead met the above requirements, and completed the present invention.
Z: That is, the present invention is a propellant composition containing at least NC and NG, which is characterized by containing copper benzoate and an organic lead salt or an inorganic lead as a fuel catalyst. be. Among the fuel catalysts used in the present invention, organic lead salts Z include:
Examples include lead salicylate, lead stearate, lead resorucinate, lead 2-ethylhexylate, and examples of inorganic lead include lead stannate, lead oxide, and metallic lead.
これらの有機鉛塩及び無機鉛は１種又は２種以上を安息
香２酸鋼と組合わせて用いる。本発明に用いる燃焼触媒
の合計量は、推進薬組成物全量の０．５乃至５重量％が
好ましく「そのうち安息香酸銅の量が推進薬全量の０．
２乃至４重量％であることが好ましい。One or more of these organic lead salts and inorganic lead salts are used in combination with benzoate steel. The total amount of the combustion catalyst used in the present invention is preferably 0.5 to 5% by weight based on the total amount of the propellant composition.
Preferably, it is 2 to 4% by weight.
安息香酸銅の量が０．２２重量％未満でかつ有機鉛塩若
しくは無機鉛の量が０．立重量％未満では圧力指数を大
幅に低下させることができないので好ましくなく、又安
息香酸銅の量が４重量％を越え燃料触媒の合計量が５重
量％を越えるとエネルギー的に不活性な燃料触媒が３増
加することになる結果、比推力の低下を招くことになる
ので好ましくない。本発明においては、ＮＣ及びＮＧ成
分以外にも必要に応じてジェチルフタレート、ジオクチ
ルフタレート、トリブチルフオスフエート、トリアセチ
３ン、ジオクチルアジベート、ジオクチルセバケート等
の可塑剤や、ＲＤＸ、シクロテトラメチレンテトラニト
ラミン（ＨＭＫ）、ＡＰ、過塩素酸カリ等の酸化剤や、
アルミニウム等の金属粉や「ジフェニルァミソ等の安定
剤や、末端ィソシァネート生のポリエステル等の燃料兼
結合剤や、豚化剤等を合有することができる。The amount of copper benzoate is less than 0.22% by weight and the amount of organic lead salt or inorganic lead is 0.22% by weight. If the amount of copper benzoate exceeds 4% by weight and the total amount of fuel catalyst exceeds 5% by weight, the fuel becomes energetically inert. This is not preferable because the number of catalysts increases by 3, which leads to a decrease in specific impulse. In the present invention, in addition to the NC and NG components, plasticizers such as diethyl phthalate, dioctyl phthalate, tributyl phosphate, triacetin, dioctyl adibate, dioctyl sebacate, RDX, cyclotetramethylene, etc. Oxidizing agents such as tetranitramine (HMK), AP, potassium perchlorate,
Metal powder such as aluminum, a stabilizer such as diphenylamiso, a fuel/binder such as polyester containing terminal isocyanate, a swinizing agent, etc. can be combined.
これらの各成分の配合組成は、通常比推力等の燃焼性能
、機械的物性、安全性、製造性及び老化特性等を考慮し
て決めることが出来る。The composition of each of these components can be determined by taking into account combustion performance such as specific impulse, mechanical properties, safety, manufacturability, aging characteristics, etc.
