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公开(公告)号：KR101409939B1
公开(公告)日：2014-06-20
申请号：KR1020130005054
申请日：2013-01-16
Applicant: 한국항공우주연구원
Inventor： 정영석
Abstract: The purpose of the present invention is to provide a cryogenic liquid propellant collecting apparatus for reigniting a rocket propulsion engine, wherein the cryogenic liquid propellant collecting apparatus is made up simply to not only trap a cryogenic liquid propellant in order to ignite the propulsion engine under a low gravitational condition or a non-gravitational condition, but also prevent the evaporation of the cryogenic liquid propellant beforehand. According to the present invention for the effects above, the cryogenic liquid propellant collecting apparatus for reigniting the rocket propulsion engine collects the cryogenic liquid propellant for reignition from a liquid propellant tank so that the cryogenic liquid propellant can be transferred to a connection pipe connected to the rocket propulsion engine, and comprises: a collecting part communicating with the bottom of the cryogenic liquid propellant tank, and connected to the connecting pipe; an inner pipe forming a flow path for the cryogenic liquid propellant flowing into the collecting part; at least one screen installed in the inner pipe, and separating a gas from the cryogenic liquid propellant; and a circulating unit circulating the cryogenic liquid propellant to the liquid propellant tank through the collecting part after the gas is separated from the cryogenic liquid propellant.
Abstract translation: 本发明的目的是提供一种用于重新点燃火箭推进发动机的低温液体推进剂收集装置，其中低温液体推进剂收集装置简单地构成为不仅捕获低温液体推进剂，以便在一个 低引力条件或非重力条件，也预防了低温液体推进剂的蒸发。 根据上述效果的本发明，用于重新点燃火箭推进发动机的低温液体推进剂收集装置从液体推进剂罐收集用于重新点燃的低温液体推进剂，使得低温液体推进剂可以转移到连接到 火箭推进发动机，包括：与低温液体推进剂罐的底部连通并连接到连接管的收集部分; 形成流入所述收集部的低温液体推进剂的流路的内管; 至少一个屏幕安装在内管中，并且从低温液体推进剂中分离出气体; 以及在气体与低温液体推进剂分离之后循环装置将低温液体推进剂循环通过收集部分的液体推进剂罐。
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公开(公告)号：KR1020030052127A
公开(公告)日：2003-06-26
申请号：KR1020010082019
申请日：2001-12-20
Applicant: 한국항공우주연구원
IPC: F16K15/00
Abstract: PURPOSE: A check valve is provided to design a passage not to largely generate the inner differential pressure and to maintain the sealing though the elasticity of a spring for the inner sealing is not large. CONSTITUTION: The inside of a valve body(1) is formed in a streamline. A seat(2) is fixed in a secondary side(2) of the valve body through a seat bolt(6). A guide(5) is installed in a primary side(1') of the valve body. A spring(6) is installed between a spool(3) and the guide. The spool is combined with the guide. The spool maintains the sealing of the secondary side by contacting to the seat. Thereby, the processing error of the body and the seat is prevented and the leakage is prevented.
Abstract translation: 目的：提供止回阀来设计通道，不会大量产生内压差并保持密封，尽管内密封弹簧的弹性不大。 构成：阀体（1）的内部形成为流线。 座椅（2）通过座椅螺栓（6）固定在阀体的次级侧（2）中。 引导件（5）安装在阀体的初级侧（1'）中。 弹簧（6）安装在阀芯（3）和引导件之间。 阀芯与导轨结合。 阀芯通过与座椅接触来保持次级侧的密封。 由此，防止了主体和座椅的加工误差，防止了泄漏。
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公开(公告)号：KR101409940B1
公开(公告)日：2014-06-20
申请号：KR1020130005055
申请日：2013-01-16
Applicant: 한국항공우주연구원
Inventor： 정영석
Abstract: The purpose of the present invention is to provide a flow rate control apparatus for a rocket turbo pump engine, wherein the flow rate control apparatus is capable of controlling the flow rate of a propellant in order to prevent pressure in a line at the inlet of a pump from being dropped by the sudden supply of the propellant to a main combustor when the engine is ignited. According to the present invention for the effect above, the flow rate control apparatus for the rocket turbo pump engine is a flow rate control apparatus for the rocket turbo pump engine, which controls the flow rate of the propellant flowing to the main combustor along the line, and comprises: a valve housing installed to communicate with the line; a flow rate control sleeve installed inside the valve housing, and having at least one through-hole on the side surface thereof; a valve body installed in the flow rate control sleeve, able to slide, and controlling the opening degree of the through-hole; and an actuating unit actuating the valve body.
