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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：KR1020040045717A
公开(公告)日：2004-06-02
申请号：KR1020020073566
申请日：2002-11-25
Applicant: 한국항공우주연구원
IPC: B65H54/06
CPC classification number: B65H54/06 , B65H54/28 , B65H54/553 , B65H55/04
Abstract: PURPOSE: A filament is wound in a helical way, and attached to a product tightly to have an enough strength and to reduce used filament. CONSTITUTION: A rotation shaft(51) supports both sides of a product(60) to wind a filament(50). Hemispherical vices are attached to both sides of the product, and are connected to the rotation shaft. A filament supplying device(52) is provided to supply the filament moving shaft direction of the product. The filament supplying device is positioned adjacent to the product, and moves to the position of the hemispherical vices.
Abstract translation: 目的：丝线以螺旋方式缠绕，并紧紧地附着在产品上以具有足够的强度并减少使用过的细丝。 构成：旋转轴（51）支撑产品（60）的两侧以卷绕细丝（50）。 半球形附件连接到产品的两侧，并连接到旋转轴。 提供灯丝供给装置（52）以供应产品的灯丝移动轴方向。 灯丝供应装置定位成与产品相邻，并且移动到半球状的位置。
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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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Patent Agency Ranking
公开(公告)号：KR1020120075944A
公开(公告)日：2012-07-09
申请号：KR1020100137866
申请日：2010-12-29
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A gas-gas injector for a small rocket engine using the ignition characteristics of kerosene contacting with hydrogen peroxide is provided to omit atomizing and evaporating processes by supplying the gaseous kerosene to a combustion chamber. CONSTITUTION: A gas-gas injector for a small rocket engine using the ignition characteristics of kerosene contacting with hydrogen peroxide supplies the hydrogen peroxide in a gas-gas state to a combustion chamber of the rocket engine by evaporating the kerosene and decomposing the hydrogen peroxide. A gas-gas injector for the small rocket engine comprises a catalyst unit(10), and a vaporizing pipe(20). The catalyst unit decomposes the hydrogen peroxide with gas for decomposing the hydrogen peroxide. The vaporizing pipe is installed inside the catalyst unit, and evaporates the kerosene.
Abstract translation: 目的：提供使用与过氧化氢接触的煤油点火特性的小型火箭发动机的气体 - 气体注入器，以通过将气态煤油供应到燃烧室来省略雾化和蒸发过程。 构成：使用与过氧化氢接触的煤油的点燃特性的小型火箭发动机的气体气体喷射器通过蒸发煤油并分解过氧化氢将气体状态的过氧化氢供应到火箭发动机的燃烧室。 用于小火箭发动机的气体 - 气体喷射器包括催化剂单元（10）和蒸发管（20）。 催化剂单元用分解过氧化氢的气体分解过氧化氢。 蒸发管安装在催化剂单元内部，蒸发煤油。
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公开(公告)号：KR1020110071232A
公开(公告)日：2011-06-29
申请号：KR1020090127739
申请日：2009-12-21
Applicant: 한국항공우주연구원
CPC classification number: B01D53/005 , B01D2259/4575 , C01B21/16
Abstract: PURPOSE: A decomposition gas processing unit for a hydrazine thruster using a reheating process is provided to transform harmful hydrazine decomposition gas after purifying into non-toxic gas. CONSTITUTION: A decomposition gas processing unit for a hydrazine thruster comprises the following: a vacuum chamber(140); a low temperature nitrogen supply line(120) discharging hydrazine decomposition gas inside the vacuum chamber by supplying low temperature nitrogen gas; a decomposition gas supply line connected to one end of the vacuum chamber; a reheating chamber(170) connected to the decomposition gas supply line for reheating the hydrazine decomposition gas and discharging to the atmosphere; and a heater(150) located on the lower side of the vacuum chamber.
Abstract translation: 目的：提供一种使用再加热方法的肼推进器的分解气处理装置，用于将有害的肼分解气体净化后转化成无毒气体。 构成：用于肼推进器的分解气体处理单元包括：真空室（140）; 低温氮气供应管线（120），通过供应低温氮气排出真空室内的肼分解气体; 连接到真空室的一端的分解气体供给管线; 连接到分解气体供应管线的再加热室（170），用于再加热肼分解气体并排放到大气中; 以及位于真空室的下侧的加热器（150）。
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公开(公告)号：KR1020090068721A
公开(公告)日：2009-06-29
申请号：KR1020070136449
申请日：2007-12-24
Applicant: 한국항공우주연구원
Abstract: A liquid level measuring device for a tank is provided to recover scattered liquid into a tank without flowing back into a differential pressure measuring pipe, thereby obtaining a precise liquid level in the tank. A liquid level measuring device for a tank includes a tank(10), a differential pressure measuring pipe(20), a differential pressure sensor(30), and a reservoir(40). The tank stores liquid(11) inside and discharges the liquid. The differential pressure measuring pipe connects the upper and lower parts of the tank to each other. The differential pressure sensor is connected to the differential pressure measuring pipe at the connection position between the differential pressure measuring pipe and the tank. The reservoir is connected to the differential pressure measuring pipe at an upper part of the tank and has an internal space for introducing the liquid scattered in the tank.