例えば高比推力型のＤ凶推進薬の場合は、ＮＣが２５乃
至５０重量％、ＮＧが４０乃至６５重量％、可塑性及び
腰化剤が３乃至１５重量％及び安定剤が０．３乃至５重
量％であり、ＣＭＤ母推進薬の場合は、前記成分全量に
対し外割でＡＰを０乃至４の重量％、ＲＤＸやＨＭＫ等
のニトラミン類を０乃至６の重量％、アルミニウムを０
乃至３の重量％単独又は混合系で添加した組成等であり
、ＣＤＢ推進薬の場合は、更に前記可塑剤及び腰化剤の
量のうち０．３乃至１０重量％を燃料兼結合剤とした組
成等であって、いずれも本発明において特定される燃焼
触媒を０．５乃至５重量％含有した配合組成を例示する
ことができる。本発明の推進薬組成物は、例えば次のよ
うな方法で製造することができる。まずＮＧと可塑剤と
燃焼触媒とを減圧下で混和し「必要ならば酸化剤や金属
粉を添加して混和を続け更に必要ならば燃料兼結合剤を
加えて混和し、次いで安定剤と微粒子状のＮＣを添加し
て減圧下で混和する、混和後、混和物であるスラリーを
減圧下で注型し、加温下でキュアしてＤＢ推進薬、ＣＭ
Ｄ母推進薬又はＣＤ母推進薬を得る。For example, in the case of a high specific impulse type D propellant, NC is 25 to 50% by weight, NG is 40 to 65% by weight, plasticizer and stiffening agent is 3 to 15% by weight, and stabilizer is 0.3 to 5% by weight. %, and in the case of a CMD parent propellant, AP is 0 to 4% by weight, nitramines such as RDX and HMK are 0 to 6% by weight, and aluminum is 0% by weight, based on the total amount of components.
In the case of CDB propellants, 0.3 to 10% by weight of the plasticizer and stiffening agent is added as a fuel and binder. etc., all of which contain 0.5 to 5% by weight of the combustion catalyst specified in the present invention. The propellant composition of the present invention can be produced, for example, by the following method. First, NG, plasticizer, and combustion catalyst are mixed under reduced pressure, and if necessary, oxidizing agent and metal powder are added and mixing is continued.Furthermore, if necessary, fuel/binder is added and mixed, and then stabilizer and fine particles are mixed. After mixing, the slurry of the mixture is poured under reduced pressure and cured under heating to form DB propellant and CM.
Obtain D mother propellant or CD mother propellant.
次に実施例によって本発明を説明する。なお表中の％表
示は重量基準である。実施例 １
第１表に示す実施例１の配合組成物（ＯＢ推進薬）を以
下のようにして製造した。Next, the present invention will be explained by examples. Note that the percentages in the table are based on weight. Example 1 The formulation composition (OB propellant) of Example 1 shown in Table 1 was manufactured as follows.
ＮＧ３２００のこジヱチルフタレート（ＤＥＰ）８００
夕を加えて燈拝し混和機に入れた。NG3200 Diethyl Phthalate (DEP) 800
Add the evening water to the mixture and put it in the mixing machine.
次いで平均粒径が１０ムの以下のサリチル酸鉛（Ｐｂ−
Ｓａ）２００夕と平均粒径が１０仏の以下の安息香酸銅
（Ｃｕ−Ｂｅ）１００夕とを加えて３０ｏｏで２０分間
減圧で混和を行なった。混和後２ーニトロジフェニルア
ミン（２一ＮＤＰＡ）２００夕を加え、更に微粒子状の
ＮＣ５５００夕を加え４０ｏｏで４び分間減圧下で混和
した。混和後、スラリーを減圧下で注型し、５０００で
１０日間かけて豚化させＤＢ推進薬を得た。この推進薬
からストランド試料を５５本作製し次の方法でストラン
ド試験を行なった。即ち、クロフオード型ストランド装
置を用い、窒素ガス雰囲気下で圧力３０ｋ９・ｆ／のか
ら１０ｋｇ・ｆ′の刻みで１３０ｋｇ・ｆ′のまで各点
５本づつ燃焼させてその燃焼速度を求めた。結果を第１
図の実線で示す。Next, lead salicylate (Pb-
200 g of copper benzoate (Cu-Be) having an average particle size of 10 mm or less were added and mixed under reduced pressure at 30 mm for 20 minutes. After mixing, 200 g of 2-nitrodiphenylamine (2-NDPA) was added, and further finely divided NC5500 was added, and the mixture was mixed under reduced pressure at 400 g for 4 minutes. After mixing, the slurry was cast under reduced pressure and swinized at 5,000 yen for 10 days to obtain a DB propellant. Fifty-five strand samples were prepared from this propellant and a strand test was conducted using the following method. That is, five strands were burned at each point from a pressure of 30 k9·f/ to a pressure of 130 kg·f' in steps of 10 kg·f' in a nitrogen gas atmosphere using a Crochet type strand apparatus, and the combustion speed was determined. Results first
Shown by the solid line in the figure.
