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公开(公告)号：KR1020140098454A
公开(公告)日：2014-08-08
申请号：KR1020130011119
申请日：2013-01-31
Applicant: 한국항공우주연구원
Abstract: Introduced in the present invention is a ground-based combustion testing system of a rocket engine, capable of conducting starting properties of an engine by performing a combustion test of an engine without a delamination inside a nozzle. The ground-based combustion testing system of a rocket engine includes a thrust wall which acts as a base for measuring the thrust of a rocket engine; a rocket engine having a main nozzle; a rocket engine control-measurement unit positioned between the thrust wall and the rocket engine to conduct the combustion test of the rocket engine; and an auxiliary nozzle unit installed along the bordering portions of the rocket engine main nozzle, while including a plurality of auxiliary rocket engines having respective auxiliary nozzles.
Abstract translation: 在本发明中引入的是一种火箭发动机的基于地面的燃烧测试系统，其能够通过在喷嘴内进行发动机的分层而进行发动机的燃烧试验来进行发动机的起动性能。 火箭发动机的基于地面的燃烧测试系统包括作为用于测量火箭发动机的推力的基座的推力壁; 具有主喷嘴的火箭发动机; 位于推力壁和火箭发动机之间的火箭发动机控制测量单元，用于进行火箭发动机的燃烧试验; 以及沿着火箭发动机主喷嘴的边界部分安装的辅助喷嘴单元，同时包括具有相应辅助喷嘴的多个辅助火箭发动机。
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公开(公告)号：KR1020140096558A
公开(公告)日：2014-08-06
申请号：KR1020130009248
申请日：2013-01-28
Applicant: 한국항공우주연구원
CPC classification number: F16L53/00 , F16L27/11 , F16L51/025 , F16L51/028
Abstract: The present invention relates to a bellows type, high temperature and high pressure flexible pipe unit having a cooling passage. The bellows type flexible pipe unit having a cooling passage, which cools a hot fluid by mixing the hot fluid flowing inside the bellows pipe with the cooling fluid, comprises at least one inlet hole perforated from the outside to the inside in one end and the other end of a bellows pipe respectively; and a cooling fluid supply unit, which makes a cooling fluid flow from the outside of the bellows pipe to the inside of the bellows pipe through the inlet hole. The bellows type flexible pipe unit prevents the temperature of the bellows pipe from increasing to the temperature of the fluid flowing inside the bellows pipe, thereby preventing the bellows pipe from being structurally vulnerable due to the dramatically lowered yield stress of the bellows pipe. Also, a straight pipe is installed inside the bellows pipe, so a groove formed inside the bellows pipe can be prevented from being contaminated by foreign materials as a fluid flows inside. In addition, due to the straight pipe, the cooling passage can maintain smooth flow of the fluid.
Abstract translation: 本发明涉及具有冷却通道的波纹管式，高温高压柔性管单元。 波纹管型柔性管单元具有冷却通道，其通过将在波纹管内流动的热流体与冷却流体混合来冷却热流体，包括至少一个从一端到另一端穿孔的入口孔，另一端 分别为波纹管末端; 以及冷却流体供给单元，其使冷却流体从波纹管的外部通过入口孔流到波纹管的内部。 波纹管式柔性管单元可以防止波纹管的温度升高到波纹管内流体的温度，从而防止波纹管在波纹管的屈服应力显着降低的情况下结构脆弱。 此外，在波纹管内部安装有直管，因此当流体流入内部时，可以防止在波纹管内形成的槽被异物污染。 此外，由于直管，冷却通道可以保持流体的平稳流动。
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公开(公告)号：KR1020140057777A
公开(公告)日：2014-05-14
申请号：KR1020120123951
申请日：2012-11-05
Applicant: 한국항공우주연구원
Abstract: The present invention relates to a high temperature and pressure air generator and, more specifically, to a high temperature and pressure air generator simply and conveniently generating high temperature and pressure air. The high temperature and pressure air generator comprises: a head plate having a path through which liquid oxygen (LOx) and fuel are introduced; an spraying unit which is coupled to the head plate and mixes and sprays the introduced liquid oxygen and fuel; a head unit which is coupled with the spraying unit and the head plate and fixes and supports the spraying unit and the head plate; a chamber unit which is coupled to the head part and which discharges high temperature and pressure air mixed of combustion gas and liquid nitrogen (LN2) after combusting the liquid oxygen and fuel sprayed from the spraying unit; and an introducing hole which is provided on side of the chamber unit and is a passage through which the liquid nitrogen is introduced into the chamber unit. The chamber unit includes: a combustion zone which is a space for generating combustion gas by combusting the liquid oxygen and fuel; and a mixing zone which is a space in which the combustion gas generated in the combustion zone and the liquid nitrogen are mixed.