Abstract translation: 本发明的目的是提供一种用于火箭涡轮泵发动机的流量控制装置，其中，流量控制装置能够控制推进剂的流量，以便防止在入口处的管线中的压力 当发动机点燃时，泵不会被推进剂突然供应到主燃烧室而下降。 根据上述效果的本发明，用于火箭涡轮泵发动机的流量控制装置是用于火箭涡轮泵发动机的流量控制装置，其控制沿着管线流向主燃烧器的推进剂的流量 并且包括：安装成与所述线路连通的阀壳体; 流量控制套筒，其安装在所述阀壳体内部，并且在其侧表面上具有至少一个通孔; 阀体，安装在流量控制套筒中，能够滑动并控制通孔的开度; 以及致动单元致动阀体。
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公开(公告)号：KR101357617B1
公开(公告)日：2014-02-03
申请号：KR1020130005052
申请日：2013-01-16
Applicant: 한국항공우주연구원
Inventor： 정영석
Abstract: The purpose of the present invention is to provide a pressure correcting method of a turbo-pump engine for rocket, which can simplify the pressure correction of the engine for reducing a thrust error to reduce the number of times of combustion tests used to correct the pressure, thereby minimizing the reduction of life of the turbo-pump engine. To this end, the pressure correcting method of a turbo-pump engine for rocket of the present invention corrects pressure while varying the opening of a main oxidizer line, main fuel line, sub oxidizer line, and sub fuel line, and comprises the steps of: driving the engine so as to vary the opening; fixing the opening of the sub fuel line if the pressure of the sub fuel line is in a first predetermined pressure section for a limited time; fixing the opening of the sub oxidizer line if the pressure of the sub oxidizer line is in a second predetermined pressure section for the limited time; fixing the opening of the main fuel line if the pressure of the main fuel line is in a third predetermined pressure section for the limited time; fixing the opening of the main oxidizer line if the pressure of the main oxidizer line is in a fourth predetermined pressure section for the limited time; and stopping the engine if the opening of each line is fixed. [Reference numerals] (S110) Start an engine; (S111) Stop the change of opening for a first predetermined time; (S120) Is sub fuel line pressure in a first predetermined pressure section for a limited time?; (S121) Fix the opening of a sub fuel line; (S130) Is sub oxidizer line pressure in a second predetermined pressure section for the limited time?; (S131) Fix the opening of a sub oxidizer line; (S140) Is main fuel line pressure in a third predetermined pressure section for the limited time?; (S141) Fix the opening of a main fuel line pressure; (S150) Is main oxidizer line pressure in a fourth predetermined pressure section for the limited time?; (S151) Fix the opening of a main oxidizer line; (S160) Maintain the operation of the engine(for a second predetermined time); (S170) Notify; (S180) Stop emergently; (S190) Drive an engine stop sequence; (S191) Stop the engine