なお第１図におし、て縦軸は燃焼速度（ｒ、側／ｓｅｃ
）の対数を、横軸は燃焼圧力（Ｐ、ｋ９・ｆ／の）の対
数を示す。第１図は各燃焼圧力における平均燃焼速度を
プロットした燃焼圧力〜燃焼速度関係図である。比較例
１
安息香酸銅に変えサリチル酸鋼を用いた以外は実施例１
に準じてＤＢ推進薬を製造した。In Figure 1, the vertical axis is the combustion rate (r, side/sec
), and the horizontal axis shows the logarithm of the combustion pressure (P, k9·f/). FIG. 1 is a diagram showing the relationship between combustion pressure and combustion speed, in which the average combustion speed at each combustion pressure is plotted. Comparative Example 1 Example 1 except that salicylic acid steel was used instead of copper benzoate
DB propellant was manufactured according to the method.
この推進薬を用いて実施例１と同じ試験を行ない得られ
た結果を第１図の破線で示す。実施例 ２
ＺＮＣとＮＧの量を第１表の
実施例２に示す比率に変えた以外は実施例１に準じて高
比推力型のＤＢ推進薬を製造した（なお第１表中の比推
力はＮＡＳＡの特徴数計算プログラムを用いて計算した
値あり、燃焼圧力８０ｋ９・ｆ／のにおける値である）
。The same test as in Example 1 was conducted using this propellant, and the results obtained are shown by the broken line in FIG. Example 2
A high specific impulse type DB propellant was manufactured according to Example 1 except that the amounts of ZNC and NG were changed to the ratio shown in Example 2 in Table 1 (the specific impulse in Table 1 is based on NASA's There is a value calculated using a feature number calculation program, and the value is at a combustion pressure of 80k9・f/)
.
Ｚ得られた推進薬を用いて実施例１と同じ試験を行なっ
た。結果を第２図の実線で示す。比較例 ２
安息香酸銅に変えたサリチル酸鋼を用いた以外は実施例
２に準じて高比推力型のＤＢ推進薬を製造した。The same test as in Example 1 was conducted using the propellant obtained. The results are shown by the solid line in FIG. Comparative Example 2 A high specific impulse type DB propellant was manufactured according to Example 2 except that salicylic acid steel was used instead of copper benzoate.
得られた推進薬を用いて実施例１と同じ試験を行なった
。結果を第２図の破線で示す。実施例 ３サリチル酸鉛
を酸化鉛（Ｐの）に変えた以外は実施例１に準じて第１
表に示される実施例３の配合組成物の高比推力型のＤＢ
推進薬を製造した。The same test as in Example 1 was conducted using the obtained propellant. The results are shown by the dashed line in FIG. Example 3 Example 1 was carried out according to Example 1 except that lead salicylate was replaced with lead oxide (P).
High specific impulse type DB of the blended composition of Example 3 shown in the table
Propellant was manufactured.
得られた推進薬を用いて実施例１と同じ試験を行なった
。結果を第３図の実線で示す。比較例 ３
安息香酸銅をサリチル酸鋼に変えた以外は実施例３に準
じて第１表に示される比較例３の配合組成物の高比推力
型のＤＢ推進薬を製造した。The same test as in Example 1 was conducted using the obtained propellant. The results are shown by the solid line in FIG. Comparative Example 3 A high specific impulse type DB propellant having the compounding composition of Comparative Example 3 shown in Table 1 was produced according to Example 3 except that copper benzoate was replaced with salicylic acid steel.
