-
公开(公告)号：KR1020100070062A
公开(公告)日：2010-06-25
申请号：KR1020080128653
申请日：2008-12-17
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A high-pressure flexible pipe unit of bellows type having an extension restricting member is provided to prevent the excessive deformation of a bellows pipe by preventing the expansion of the pipe. CONSTITUTION: A high-pressure flexible pipe unit of bellows type having an extension restricting member comprises an expansion limit member(400) and a folding-type clamping member(500). The expansion limit member is installed in each gully(310) of the bellows pipe. The expansion limit member has elasticity, and restricts the expansion of the bellows pipe. The clamping member is installed outside the bellows pipe. The clamping member restricts longitudinal extension of the bellows pipe. The clamping member bends the bellows pipe in the limited range.
Abstract translation: 目的：提供具有延伸限制构件的波纹管型高压柔性管单元，以防止管道膨胀导致波纹管过度变形。 构成：具有延伸限制构件的波纹管型高压柔性管单元包括膨胀限制构件（400）和折叠式夹紧构件（500）。 膨胀限制件安装在波纹管的每个沟槽（310）中。 膨胀限制件具有弹性，并限制了波纹管的膨胀。 夹紧件安装在波纹管外。 夹紧构件限制波纹管的纵向延伸。 夹紧构件将波纹管弯曲在有限的范围内。
-
公开(公告)号：KR100955660B1
公开(公告)日：2010-05-06
申请号：KR1020070136449
申请日：2007-12-24
Applicant: 한국항공우주연구원
Abstract: 본 발명은 탱크 내에 저장된 액체의 레벨측정장치에 관한 것으로서, 그 구성은, 내부에 액체가 저장되어 있으며, 상기 액체를 방출하는 탱크; 상기 탱크의 상하부를 연결하는 차압측정배관; 상기 차압측정배관에 연결되어 있으며, 상기 차압측정배관이 상기 탱크의 하부에 연결된 부분과 동일한 위치에 배치되는 차압센서; 및 상기 차압측정배관에 연결되어 있고, 상기 탱크의 상부에 위치하며, 상기 탱크 내의 비산된 액체가 유입되는 내부공간이 마련되어 있는 리저버를 포함하며, 상기의 구성에 따르면, 탱크 상부에 연결된 차압측정배관으로의 액체 역류를 억제하여 정확한 레벨을 측정할 수 있다는 효과가 있다.
레벨측정, 차압센서, 차압측정배관, 리저버, 격막, 경사, 교차-
公开(公告)号：KR1020040009468A
公开(公告)日：2004-01-31
申请号：KR1020020043419
申请日：2002-07-23
Applicant: 한국항공우주연구원
IPC: F02K9/96
Abstract: PURPOSE: An apparatus for airtightness test is provided to reduce the size and weight of the apparatus, while allowing for ease of attachment/detachment of airtightness plate and airtightness test. CONSTITUTION: An apparatus for airtightness test comprises a support shaft(51) disposed at the center of a nozzle(100) of a rocket; an airtightness plate(52) coupled to the support shaft in such a manner that the airtightness plate is movable in forward and rearward directions, wherein the sealing plate has an outer side edge tightly contacting the inner wall of the nozzle; a handle portion mounted on the support shaft so as to move the sealing plate in forward and rearward directions; a plurality of support legs(55) each of which has an end hinge fixed at the end of the support shaft and the other end tightly contacting the inner wall of the nozzle so as to support the support shaft; and a lever adjustment member mounted on the support shaft so as to open or close the support leg.
Abstract translation: 目的：提供一种用于气密性测试的装置，以减小设备的尺寸和重量，同时允许气密性板的附接/拆卸以及气密性测试。 构成：用于气密性试验的装置包括设置在火箭喷嘴（100）的中心的支撑轴（51） 密封板（52），其以能够使前述前后方向移动的方式与所述支撑轴连结，其特征在于，所述密封板具有与所述喷嘴的内壁紧密接触的外侧边缘; 安装在所述支撑轴上的手柄部分，以使所述密封板沿前后方向移动; 多个支撑腿（55），每个支撑腿具有固定在支撑轴端部的端部铰链，另一端与喷嘴的内壁紧密接触以支撑支撑轴; 以及安装在所述支撑轴上以便打开或关闭所述支撑腿的杠杆调节构件。
-
公开(公告)号：KR1020110068080A
公开(公告)日：2011-06-22
申请号：KR1020090124915
申请日：2009-12-15
Applicant: 한국항공우주연구원
Abstract: PURPOSE: An overflow prevention valve and a hydro-pneumatic system including the same are provided to prevent water hammering without a bypass system. CONSTITUTION: An overflow prevention valve(120) comprises a body(121), a spring supporter(122), a spring(123), and an orifice(124). The body has a flow path(129) which fluid flows through and raised protrusions(121a,121b). The spring supporter is coupled to the middle of the body flow path. The spring is coupled to one side of the spring supporter and extended or compressed according to the differential pressure of the flow path. The orifice contacts the raised protrusions to block the flow path when the differential pressure of the flow path exceeds the designated differential pressure.