Abstract translation: 提供一种用于罐的液面测量装置，用于将分散的液体回收到罐中而不流回到差压测量管中，从而在罐中获得精确的液位。 一种用于罐的液位测量装置，包括一个罐（10），一个差压测量管（20），一个差压传感器（30）和一个储存器（40）。 储罐内存储液体（11）并排出液体。 差压测量管将罐的上部和下部彼此连接。 差压传感器与压差测量管连接在差压测量管和油箱之间的连接位置。 储存器连接到罐的上部的差压测量管，并且具有用于引入散布在罐中的液体的内部空间。
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公开(公告)号：KR100513929B1
公开(公告)日：2005-09-08
申请号：KR1020030071388
申请日：2003-10-14
Applicant: 한국항공우주연구원
IPC: F16K3/28
Abstract: 본 발명은 발사체 로켓의 극저온 환경에 사용될 게이트 밸브 형태의 자동밸브에 관한 것으로, 더욱 상세하게는 벨로우즈를 이용하여 극저온 환경에서도 밸브의 개폐가 확실하며 밸브 구동용 헬륨의 누설이 없고 밸브 구동용 헬륨의 요구 양이 적게 소모되고 밸브의 차압이 거의 없는 벨로우즈를 이용한 게이트형 극저온 밸브에 관한 것이다.
이러한 본 발명은 헬륨가스 입출구(2)에 연결되며 상측에 설치되는 밸브 제어 유체부 벨로우즈(5)와,
상기 밸브 제어 유체부 벨로우즈(5)의 하측으로 중앙에 유로부(7)가 형성된 상측구동부(4)와 하측구동부(8)로 이루어진 밸브구동부(20)와,
상기 하측구동부(8)의 하측에 스프링(9)을 설치하여 유로부(7)를 자동으로 차단하도록 함을 특징으로 하는 것이다.-
公开(公告)号：KR1020040034783A
公开(公告)日：2004-04-29
申请号：KR1020020063383
申请日：2002-10-17
Applicant: 한국항공우주연구원
IPC: F02K9/97
Abstract: PURPOSE: A throat plug of a rocket engine for sealing and safekeeping is provided to execute air-tightness text without a nozzle expansion part whose structural rigidity is weak relatively to a combustion chamber part. CONSTITUTION: A throat plug comprises a support installation part(A) with a single shaft(1) fixing supports(4) to an upper side of a neck of a nozzle of a nozzle wall; and an airtight plate installation part(B) having an air tight plate(8) fixed to the neck of the nozzle to keep air-tightness. The shaft has a head part(2) installed on an upper side of the shaft, and having blades(2') protruded on an upper side thereof in three directions; and a screw part(1') formed on a lower side thereof so that a supporting plate connecting body(6) and an airtight plate fixing handle(9) are coupled thereto and rotated to move up and down. Support lever(3) are protruded from the blades of the head part, and connected to the blades by first hinges(3'), and have the supports formed with arc-shaped soft material, or having soft material fixed on front ends thereof, and connected to front ends of the support lever.
Abstract translation: 目的：提供一种用于密封和保管的火箭发动机的喉塞，以执行气密性文本，而没有相对于燃烧室部分的结构刚度较弱的喷嘴扩张部分。 构成：喉塞包括支撑安装部分（A），单个轴（1）将支撑件（4）固定到喷嘴壁的喷嘴的颈部的上侧; 以及气密板安装部（B），其具有固定在喷嘴颈部的气密板（8），以保持气密性。 所述轴具有安装在所述轴的上侧的头部（2），并且具有在三个方向上在其上侧突出的叶片（2'）; 以及形成在其下侧的螺纹部分（1'），使得支撑板连接体（6）和气密板固定手柄（9）联接到其上并旋转以上下移动。 支撑杆（3）从头部的刀片突出，并通过第一铰链（3'）连接到刀片，并且具有形成有弧形软质材料的支撑件或固定在前端上的软质材料， 并连接到支撑杆的前端。
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