得られた推進薬を用いて実施例１と同じ試験を行なった
。結果を第３図の破線で示す。実施例 ４
第１表に示す実施例４の配合組成物（ＣＭＤＢ椎進薬）
を以下のようにして製造した。The same test as in Example 1 was conducted using the obtained propellant. The results are shown by the dashed line in FIG. Example 4 Compounded composition of Example 4 shown in Table 1 (CMDB Shiishinyaku)
was produced as follows.
ＮＧ３９２０のこＤＥＰ６４０夕を加えて燈拝し混和機
に入れ、次いで平均粒径がｌｏＡｍ以下のサリチル酸鉛
１６Ｍと安息香酸銅８０夕とを加え３０００で２０分間
減圧で混和を行なった。NG3920 powder and DEP640 powder were added, and the mixture was heated and put into a mixer. Next, 16M of lead salicylate and 80M of copper benzoate having an average particle size of less than 10Am were added, and the mixture was mixed under reduced pressure at 3,000 °C for 20 minutes.
混和後ＲＯＸを２０００夕加えて混和してから２一ＮＤ
ＰＡを１６０夕加え、更に微粒子状のＮＣを３０４０夕
加え４０ｑ０で４び分間減圧下で混和した。混和後、ス
ラリーを減圧下で蓬型し、５０００で１０日間かけて豚
化させてＯＭＤＢ推進薬を得た。この推進薬を用いて実
施例１と同じ試‐験を行なった。結果を第４図の実線で
示す。比較例 ４安息香酸銅をサリチル酸鋼に変えた以
外は実施例４‘こ準じてＣＭＤ母推進薬を製造した。After mixing, add ROX for 2,000 minutes, mix, and then add 21 ND.
PA was added for 160 minutes, and finely divided NC was further added for 3,040 minutes and mixed at 40q0 for 4 minutes under reduced pressure. After mixing, the slurry was molded under reduced pressure and molded at 5,000 yen for 10 days to obtain an OMDB propellant. The same test as in Example 1 was conducted using this propellant. The results are shown by the solid line in FIG. Comparative Example 4 A CMD parent propellant was produced in the same manner as in Example 4' except that copper benzoate was replaced with steel salicylate.
得られた推進薬を用いて実施例１と同じ試験を行なった
。結果を第４図の破線で示す。実施例 ５
第１表に示す実施例５の配合組成物（ＣＤＢ推進薬）を
以下のようにして製造した。The same test as in Example 1 was conducted using the obtained propellant. The results are shown by the dashed line in FIG. Example 5 The formulation composition of Example 5 (CDB propellant) shown in Table 1 was manufactured as follows.
ＮＧ６０００のこＤＥＰ４００夕を加えて燈拝し混和機
に入れ、次いで平均粒径がｌｏＡｍ以下のサリチル酸鉛
２００夕と安息香酸銅２００夕とを加え３０ｑｏで２０
分間減圧で混和し、次いで分子量３０００の２官能性の
末端イソシアネートのポリエステル４００夕を加え３０
℃で２０分間混和した後、２一ＮＤＰＡ２００夕及び微
粒子状のＮＣ２６００夕を加え４０℃で４０分間減圧下
で混和した。Add NG6000 and DEP400 and put it in a mixing machine, then add 200 lead salicylate and 200 copper benzoate with an average particle size of less than loAm and mix it with 30 qo.
Mix for 3 minutes under reduced pressure, then add 400 g of difunctional terminal isocyanate polyester having a molecular weight of 3000 and add 300 g of
After mixing at 40°C for 20 minutes, NDPA 200 and fine particulate NC2600 were added and mixed at 40°C for 40 minutes under reduced pressure.