Abstract translation: 本发明涉及一种高温高压空气发生器，更具体地说，涉及高温高压空气发生器，简单地且方便地产生高温和高压的空气。 高温高压空气发生器包括：头板，其具有通过液体氧（LOx）和燃料引入的路径; 喷射单元，其联接到头板并混合并喷射引入的液氧和燃料; 头单元，其与喷射单元和头板联接，并固定和支撑喷射单元和头板; 连接到头部并在燃烧液体氧气和从喷射单元喷射的燃料之后排出燃烧气体和液氮（LN2）混合的高温和高压空气的室单元; 以及引导孔，其设置在所述室单元的侧面，并且是将液氮引入所述室单元的通道。 室单元包括：燃烧区，其是通过燃烧液体氧和燃料而产生燃烧气体的空间; 以及混合区，其是在燃烧区中产生的燃烧气体和液氮混合的空间。
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公开(公告)号：KR1020110132670A
公开(公告)日：2011-12-09
申请号：KR1020100052125
申请日：2010-06-03
Applicant: 한국항공우주연구원
IPC: F16L23/032 , F16L23/02 , F16L23/16 , F16L23/18
CPC classification number: F16L23/0283 , F16L23/032 , F16L23/20 , F16L25/12
Abstract: PURPOSE: A pipe joint structure using a sphere zone-shaped flange is provided to increase the freedom of pipe connection by assembling flanges even if the flanges are not horizontal state. CONSTITUTION: A pipe joint structure using a sphere zone-shaped flange comprises first and second pipes(10,20), a bolt(30) and a contact unit. The first and second pipes have first and second flanges(11,21) upon each one end. The second flange of the second pipe is combined with the first flange of the first pipe. The bolt connects the first and second flanges and couples the first and second pipes. The first and second flanges are combined in the contact unit. The sphere zone-shaped protruded portion(12) of the first flange and the sphere zone-shaped recessed portion(22) of the second flange are each other combined and the contact unit is formed. The sphere zone-shaped protruded portion corresponds to the sphere zone-shaped recessed portion.
Abstract translation: 目的：提供一种使用球形区域法兰的管接头结构，即使法兰不是水平状态，也可通过组装法兰来增加管道连接的自由度。 构成：使用球形区域形凸缘的管接头结构包括第一和第二管道（10,20），螺栓（30）和接触单元。 第一和第二管在每一端上具有第一和第二凸缘（11,21）。 第二管的第二凸缘与第一管的第一凸缘组合。 螺栓连接第一和第二法兰并连接第一和第二管道。 第一和第二凸缘组合在接触单元中。 第一凸缘的球形区域形突出部分（12）和第二凸缘的球形区域形凹部（22）彼此组合，形成接触单元。 球形区域形突出部分对应于球形区域形凹部。
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公开(公告)号：KR1020030049797A
公开(公告)日：2003-06-25
申请号：KR1020010080114
申请日：2001-12-17
Applicant: 한국항공우주연구원
IPC: F02K9/96
Abstract: PURPOSE: Structure for testing the combustion stability of a rocket engine is provided to reduce the trials and errors accompanied with the development of an engine and to perform the combustion stability test many times in a single combustion test by efficiently inducing a pressure wave induction unit. CONSTITUTION: A pulse gun(20) has an explosion part consisting of a primer and an electricity supply unit. In a pulse gun cavity, main charge is stored. The front position is connected with a connecting bolt(2) and closed with a membrane(1). A pressure wave induction device(30) has a pulse gun pressure wave inlet portion formed in a pulse gun adapter(13) connected with the pulse gun. A nitrogen purging adapter and an engine adapter are installed in an induction cavity formed in the pressure wave induction device.
Abstract translation: 目的：提供用于测试火箭发动机燃烧稳定性的结构，以减少随发动机发展的试验和误差，并通过有效地引导压力波感应装置在单次燃烧试验中进行多次燃烧稳定性试验。 构成：脉冲枪（20）具有由底漆和电力供应单元组成的爆炸部分。 在脉冲枪腔中存储主要电荷。 前部位置与连接螺栓（2）连接并用膜（1）封闭。 压力波感应装置（30）具有形成在与脉冲枪连接的脉冲枪适配器（13）中的脉冲枪压力波入口部分。 氮气吹扫适配器和发动机适配器安装在形成在压力波感应装置中的感应腔中。
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Patent Agency Ranking
公开(公告)号：KR100614631B1
公开(公告)日：2006-08-21
申请号：KR1020030088182
申请日：2003-12-05
Applicant: 한국항공우주연구원
Abstract: 본 발명은, 로켓 연소기 노즐냉각장치에 관한 것이다.
