公开(公告)号：KR1020040044637A

公开(公告)日：2004-05-31

申请号：KR1020020072723

申请日：2002-11-21

Applicant: 한국항공우주연구원

Inventor： 정태규 ,  정동호 ,  오승협

IPC: F02K9/95

Abstract: PURPOSE: An igniting device of a liquid rocket engine is provided to improve the reliability by safely storing TEAL(Triethylaluminum) for drastic combustion in combining with oxygen as the ignition agent, and to cut down manufacturing cost by reusing the igniting device with charging the ignition agent safely and easily. CONSTITUTION: An igniting device ignites a liquid rocket engine for supplying driving force to a projectile for launching a rocket or a satellite, and comprises a cylinder(1) filled with the ignition agent, two-way valves(2,2') charging the ignition agent to the upper part of the cylinder and pyro valves(3,3') installed at both ends of the cylinder to regulate the ignition agent. The ignition agent is injected from the cylinder to the engine with opening the pyro valves in applying the ignition command, and combined with oxygen in the combustion chamber of the engine to ignite the engine. Oxygen is purged with nitrogen or helium gas after charging the ignition agent.

Abstract translation: 目的：提供液体火箭发动机的点火装置，通过安全地存储用于与作为点燃剂的氧组合的急剧燃烧的TEAL（三乙基铝）来提高可靠性，并通过点燃点火装置重新使用点火装置来降低制造成本 代理安全，轻松。 构成：点火装置点燃液体火箭发动机，向发射火箭或卫星的射弹提供驱动力，并包括装有点火剂的气缸（1），充满点火剂的二通阀（2,2'） 点火剂到气缸的上部，并安装在气缸两端的热敏阀（3,3'）以调节点火剂。 点火剂从气缸喷射到发动机上，在施加点火指令的同时打开热敏阀，并与发动机的燃烧室中的氧气结合以点燃发动机。 充满点火剂后，用氮气或氦气吹扫氧气。

公开(公告)号：KR1020040034031A

公开(公告)日：2004-04-28

申请号：KR1020020063358

申请日：2002-10-17

Applicant: 한국항공우주연구원

Inventor： 정동호 ,  정태규 ,  오승협

IPC: B64G1/42

Abstract: PURPOSE: A jig for carrying an igniter for a liquid rocket is provided to prevent the leakage of an ignition charge by safely carrying the igniter. CONSTITUTION: A protrusion(5') is formed at the lower part of a moving guide(5). An opening is formed at one side of a jig case(11). A moving rail(3) moves along the moving guides, and has a fixing clamp(2) for fixing an igniter(1). A cover(6) is formed at the front of the moving rail, and seals the jig case up. A nitrogen filling valve(8) is connected to the cover. A nitrogen discharge valve(9) is connected to the jig case. The jig case is filled with nitrogen.

Abstract translation: 目的：提供用于携带液体火箭点火器的夹具，以通过安全地携带点火器来防止点火电荷的泄漏。 构成：在移动导轨（5）的下部形成突起（5'）。 在夹具壳体（11）的一侧形成有开口。 移动轨道（3）沿着移动导轨移动，并且具有用于固定点火器（1）的固定夹具（2）。 在移动轨道的前部形成有盖（6），并将夹具壳体向上密封。 氮气充填阀（8）连接到盖子上。 氮气排出阀（9）与夹具壳体连接。 夹具盒充满氮气。

公开(公告)号：KR1020010057323A

公开(公告)日：2001-07-04

申请号：KR1019990059838

申请日：1999-12-21

Applicant: 한국항공우주연구원

Inventor： 정용갑 ,  오승협 ,  채연석 ,  김유 ,  김선진

IPC: F01N1/00

Abstract: PURPOSE: An apparatus for damping noise is provided to reduce the noise generated due to the discharge of combustion gas to the atmosphere via a nozzle in a liquid fuel rocket engine test. CONSTITUTION: A noise damping apparatus comprises: a multi-stage duct whose diameter becomes larger as going to an exhaust port from an intake port(11); an angular injection ring header(20) installed in the intake port to inject water toward the exhaust port; horizontal injection ring headers(30) installed in the duct to inject water toward the exhaust port parallel to exhaust gas; and a water supply tube(40) supplying water to the injection ring headers. The water supplied via the water supply tube evaporates the exhaust gas. While the exhaust gas is evaporated, temperature falls and density increases. According to the enlargement of the area discharged to the atmosphere, the speed of combustion gas is reduced. Therefore, noise is damped.

Abstract translation: 目的：提供一种用于阻尼噪声的装置，以减少在液体燃料火箭发动机试验中通过喷嘴将燃烧气体排放到大气中产生的噪声。 构成：噪声消除装置包括：从进气口（11）到达排气口的直径变大的多级管道; 安装在进气口中的角度注射环集管（20），用于向排气口注入水; 安装在管道中的水平注射环集管（30），以与排气平行地向排气口注入水; 以及向注射环集管供水的供水管（40）。 通过供水管供水的水蒸发废气。 当废气蒸发时，温度下降并且密度增加。 根据排放到大气中的面积的扩大，燃烧气体的速度降低。 因此，噪声被抑制。