混和後、スラリーを減圧下で洋型し、５０ｑＣで１０日
間かけて腰化（硬化）させＣＯＢ推進薬を得た。この推
進薬を用いて実施例１と同じ試験を行なった。結果を第
５図の実線で示す。比較例 ５安息香酸銅をサリチル酸
鋼に変えた以外は実施例５に準じてＣＤＢ推進薬を製造
した。After mixing, the slurry was molded under reduced pressure and stiffened (hardened) at 50 qC for 10 days to obtain a COB propellant. The same test as in Example 1 was conducted using this propellant. The results are shown by the solid line in FIG. Comparative Example 5 A CDB propellant was produced according to Example 5 except that copper benzoate was replaced with salicylic acid steel.
得られた推進薬を用いて実施例１と同じ試験を行なった
。結果を第５図の破線で示す。第１表
Ｇ注） ＮＣ：ニトロセルロース、ＮＧ：ニトログリセ
リン、ＤＥＰ：ジェチルフタレート、燃料兼結合剤：分
子量３０００の２官能性末端ィソシァネートのポリエス
テル、２−ＮＤＰＡ：２−ニトロジフェニルァミン、Ｒ
ＤＸ：シクロトリメチレントリニトラミン、Ｐｂ−Ｓａ
：サリチル酸鉛、Ｐｂ○：酸化鉛、Ｃｕ【Ｂｅ：安息香
酸銅、Ｃｕ−Ｓａ：サリチル酸銅※比推力は特徴数計算
にょり求めた値
前記式で示されるｎ指数は、燃焼圧力 ｐ と燃焼速度
（ｒ）とを両対数軸にとってプロットした時の傾きで示
されることから各実施例（実線）と比較例（破線）の傾
きを図面でみると以下のことが明らかである。The same test as in Example 1 was conducted using the obtained propellant. The results are shown by the dashed line in FIG. Table 1 G Note) NC: nitrocellulose, NG: nitroglycerin, DEP: jetyl phthalate, fuel/binder: polyester of bifunctional terminal isocyanate with a molecular weight of 3000, 2-NDPA: 2-nitrodiphenylamine, R
DX: cyclotrimethylene trinitramine, Pb-Sa
: Lead salicylate, Pb○: Lead oxide, Cu [Be: Copper benzoate, Cu-Sa: Copper salicylate *Specific impulse is the value obtained by calculating the number of features The n index shown in the above formula is the combustion pressure p and combustion The following is clear when looking at the slopes of each example (solid line) and comparative example (broken line) in the drawings, as shown by the slope when plotting the speed (r) on the logarithmic axis.
まず実施例１〜３（比較例１〜３）はＤＢ推進薬の例で
あって、第１表に示されるように実施例２及び３（比較
例２及び３）は、高比推力型を、実施例１（比較例１）
は、それ程高比推力型でない例を示している。First, Examples 1 to 3 (Comparative Examples 1 to 3) are examples of DB propellants, and as shown in Table 1, Examples 2 and 3 (Comparative Examples 2 and 3) are of high specific impulse type. , Example 1 (Comparative Example 1)
shows an example of a not so high specific impulse type.
第１図において、本発明で特定される燃焼触媒を用いた
実施例１及び公知の燃焼触媒を用いた比較例１とも高圧
部においてメサ燃焼特性を示しているが、その傾きは明
らかに実施例１の方が大であり、かつ、メサ燃焼領域が
広い。In FIG. 1, both Example 1 using the combustion catalyst specified in the present invention and Comparative Example 1 using a known combustion catalyst show mesa combustion characteristics in the high pressure section, but the slope is clearly different from that of Example 1. 1 is larger and has a wider mesa burning area.