특히, 내측으로 챔버가 형성되는 원통형의 헤드부에 중공상의 몸체부가 고정결합되고 상기 몸체부를 일측에서 지지하는 지지부로 이루어지는 하우징과, 상기 헤드부의 챔버 내측으로 고정 결합되고, 내측으로 직경이 축소후 확대되는 노즐구가 형성되며 그 외주연으로 냉각수가 유동토록 원반형홈이 형성되는 노즐과, 상기 원반형홈에 소정간격 유지하며 끼워지는 한쌍의 인서트 슬랏를 포함하는 구성으로 이루어 진다.
이에따라, 로켓 엔진 연소기에서 고온의 가스와 접하게 되는 노즐을 높은 열로 부터 보호하기 위해 냉각수의 순환에 의해 효과적인 냉각이 이루어지고, 연소압을 안정하게 유지함으로서 노즐의 재사용을 가능토록 하여 시험에 소요되는 시간과 경비를 절감할 수 있도록 하는 것이다.
노즐, 연소기, 로켓-
公开(公告)号：KR1020040045726A
公开(公告)日：2004-06-02
申请号：KR1020020073575
申请日：2002-11-25
Applicant: 한국항공우주연구원
IPC: F02K9/62
Abstract: PURPOSE: Heat resisting structure of a mixer for a rocket engine is provided to prevent the outlet from melting by heat by shielding heat from the combustion chamber with coating the outlet of the mixer with the heat shielding layer. CONSTITUTION: A rocket engine comprises a mixer injecting and mixing fuel and the oxidizing agent to the outlet combined with plural injectors, and a combustor combined with the rear end of the mixer to burn fuel and the oxidizing agent. The outlet is coated by a heat shielding layer(30) to restrict heat from being transmitted to the outlet in burning fuel and the oxidizing agent. The heat shielding layer includes a heat resisting material(32) including the zirconia compound, and an adhesive comprising the nickel compound to stick the heat resisting material to the outlet. The heat resisting material is 230-350 micrometers in thickness for shielding heat and bonding, and the adhesive is 80 -200 micrometers in thickness.
Abstract translation: 目的：提供用于火箭发动机的混合器的耐热结构，以通过用混合器的出口与隔热层一起涂覆来自燃烧室的热量来防止出口熔化。 构成：火箭发动机包括将燃料和氧化剂注入并混合到与多个喷射器组合的出口的混合器，以及与混合器的后端结合以燃烧燃料和氧化剂的燃烧器。 出口由隔热层（30）涂覆以限制在燃烧燃料和氧化剂中的热量被传递到出口。 隔热层包括包含氧化锆化合物的耐热材料（32）和包含镍化合物以将耐热材料粘贴到出口的粘合剂。 耐热材料的厚度为230-350微米，用于屏蔽热和粘合，并且粘合剂的厚度为80-200微米。
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公开(公告)号：KR1020040045715A
公开(公告)日：2004-06-02
申请号：KR1020020073564
申请日：2002-11-25
Applicant: 한국항공우주연구원
IPC: F02K9/62
Abstract: PURPOSE: A rocket engine is provided to cut down manufacturing cost, and to increase the productivity by gaining materials easily and processing conveniently with forming the desired shape of the baffle by pressing at high temperature in winding the heat resisting material made of glass fiber on the metal frame. CONSTITUTION: A rocket engine comprises a mixer(10) injecting compound by mixing fuel with an oxidizer; a combustion chamber forming the space for burning fuel and the oxidizer in the rear part of the mixer; and plural baffles(52,54) installed in the rear part of the mixer to divide the part of the combustion chamber for completely burning fuel and the oxidizer from the mixer. The baffle is manufactured by winding a heat resisting material on a frame to prevent transfer of heat from the combustion chamber to the mixer. The heat resisting material is formed by weaving glass fiber, and the textile is pressed at high temperature.
