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公开(公告)号：KR1020160036286A
公开(公告)日：2016-04-04
申请号：KR1020140128302
申请日：2014-09-25
Applicant: 국방과학연구소
Abstract: 본발명은고반응성금속분말제조방법및 이로부터제조되는금속분말에관한것이다. 본발명에따른고반응성금속분말제조방법은고반응성금속분말제조방법은 Al나노분말, Al마이크로분말및 볼을볼 밀(Ball Mill)의용기내에투입하는투입단계(S100); 상기볼 밀(Ball Mill)의용기를불활성분위기로제어하는분위기제어단계(S200); 상기분위기제어단계(S200) 후볼 밀(Ball Mill)을작동시켜, 상기 Al나노분말이상기 Al마이크로분말의표면에부착된고반응성 Al분말을제조하는제조단계(S300); 및상기제조단계(S300)에서제조된상기고반응성 Al분말의표면에일부산화막을씌우는부동태화(Passivation) 처리단계(S400);를포함한다. 본발명에따르면, 기존의마이크로크기의분말소재와비교하여높은비표면적을가질뿐만아니라, 나노입자의낮은점화온도특성을활용함으로써종래의마이크로분말에비하여반응성이높으면서도적절한부피와무게를동시에확보할수 있으므로, 종래의마이크로분말의폭발력에비하여향상된특성을확보할수 있다.
Abstract translation: 本发明涉及一种制造高反应性金属粉末和由其制造的金属粉末的方法。 根据本发明，制造高反应性金属粉末的方法包括：（S100）将Al微粉末和球引入球磨机容器的内部的引入步骤; （S200）使用惰性气氛来控制球磨机的容器的气氛控制工序; （S300）通过在气氛控制步骤之后致动球磨机，制造具有附着到Al微粉末表面的Al纳米粉末的高反应性Al粉末的制造步骤（S200）; 和（S400）钝化处理步骤，用氧化膜部分地覆盖在制造步骤（S300）中制造的高反应性Al粉末的表面。 根据本发明，可以获得与常规微粉末材料相比较高的比表面积; 此外，与常规微粉相比，与纳米颗粒的低点火温度同时可以获得足够的体积和重量的较高的反应性，从而与常规的微粉爆炸力相比确保改善的性能。
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公开(公告)号：KR101334732B1
公开(公告)日：2013-12-12
申请号：KR1020110020788
申请日：2011-03-09
Applicant: 국방과학연구소
CPC classification number: C06B29/22 , C06B33/14 , C06B45/105
Abstract: 본 발명은 수산기말단 폴리에테르(Hydroxy-terminated polyether: HTPE), N-부틸-N-(2-니트레이토에틸)니트라민(N-butyl-(2-nitratoethyl)nitramine: BuNENA) 및 암모늄퍼클로레이트(ammonium perchlorate: AP)를 포함하는, 충격 및 열 반응에 둔감한 고체 로켓 추진 기관용 고체 추진제 조성물에 관한 것이다.
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公开(公告)号：KR1020130112451A
公开(公告)日：2013-10-14
申请号：KR1020120034842
申请日：2012-04-04
Applicant: 국방과학연구소
Abstract: PURPOSE: An open type Propulsion system for rapid launching an interceptor of an active protection system is provided to perform rapid launching of the interceptor while maintaining stable a trajectory by supplying sufficient energy to a propellant before combustion gas of the propellant is discharged to the outside of a launching pipe. CONSTITUTION: An open type Propulsion system for rapid launching an interceptor of an active protection system comprises a launching pipe, a propellant, an igniter, and a bursting pipe. The igniter comprises an igniter body (41), an ignition cartridge (43), a firing unit (43), and an ignition wire (44). The firing unit is arranged in the igniter body and ignites an ignition agent according to an electric signal. The ignition wire is installed at the rear end of the firing unit towards the inside of the ignition cartridge in the longitudinal direction of the igniter and includes gunpowder with a predetermined combustion speed.
Abstract translation: 目的：提供一种用于快速发射主动防护系统拦截器的开放式推进系统，以便在将推进剂的燃烧气体排放到外部之前向推进剂提供足够的能量，同时保持稳定的轨迹，从而快速启动拦截器 一个发射管。 构成：用于快速发射主动保护系统拦截器的开放式推进系统包括发射管，推进剂，点火器和爆破管。 点火器包括点火器主体（41），点火盒（43），点火单元（43）和点火线（44）。 点火单元布置在点火器体中，并根据电信号点燃点火剂。 点火线沿着点火器的长度方向安装在点火单元的后端，朝向着火盒的内侧，并且包括具有预定燃烧速度的火药。
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公开(公告)号：KR1020120104457A
公开(公告)日：2012-09-21
申请号：KR1020110020788
申请日：2011-03-09
Applicant: 국방과학연구소
CPC classification number: C06B29/22 , C06B33/14 , C06B45/105
Abstract: PURPOSE: An insensitive solid propellant composition is provided to provide a solid propellant composition which dull reaction towards impacts and thermal reactions by including hydroxy-terminated polyether(HTPE), N-butyl-(2-nitratoethyl)nitramine(BuNENA) and ammonium perchlorate(AP). CONSTITUTION: An insensitive solid propellant composition comprises 5-10 wt% of one or more selected from the terminal part of hydroxyl polyether and terminal part of hydroxyl poIycaprolactone ether as a binder, 5-15 wt% of 5-15 wt% of N-butyl-N-(2- nitrato ethyl)nitramine as a plasticizer, 10-70 wt% of ammonium perchlorate as a main oxidizer, 10-30 wt% of ammonium nitrate as a sub-oxidizer, and 1-30 wt% of one selected from Al compound, Zr compound, iron compound and B compound. The insensitive solid propellant composition additionally includes one or more hardeners selected from isophorone diisocyanate and polyfunctional aliphatic isocyanate. The insensitive solid propellant composition additionally includes N-methyl -p- nitroaniline or 2- nitrodiphenylamine.