又第２図においては、本発明で特定される燃焼触媒を用
いた実施例２は高圧部でメサ燃焼特性を示しているのに
対し、公知の燃焼触媒を用いた比較例２では傾き３の低
下がみられない。又第３図においては、公知の燃焼触媒
を用いた比較例３でも高圧部で傾きが低下しているもの
の、本発明で特定される燃焼触媒を用いた実施例３の方
がその低下が著しく、メサ燃焼特性を示しているし、又
全体的にも比較例３よりも傾きが低くなっている。第４
図は、ＣＭＤ母推進薬の例を示したものであり、公知の
燃焼触媒を用いた比較例４よりも本発明で特定される燃
焼触媒を用いた実施例４の方が高圧部にかけての傾きが
著しく低くほぼプラトー燃焼特性を示している。Further, in FIG. 2, Example 2 using the combustion catalyst specified in the present invention shows mesa combustion characteristics in the high pressure section, whereas Comparative Example 2 using a known combustion catalyst shows a slope of 3. No decrease is seen. Furthermore, in FIG. 3, although the slope of Comparative Example 3 using a known combustion catalyst is also reduced in the high pressure section, the reduction is more remarkable in Example 3 using the combustion catalyst specified by the present invention. , exhibits mesa combustion characteristics, and the overall slope is lower than that of Comparative Example 3. Fourth
The figure shows an example of a CMD mother propellant, and the slope toward the high pressure part is higher in Example 4 using the combustion catalyst specified by the present invention than in Comparative Example 4 using a known combustion catalyst. is extremely low, indicating almost plateau combustion characteristics.
又第５図は、ＣＤＢ推進薬の例を示したものであるが、
公知の燃焼触媒を用いた比較例５よりも本発明で特定さ
れる燃焼触媒を用いた実施例５の方が全体に傾きが低く
ｎ指数が低下していることがわかる。Also, Figure 5 shows an example of CDB propellant.
It can be seen that the slope of Example 5 using the combustion catalyst specified by the present invention is lower overall and the n-index is lower than that of Comparative Example 5 using a known combustion catalyst.
以上の実施例の結果から明らかなように本発明は、特定
の燃焼触媒を用いることによってｎ指数を大幅に低下さ
せた推進薬組成物であって、特に高比推力型の推進薬組
成物において、その効果が顕著である。As is clear from the results of the above examples, the present invention provides a propellant composition in which the n-index is significantly reduced by using a specific combustion catalyst, and particularly in a high specific impulse type propellant composition. , the effect is remarkable.
第１図〜第３図はＤＢ推進薬の燃焼圧力−燃焼速度関係
図であり、第４図及び第５図はＣＭＤＢ推進薬及びＣＤ
Ｂ推進薬の燃焼圧力−燃焼速度関係図である。
各図中実線は実施例を破線は比較例を示す。第１図
第２図
第３図
第４図
第５図Figures 1 to 3 are combustion pressure-burning rate relationship diagrams for DB propellant, and Figures 4 and 5 are for CMDB propellant and CD propellant.
It is a combustion pressure-combustion speed relation diagram of B propellant. In each figure, solid lines indicate examples and broken lines indicate comparative examples. Figure 1 Figure 2 Figure 3 Figure 4 Figure 5
Claims (1)
を含有する推進薬組成物において、安息香酸銅及び有機
鉛塩若しくは無機鉛を含有してなることを特徴とする推
進薬組成物。 ２ 安息香酸銅及び有機鉛塩若しくは無機鉛の合計量が
推進薬組成物全量の０．５乃至５重量％である特許請求
の範囲第１項に記載の推進薬組成物。 ３ 安息香酸銅の量が推進薬組成物全量の０．２乃至４
重量％である特許請求の範囲第２項に記載の推進薬組成
物。[Scope of Claims] 1. A propellant composition containing at least nitrocellulose and nitroglycerin, which further contains copper benzoate and an organic lead salt or an inorganic lead salt. 2. The propellant composition according to claim 1, wherein the total amount of copper benzoate and organic lead salt or inorganic lead is 0.5 to 5% by weight based on the total amount of the propellant composition. 3 The amount of copper benzoate is 0.2 to 4 of the total amount of the propellant composition.