Abstract translation: 目的：提供一种火箭发动机，以降低制造成本，并通过轻松获得材料并通过在高温下压制形成所需形状的挡板而提高生产率，将玻璃纤维制成的耐热材料卷绕在 金属框架。 构成：火箭发动机包括通过将燃料与氧化剂混合来注入化合物的混合器（10）; 燃烧室，形成用于燃烧燃料的空间和混合器后部的氧化剂; 和多个挡板（52,54），其安装在混合器的后部，以分隔燃烧室的一部分以将燃料和氧化剂从混合器中完全燃烧。 挡板是通过将耐热材料卷绕在框架上来制造的，以防止热量从燃烧室传递到混合器。 耐热材料通过编织玻璃纤维形成，纺织品在高温下被压制。
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公开(公告)号：KR100424792B1
公开(公告)日：2004-03-30
申请号：KR1020010080114
申请日：2001-12-17
Applicant: 한국항공우주연구원
IPC: F02K9/96
Abstract: PURPOSE: Structure for testing the combustion stability of a rocket engine is provided to reduce the trials and errors accompanied with the development of an engine and to perform the combustion stability test many times in a single combustion test by efficiently inducing a pressure wave induction unit. CONSTITUTION: A pulse gun(20) has an explosion part consisting of a primer and an electricity supply unit. In a pulse gun cavity, main charge is stored. The front position is connected with a connecting bolt(2) and closed with a membrane(1). A pressure wave induction device(30) has a pulse gun pressure wave inlet portion formed in a pulse gun adapter(13) connected with the pulse gun. A nitrogen purging adapter and an engine adapter are installed in an induction cavity formed in the pressure wave induction device.
Abstract translation: 目的：提供用于测试火箭发动机的燃烧稳定性的结构，以减少伴随发动机开发的试验和错误，并通过有效地诱导压力波感应单元在单次燃烧测试中多次执行燃烧稳定性测试。 构成：脉冲枪（20）具有由底漆和电源单元组成的爆炸部件。 在脉冲枪腔中存储主要电荷。 前部位置连接一个连接螺栓（2）并用薄膜（1）封闭。 压力波感应装置（30）具有形成在与脉冲枪连接的脉冲枪适配器（13）中的脉冲枪压力波入口部分。 氮气净化适配器和发动机适配器安装在压力波感应装置中形成的感应腔中。
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公开(公告)号：KR101181420B1
公开(公告)日：2012-09-19
申请号：KR1020100052125
申请日：2010-06-03
Applicant: 한국항공우주연구원
IPC: F16L23/032 , F16L23/02 , F16L23/16 , F16L23/18
Abstract: 본 발명은 구띠형 플랜지를 이용한 배관 이음 구조에 관한 것으로, 더욱 상세하게는 분리가 가능하도록 설계된 배관의 연결에 사용되면서, 연결되는 배관의 중심축이 일치하지 않고 소정 각도 회전이 가능하도록 플랜지 접촉부를 볼록한 구띠부 및 오목한 구띠부로 형성되도록 하고, 상기 접촉부에는 이에 적합한 실링부재가 구비된 구띠형 플랜지를 이용한 배관 이음 구조에 관한 것으로, 일단에 제1플랜지를 구비한 제1배관과, 일단에 상기 제1배관의 제1플랜지와 결합되는 제2플랜지를 구비한 제2배관 및 상기 제1플랜지와 상기 제2플랜지를 상호 연결하여 상기 제1배관과 상기 제2배관을 결합하는 볼트를 포함하여 구성되는 배관의 이음 구조에 관한 것으로, 상기 제1플랜지 및 상기 제2플랜지가 결합되는 접촉부는, 상기 제1플랜지의 볼록한 구띠부와, 상기 제1플랜지의 볼록한 구띠부에 상응하는 상기 제2플랜지의 오목한 구띠부가 상호 결합되어 형성된 것을 특징으로 하는 구띠형 플랜지를 이용한 배관 이음 구조를 제공한다.
나아가, 상기 제1,2플랜지 사이에 설치되어 상기 제1,2배관의 접촉부로 유체의 누출을 방지하는 링 형상의 실링부재가 더 구비되는 것을 특징으로 하며, 상기 실링부재는 본 발명에 적합하도록 하단이 상기 실링홀에 거치되고 상단은 상기 제2플랜지의 오목한 구띠부에 거치되는 수직지지링 및 상기 수직지지링의 상부에 좌우로 구비되는 하나는 상기 실링홀에 거치되고 다른 하나는 상기 제2플랜지의 오목한 구띠부에 거치되는 제1,2날개링을 포함하여 구성되는 것을 특징으로 한다.
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