公开(公告)号：KR100868075B1

公开(公告)日：2008-11-11

申请号：KR1020070107298

申请日：2007-10-24

Applicant: 한국항공우주연구원

Inventor： 권오성 ,  한상엽 ,  조인현

IPC: F02K9/42 ,  F02K9/50 ,  F02K9/60

Abstract: A diffuser for pressurizing and a liquid propellant rocket using the same are provided to prevent the drop of the pressurized gas by passing through the diffuser and spray the pressurized gas uniformly in the whole area of the outlet of the diffuser. An inflow pipe is arranged in one side of a storage tank and the pressurized gas is inputted to the inflow pipe. A diffuser body is equipped in the bottom of the inflow pipe and sprays the pressurized gas into the inside of the storage tank. A conical pitching plate(110) is equipped inside the diffuser and includes a plurality of flow holes in a plate with a conical shape. The conical pitching plate is separated from the diffuser body with a predetermined interval and is installed adjacently to the inflow pipe. A support stand(120) is arranged in the bottom of the conical pitching plate and is installed in the diffuser body. The support stand supports the conical pitching plate.

Abstract translation: 提供用于加压的扩散器和使用其的液体推进剂火箭，以防止加压气体通过扩散器而下降，并将加压气体均匀地喷射在扩散器的出口的整个区域中。 流入管布置在储罐的一侧，加压气体输入到流入管中。 在流入管的底部装有扩散器主体，并将加压气体喷射到储罐的内部。 在扩散器内部装有锥形俯仰板（110），并且在圆板形状的板中包括多个流动孔。 锥形俯仰板以预定间隔与扩散体本体分离，并与流入管相邻地安装。 支撑架（120）布置在锥形俯仰板的底部，并安装在扩散器主体中。 支撑台支撑锥形投影板。

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

Inventor： 이중엽 ,  정태규 ,  한상엽 ,  이한주 ,  하성업

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

Inventor： 한상엽 ,  류철성 ,  하성업 ,  김병훈

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。