A propellant composition according to claim 2 which is % by weight.
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7537182A JPS609998B2 (en) | 1982-05-07 | 1982-05-07 | propellant composition |
| GB08312345A GB2121399B (en) | 1982-05-07 | 1983-05-05 | Propellant compositions |
| FR8307636A FR2526418B1 (en) | 1982-05-07 | 1983-05-06 | PROPULSIVE COMPOSITION CONTAINING NITROCELLULOSE, NITROGLYCERIN, COPPER BENZOATE AND LEAD OR DERIVATIVES THEREOF, ESPECIALLY FOR ROCKETS |
| DE19833316676 DE3316676A1 (en) | 1982-05-07 | 1983-05-06 | FUEL COMPOSITIONS |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7537182A JPS609998B2 (en) | 1982-05-07 | 1982-05-07 | propellant composition |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS58194790A JPS58194790A (en) | 1983-11-12 |
| JPS609998B2 true JPS609998B2 (en) | 1985-03-14 |
Family
ID=13574281
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7537182A Expired JPS609998B2 (en) | 1982-05-07 | 1982-05-07 | propellant composition |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JPS609998B2 (en) |
| DE (1) | DE3316676A1 (en) |
| FR (1) | FR2526418B1 (en) |
| GB (1) | GB2121399B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2152920B (en) * | 1983-08-12 | 1987-06-24 | Secr Defence | Propellant composition |
| GB8409867D0 (en) * | 1984-04-16 | 1993-06-16 | Ici Plc | Nitrocellulose propellant composition |
| WO1986001796A1 (en) * | 1984-09-11 | 1986-03-27 | The Commonwealth Of Australia Care Of The Secretar | Gun flash suppressants |
| GB2246348B (en) * | 1986-07-15 | 1993-03-03 | Ici Plc | Nitrocellulose propellant composition |
| US6024810A (en) * | 1998-10-06 | 2000-02-15 | Atlantic Research Corporation | Castable double base solid rocket propellant containing ballistic modifier pasted in an inert polymer |
| US8828161B1 (en) * | 2006-01-30 | 2014-09-09 | The United States Of America As Represented By The Secretary Of The Navy | Ballistic modification and solventless double base propellant, and process thereof |
| CN103333036B (en) * | 2013-06-21 | 2016-06-29 | 宜宾北方川安化工有限公司 | A kind of low critical pressure double base propellant |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3138499A (en) * | 1964-06-23 | Pressure | ||
| US3960621A (en) * | 1957-03-12 | 1976-06-01 | Imperial Chemical Industries Limited | Propellents |
| US3954533A (en) * | 1969-10-29 | 1976-05-04 | The United States Of America As Represented By The Secretary Of The Navy | High pressure-burning propellant composition |
| US4000025A (en) * | 1974-05-28 | 1976-12-28 | The United States Of America As Represented By The Secretary Of The Navy | Incorporating ballistic modifiers in slurry cast double base containing compositions |
-
1982
- 1982-05-07 JP JP7537182A patent/JPS609998B2/en not_active Expired
-
1983
- 1983-05-05 GB GB08312345A patent/GB2121399B/en not_active Expired
- 1983-05-06 FR FR8307636A patent/FR2526418B1/en not_active Expired
- 1983-05-06 DE DE19833316676 patent/DE3316676A1/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| DE3316676A1 (en) | 1983-12-08 |
| FR2526418A1 (en) | 1983-11-10 |
| GB2121399A (en) | 1983-12-21 |
| FR2526418B1 (en) | 1986-03-21 |
| GB2121399B (en) | 1985-12-11 |
| DE3316676C2 (en) | 1987-04-02 |
| GB8312345D0 (en) | 1983-06-08 |
| JPS58194790A (en) | 1983-11-12 |
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