公开(公告)号：KR1020060063056A

公开(公告)日：2006-06-12

申请号：KR1020040102114

申请日：2004-12-07

Applicant: 한국항공우주연구원

Inventor： 류철성 ,  정용현 ,  설우석 ,  박영채 ,  조문수

IPC: F02K1/00 ,  F02K9/97

Abstract: 개시된 액체로켓의 연소기 챔버 제작방법은, 복합재료 섬유를 수지에 함침시켜서 심재에 한 층 감는 단계와, 그 감겨진 섬유층 위에서 축방향으로 경사가 있는 부위에 접착필름을 붙이는 단계와, 수지가 함침되지 않은 섬유를 그 위에 감는 단계와, 수지를 도포하는 단계를 포함한다. 이와 같은 방법에 의하면, 복합재료 섬유를 감는 동안 섬유층간에 미끄러짐이 발생될 가능성이 거의 없기 때문에, 보다 안정적이고 깨끗한 형상의 연소실 챔버를 만들어낼 수 있다.
액체로켓, 연소기, 챔버

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

Inventor： 류철성 ,  한상엽

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：KR1020030084366A

公开(公告)日：2003-11-01

申请号：KR1020020023039

申请日：2002-04-26

Applicant: 한국항공우주연구원

Inventor： 설우석 ,  류철성 ,  조원국 ,  최환석

IPC: F02K9/52

Abstract: PURPOSE: A mixer for a fluid fuel rocket engine is provided to allow for a smooth flow of fuel and oxidizing agent by preventing the injector from being exposed outward. CONSTITUTION: A mixer comprises a main structure(53) having a fuel supply unit(55) and an oxidizing agent supply unit; an upper plate(56) for forming an oxidizing agent storing unit(58) between the upper plate and the main structure; a lower plate(57) spaced apart from the upper plate, and which forms a fuel storage unit(59); and a plurality of unit injectors(50) each of which has an upper portion braze welded to the upper plate and a lower portion braze welded to the lower plate.

Abstract translation: 目的：提供用于流体燃料火箭发动机的混合器，以通过防止喷射器向外暴露而使燃料和氧化剂平稳流动。 构成：混合器包括具有燃料供给单元（55）和氧化剂供应单元的主结构（53） 用于在所述上板和所述主结构之间形成氧化剂存储单元（58）的上板（56）; 与所述上板间隔开的下板（57），并形成燃料储存单元（59）; 以及多个单元喷射器（50），每个单元喷射器（50）具有焊接到上板的上部焊料，以及焊接到下板的下部钎焊。