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公开(公告)号：KR101664236B1
公开(公告)日：2016-10-10
申请号：KR1020140083297
申请日：2014-07-03
Applicant: 국방과학연구소
Abstract: 본발명은덕티드로켓용추진제에관한것으로, 보다상세하게는중합체에시드된보론입자, 연소시 산소공급이가능한산화제, 금속연료및 성분들에결합력을제공하는바인더를포함하며, 중합체에시드된보론입자를이용하여높은압력지수를갖도록함으로써, 덕티드로켓의가스발생기연소실압력변화에빠른응답성을갖도록하고, 금속연료로나노사이즈의알루미늄을적용하여연료과농고체추진제의연소속도를최대로증진시키는덕티드로켓용추진제에관한것이다.
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公开(公告)号：KR1020090027061A
公开(公告)日：2009-03-16
申请号：KR1020070092239
申请日：2007-09-11
Applicant: 국방과학연구소
IPC: C07D403/04
Abstract: A manufacturing method of 1,1'-dimethyl-5,5'-bitetrazole is provided to shorten a reaction time, to improve yield and to be manufactured inexpensively. A manufacturing method of 1,1'-dimethyl-5,5'-bitetrazole comprises steps of: forming intermediate by reacting N,N'-dimethyl oxamide and acetonitrile in a solvent including acetonitrile; and cyclizing it by adding sodium azide to the intermediate. The first step and the second step are performed at a temperature of 20~30°C and a same reactor.
Abstract translation: 提供1,1'-二甲基-5,5'-四唑的制备方法以缩短反应时间，提高产率并廉价制造。 1,1'-二甲基-5,5'-四唑的制备方法包括以下步骤：通过在包括乙腈的溶剂中使N，N'-二甲基草酰胺和乙腈反应形成中间体; 并通过向中间体中加入叠氮化钠使其环化。 第一步骤和第二步骤在20〜30℃的温度和相同的反应器中进行。
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公开(公告)号：KR1020160004667A
公开(公告)日：2016-01-13
申请号：KR1020140083297
申请日：2014-07-03
Applicant: 국방과학연구소
CPC classification number: C06B27/00 , C06B23/00 , C06B23/001 , C06D5/00
Abstract: 본발명은덕티드로켓용추진제에관한것으로, 보다상세하게는중합체에시드된보론입자, 연소시 산소공급이가능한산화제, 금속연료및 성분들에결합력을제공하는바인더를포함하며, 중합체에시드된보론입자를이용하여높은압력지수를갖도록함으로써, 덕티드로켓의가스발생기연소실압력변화에빠른응답성을갖도록하고, 금속연료로나노사이즈의알루미늄을적용하여연료과농고체추진제의연소속도를최대로증진시키는덕티드로켓용추진제에관한것이다.
Abstract translation: 本发明涉及一种用于管道火箭的推进剂，更具体地说，涉及用于管道火箭的推进剂，其包括：硼粒子接种到聚合物上; 燃烧时能够供氧的氧化剂; 以及向金属燃料和组分提供结合力的粘合剂。 当管道火箭的气体发生器中的燃烧室压力通过使用接种到聚合物上的硼颗粒具有高指数而变化时，用于管道火箭的推进剂具有快速响应，并且通过施加使燃料富含固体推进剂的燃烧速率最大化 纳米尺寸的铝作为金属燃料。
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公开(公告)号：KR101089247B1
公开(公告)日：2011-12-05
申请号：KR1020090058504
申请日：2009-06-29
Applicant: 국방과학연구소
Abstract: 고체 추진제용 경화제가 제공된다. 본 발명에 따른 경화제는 디이소시아네이트기를 갖는 저분자 경화제와 히드록시기로 종결된 프리폴리머를 반응시켜 얻어지는 고분자 경화제이다. 또한, 이러한 고분자 경화제를 함유하는 접착 기능이 강화된 고체 추진제 조성물도 제공된다.
고체 추진제, 경화제, 라이너, 프리폴리머-
Patent Agency Ranking
公开(公告)号：KR1020040092807A
公开(公告)日：2004-11-04
申请号：KR1020030027125
申请日：2003-04-29
Applicant: 국방과학연구소
IPC: C06D5/00
Abstract: PURPOSE: A propellant for a rocket propulsion system is provided to improve tensile deformability of a solid propellant efficiently by relieving concentration of stress around solid filler particles. CONSTITUTION: The propellant for a rocket propulsion system comprises a solid filler formed of primary particles and secondary particles having sizes less than those of primary particles, wherein the content of the primary particles is greater than 80% and less than 100% based on the total weight of the solid filler. Particularly, the ratio of the average diameter of the primary particles to that of the secondary particles ranges from 25 to 85. The primary particles may be formed of at least two groups of particles having different sizes.
Abstract translation: 目的：提供一种用于火箭推进系统的推进剂，通过减轻固体填料颗粒周围的应力集中，有效提高固体推进剂的拉伸变形性。 构成：用于火箭推进系统的推进剂包括由一次颗粒形成的固体填料和具有小于一次颗粒尺寸的二次颗粒，其中一次颗粒的含量基于总颗粒大于80％且小于100％ 固体填料的重量。 特别地，初级颗粒的平均直径与二次颗粒的平均直径的比例为25至85.初级颗粒可以由至少两组具有不同尺寸的颗粒形成。
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公开(公告)号：KR1020110001107A
公开(公告)日：2011-01-06
申请号：KR1020090058504
申请日：2009-06-29
Applicant: 국방과학연구소
CPC classification number: C06B45/00 , C06B23/006 , C06B25/24 , C06B45/10
Abstract: PURPOSE: A curing agent for a solid propellant composition is provided to prevent mass transfer of a low molecular weight hardener by reacting the low molecular weight hardener with a prepolymer. CONSTITUTION: A curing agent for a solid propellant composition is represented by chemical formula(1). A method for manufacturing a polymer hardener comprises a step of performing reaction so that the equivalence ratio of an isocianate functional group of a compound with a diiosocianate group and a hydroxyl group of a hydroxyl-terminated prepolymer is NCO/OH = 1.9-2.1. The solid propellant composition includes prepolymer 2-25 weight%, oxidation stabilizer 0.1-1 weight%, solid filler 40-90 weight%, polymer hardener 3-35 weight% and curing catalyst 0.001-0.2 weight%.