Abstract translation: 目的：提供防溢流阀和包括该溢流防止阀的液压气动系统，以防止没有旁路系统的水击。 构成：溢流防止阀（120）包括主体（121），弹簧支撑件（122），弹簧（123）和孔口（124）。 主体具有流体流过并突出的突起（121a，121b）的流动路径（129）。 弹簧支撑件联接到身体流动路径的中间。 弹簧联接到弹簧支撑件的一侧，并且根据流动路径的压差被延伸或压缩。 当流路的压差超过指定的压差时，孔与凸起突起接触以阻塞流路。
-
公开(公告)号：KR100654412B1
公开(公告)日：2006-12-05
申请号：KR1020050126379
申请日：2005-12-20
Applicant: 한국항공우주연구원
Abstract: A liquid propellant rocket engine is provided to improve the reliability of the rocket engine by maintaining a stable combustion temperature of a gas generating unit. In a liquid propellant rocket engine(100), a fuel supplying pump(120) supplied fuel to a combustion chamber(110). An oxidizer supplying pump(130) supplies an oxidizer to the combustion chamber. A gas generating unit(140) generates gas by receiving a part of the fuel and the oxidizer supplied from the fuel supplying pump and the oxidizer supplying pump. A turbine(150) is rotated by the gas supplied from the gas generating unit and drives the fuel supplying pump and the oxidizer supplying pump. A thrust controlling valve(160) controls the quantity of oxidizer supplied to the gas generating unit. An oxidizer bypass tube(170) is diverged from the gas generating unit of the thrust controlling valve. A mixing ratio stabilizer controls the fuel supplied from the gas generating unit according to the pressure of the oxidizer supplied to the oxidizer bypass tube.
Abstract translation: 提供液体推进剂火箭发动机以通过保持气体发生单元的稳定燃烧温度来提高火箭发动机的可靠性。 在液体推进剂火箭发动机（100）中，燃料供应泵（120）向燃烧室（110）供应燃料。 氧化剂供应泵（130）向燃烧室供应氧化剂。 气体发生单元（140）通过接收从燃料供给泵和氧化剂供给泵供给的燃料和氧化剂的一部分来产生气体。 涡轮机（150）通过从气体发生单元供应的气体旋转并且驱动燃料供应泵和氧化剂供应泵。 推力控制阀（160）控制供应到气体发生单元的氧化剂的量。 氧化剂旁路管（170）从推力控制阀的气体生成单元分出。 混合比稳定器根据供应到氧化剂旁路管的氧化剂的压力来控制从气体发生单元供应的燃料。
-
Patent Agency Ranking
公开(公告)号：KR100613986B1
公开(公告)日：2006-08-18
申请号：KR1020030071389
申请日：2003-10-14
Applicant: 한국항공우주연구원
Abstract: 본 발명은 기체 가압방식을 사용하여 액체추진제 로켓의 연소실로 고압의 추진제를 공급하는 시스템의 구조 및 형태에 관한 것이다.
이러한 본 발명은 경량의 구조물로 되어 있는 저압의 추진제 저장 탱크와 로켓 연소실 사이에 두 개 이상의 소용량 고압 탱크를 배치하여, 추진제를 저압의 저장탱크로부터 소용량 고압탱크로 충전하고 이를 고압의 기체에 의해 가압하여 로켓엔진 연소실로 공급을 하며, 두 개 이상의 고압탱크가 순차적으로 작동함으로써 로켓 연소실로 추진제를 일정하게 고압으로 공급할 수 있도록 하는 고압으로 로켓의 액체추진제를 공급할 수 있는 기체가압방식 장치에 관한 것이다.
로켓, 추진제, 기체가압, 고압-
公开(公告)号：KR100462931B1
公开(公告)日：2004-12-23
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：提供用于密封和保管的火箭发动机的喉塞，以在没有相对于燃烧室部分的结构刚性弱的喷嘴膨胀部分的情况下执行气密文本。 一种喉塞包括一个支撑安装部分（A），该支撑安装部分（A）具有单轴（1）固定支撑件（4）到喷嘴壁的喷嘴的颈部的上侧; 和具有固定在喷嘴颈部以保持气密性的气密板（8）的气密板安装部分（B）。 所述轴具有安装在所述轴的上侧的头部（2），并具有在其上侧沿三个方向突出的叶片（2'）; 和在其下侧形成的螺纹部分（1'），以使支撑板连接体（6）和气密板固定手柄（9）连接并旋转以上下移动。 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，并且支撑件由弧形软材料形成，或者在其前端具有柔软材料， 并连接到支撑杆的前端。
-
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。
-
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）。
-
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。
-
-
-
-
-
-
-
-
-
Search Results
23
records
(took 0.017 seconds)