Abstract translation: 目的：提供一种不敏感的固体推进剂组合物，以提供固体推进剂组合物，其通过包括羟基封端的聚醚（HTPE），N-丁基 - （2-硝基乙基）硝胺（BuNENA）和高氯酸铵（ AP）。 构成：不敏感的固体推进剂组合物包含5-10wt％的一种或多种选自羟基聚醚的末端部分和作为粘合剂的羟基聚己内酯醚的末端部分，5-15wt％的5-15wt％ 丁基-N-（2-硝基乙基）硝胺作为增塑剂，10-70重量％的高氯酸铵作为主要氧化剂，10-30重量％的硝酸铵作为副氧化剂，和1-30重量％的一种 选自Al化合物，Zr化合物，铁化合物和B化合物。 不敏感的固体推进剂组合物另外包括一种或多种选自异佛尔酮二异氰酸酯和多官能脂族异氰酸酯的硬化剂。 不敏感的固体推进剂组合物另外包括N-甲基对硝基苯胺或2-硝基二苯胺。
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公开(公告)号：KR101088750B1
公开(公告)日：2011-12-01
申请号：KR1020100046964
申请日：2010-05-19
Applicant: 국방과학연구소
CPC classification number: G01N31/16
Abstract: 본 발명은 니트라민기와 나이트레이트기를 함유한 지방족 에너지화 가소제 내의 불순물 검출방법에 관한 것으로서, 좀더 상세하게는 특정 조성의 적정 용매를 사용함으로써 분석기간 및 분석비용을 절감할 수 있는 니트라민기와 나이트레이트기를 함유한 지방족 에너지화 가소제 내의 불순물 검출방법에 관한 것이다.
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Patent Agency Ranking
公开(公告)号：KR1020110088652A
公开(公告)日：2011-08-04
申请号：KR1020100008251
申请日：2010-01-29
Applicant: 국방과학연구소
Abstract: PURPOSE: An ignition/delay assembly for a hybrid propulsion shell is provided to easily secure an installation space of a Base Bleed ignition unit and a delay/ignition unit. CONSTITUTION: An ignition/delay assembly for a hybrid propulsion shell comprises a Base Bleed ignition unit(200) and a delay/ignition unit. The BB ignition unit ignites a drag reducing propellant grain. One end of the delay/ignition unit is inserted into the inlet of the BB ignition unit, and the delay/ignition unit ignites a rocket propulsion grain. A rocket igniter body(210), a BB ignition agent(160), a retarder(170), an ignition material(180), and a rocket ignition agent(190) are successively inserted into the delay/ignition unit.
Abstract translation: 目的：提供用于混合动力推进壳的点火/延迟组件，以便轻松固定基础点火单元和延迟/点火单元的安装空间。 构成：用于混合推进壳的点火/延迟组件包括底部点火单元（200）和延迟/点火单元。 BB点火装置点燃减阻推进剂颗粒。 延时/点火单元的一端插入BB点火单元的入口，延迟点火单元点燃火箭推进颗粒。 火焰点火器体（210），BB点火剂（160），延迟器（170），点火材料（180）和火箭点火剂（190）被依次插入延迟点火单元中。
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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：KR1020100042980A
公开(公告)日：2010-04-27
申请号：KR1020080102225
申请日：2008-10-17
Applicant: 국방과학연구소
Abstract: PURPOSE: A screw pipe for a residence time of a combustion gas is provided to steadily secure flame in an initial ignition. CONSTITUTION: A screw pipe for a residence time of a combustion gas comprises a combustion chamber(110), an igniter(120), a jet nozzle(140), and a sealing member(130). A combustion chamber comprises a propellant(111). The igniter is arranged inside the combustion chamber. The igniter ignites the propellant. The get nozzle discharges a propellant gas. The sealing member is arranged in the inner side of the get nozzle. The sealing member releases the constant after making the combustion gas staying inside the combustion chamber for a fixed time.
Abstract translation: 目的：提供燃烧气体停留时间的螺旋管，以便在初始点火时稳定地固定火焰。 构成：用于燃烧气体停留时间的螺旋管包括燃烧室（110），点火器（120），喷嘴（140）和密封构件（130）。 燃烧室包括推进剂（111）。 点火器布置在燃烧室内。 点火器点燃推进剂。 得到喷嘴排出推进剂气体。 密封件布置在吸嘴的内侧。 使燃烧气体在燃烧室内停留一定时间后，密封构件释放恒定。
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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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