Abstract translation: 目的：提供固体推进剂组合物的固化剂，以通过使低分子量固化剂与预聚物反应来防止低分子量固化剂的传质。 构成：固体推进剂组合物的固化剂由化学式（1）表示。 聚合物硬化剂的制造方法包括进行反应的步骤，使得化合物的异山梨酸酯官能团与二硫代邻苯二甲酸酯基和羟基封端的预聚物的羟基的当量比为NCO / OH = 1.9-2.1。 固体推进剂组合物包括预聚物2-25重量％，氧化稳定剂0.1-1重量％，固体填料40-90重量％，聚合物硬化剂3-35重量％和固化催化剂0.001-0.2重量％。
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公开(公告)号：KR100935893B1
公开(公告)日：2010-01-07
申请号：KR1020070092239
申请日：2007-09-11
Applicant: 국방과학연구소
IPC: C07D403/04
Abstract: 본 발명은 1,1'-다이메틸-5,5'-바이테트라졸(1,1'-dimethyl-5,5'-bitetrazole)을 제조하는 방법에 관한 것으로, 벤젠, 다이클로로메탄과 같은 인체 및 환경에 유해한 용매 대신 유해성이 적은 아세토니트릴을 용매로 사용하는 것을 특징으로 한다.
다이메틸바이테트라졸, 아세토니트릴, 단일 반응기 반응-
公开(公告)号：KR100823575B1
公开(公告)日：2008-04-21
申请号：KR1020070033579
申请日：2007-04-05
Applicant: 국방과학연구소
IPC: B64G1/40
CPC classification number: B64G1/403
Abstract: A propellant assembly for a solid rocket is provided to prevent unnecessary consumption of propellant in case of a launching test of a rocket by controlling the number of propellants and igniters as occasion demands. A propellant assembly for a solid rocket comprises a propellant grain(20), a combustion pipe(18), a connector(17), and an elastic heat resisting diaphragm(15). The propellant grain is formed by sequentially connecting propellant/igniter assemblies(10) having a propellant(11) and an igniter(13). The combustion pipe forms an outer shape of the solid rocket. The propellant grain is installed in the combustion pipe. A nozzle(19) is installed at an end part of the combustion pipe. The connector is attached to a front end of the propellant grain and is coupled with a power supply device. The elastic heat resisting diaphragm is installed between the propellant/igniter assemblies and blocks thermal shock. The propellant/igniter assembly includes the propellant, an inhibitor(12), the igniter, an auxiliary ignition plate(14), the elastic heat resisting diaphragm, and an ignition wire(16). The inhibitor is coated at side surfaces of the propellant and prevents the thermal shock from being transmitted to the side parts. The auxiliary ignition plate is adhered on an upper surface of the inhibitor and amplifies output of the igniter. The ignition wire is installed along side surfaces of the elastic heat resisting diaphragm and the inhibitor and transmits fire signals to the auxiliary ignition plate of the adjacent propellant/igniter assembly.
Abstract translation: 提供用于固体火箭的推进剂组件，用于在通过根据需要控制推进剂和点火器的数量进行火箭发射试验时防止不必要的消耗推进剂。 用于固体火箭的推进剂组件包括推进剂颗粒（20），燃烧管（18），连接器（17）和弹性耐热隔膜（15）。 推进剂颗粒通过依次连接具有推进剂（11）和点火器（13）的推进剂/点火器组件（10）而形成。 燃烧管形成固体火箭的外形。 推进剂颗粒安装在燃烧管中。 喷嘴（19）安装在燃烧管的端部。 连接器连接到推进剂颗粒的前端并与电源装置耦合。 弹性耐热隔膜安装在推进剂/点火器组件之间，阻止热冲击。 推进剂/点火器组件包括推进剂，抑制剂（12），点火器，辅助点火板（14），弹性耐热隔膜和点火线（16）。 抑制剂涂覆在推进剂的侧表面，并防止热冲击传递到侧面部件。 辅助点火板粘附在抑制剂的上表面并放大点火器的输出。 点火线沿着弹性耐热隔膜和阻尼器的侧面安装，并将火灾信号传递到相邻的推进剂/点火器组件的辅助点火板。
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公开(公告)号：KR100551205B1
公开(公告)日：2006-02-10
申请号：KR1020030027125
申请日：2003-04-29
Applicant: 국방과학연구소
IPC: C06D5/00
Abstract: 본 발명은 추진제 그레인에 응력이 많이 작용하는 고체 로켓 추진기관용 고체 추진제에 관한 것으로서, 추진제를 구성하는 고체 충전제는 제1입자들과 상기 제1입자들 보다 크기가 작은 제2입자들로 구성되며, 상기 제1입자들의 함량은 전체 고체 충전제의 80% 이상 100% 미만인 것을 특징으로 하는 로켓추진기관용 추진제를 제공한다. 본 발명에 따르면 고체 추진제가 인장 변형을 받을 때 변형률 감소에 직접적인 영향을 끼치는 충전 입자 주위의 응력 집중을 완화해줄 수 있는 조성물을 제공하며 추진제 변형률 향상에 효과적이다.
고체추진제, 인장응력, 변형률
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