Abstract translation: 本发明的目的是提供一种用于火箭的涡轮泵发动机的压力校正方法，其可以简化用于减小推力误差的发动机的压力校正，以减少用于校正压力的燃烧测试次数 从而使涡轮泵发动机的寿命减少最小化。 为此，本发明的用于火箭的涡轮泵发动机的压力校正方法在改变主氧化剂管线，主燃料管线，次氧化剂管线和副燃料管线的开口的同时校正压力，并且包括以下步骤： ：驾驶发动机以改变开口; 如果副燃料管路的压力在有限的时间内处于第一预定压力段，则固定副燃料管路的开口; 如果副氧化剂管线的压力在限定时间内处于第二预定压力区段，则固定副氧化剂管线的开口; 如果主燃料管路的压力在限定时间内处于第三预定压力区段，则固定主燃料管路的开口; 如果主氧化剂管线的压力在有限的时间内处于第四预定压力段，则固定主氧化剂管线的开口; 如果每条线的开口固定，则停止发动机。 （参考号）（S110）起动发动机; （S111）停止第一预定时间的开放更改; （S120）在限定时间内在第一预定压力段中的副燃料管路压力; （S121）固定副燃料管路的开度; （S130）在限定的时间内在次级氧化剂管路压力在第二预定压力区间中; （S131）固定副氧化剂生产线的开口; （S140）在限定时间内在第三预定压力段中的主要燃料管路压力; （S141）固定主燃料管路压力的开度; （S150）在限定时间内，第四预定压力部分中的主氧化剂管路压力; （S151）固定主氧化线的开口; （S160）保持发动机的运转（第二预定时间）; （S170）通知; （S180）紧急停止; （S190）驱动发动机停止顺序; （S191）停止发动机
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Patent Agency Ranking
公开(公告)号：KR1020050037904A
公开(公告)日：2005-04-25
申请号：KR1020030073186
申请日：2003-10-20
Applicant: 한국항공우주연구원
IPC: F16K1/34
Abstract: 본 발명은 과학 연구/탐사용 로켓 및 위성 발사체에서 극저온 추진제로 사용하고 있는 액체 산소를 주입, 배출하며 기화된 저온 가스를 배기하기 위한 극저온용 벨로우즈-글로브 밸브에 관한 것이다.
이러한 본 발명은 밸브 몸체(1)에 설치된 유로(9)를 개폐시키는 디스크(2)와,
상기 디스크(2)가 연결된 스탬(8)의 하측과 밸브 몸체(1)의 상측에 설치된 하단 벨로우즈 용접부(4)를 연결하는 하단 벨로우즈(3)와,
상기 하단 벨로우즈 용접부(4)의 상측으로 공압 공급로(11)가 형성되며 상측의 상단 벨로우즈 용접부(6)와 연결된 상단 벨로우즈(5)와,
상기 상단 벨로우즈(5)에 탄성력을 제공하도록 상측에 설치된 스프링(7)과,
상기 상단 벨로우즈 용접부(6)에서 체결되어 스프링(7)의 탄성력을 제공받으며 디스크(2)가 하측에 설치된 스탬(8)으로 구성됨을 특징으로 하는 것이다.-
公开(公告)号：KR100449457B1
公开(公告)日：2004-09-21
申请号：KR1020000078600
申请日：2000-12-19
Applicant: 한국항공우주연구원
IPC: B64G5/00
Abstract: PURPOSE: A pressure reducing valve-preventing impact of vibration is provided to remove hunting performance of a valve by installing an orifice and to prevent impact transferred a piston by mounting an impact isolating film. CONSTITUTION: A pressure reducing valve for preventing impact from vibration comprises a first space(1) connected to a reservoir tank; a secondary space(2) maintaining established pressure; a spring(3) mounted on an upper portion of a piston(4); an isolating film(5) isolating impact by being protruded on a lower portion of a piston chamber(5'); an orifice(6) controlling pressure by being installed on a lower portion of the isolating film; a valve disk(9) formed on a lower portion of a sheet(8); a spring(11) contained in the valve disk; a long guide(10) contacted to the valve disk by being arranged on a lower portion of the sheet; low frictional disk guides(12,12') mounted on upper and lower portions of the long guide; and a relief valve(13) fixed on a lower portion of the secondary space. The pressure-reducing valve is mounted between the first space and the second space.
Abstract translation: 目的：提供一种防止振动冲击的减压阀，通过安装孔口来消除阀门的振荡性能，并通过安装冲击隔离膜来防止撞击传递到活塞上。 构成：用于防止振动冲击的减压阀包括连接到储液罐的第一空间（1） 第二空间（2）保持已建立的压力; 安装在活塞（4）上部的弹簧（3）; 隔离膜（5），其通过突出在活塞室（5'）的下部而隔离冲击; 通过安装在隔离膜的下部上来控制压力的孔口（6） 形成在薄片（8）的下部上的阀盘（9）; 包含在阀盘中的弹簧（11） 长引导件（10），其通过布置在片材的下部上而与阀盘接触; 低摩擦盘导向装置（12,12'），其安装在长导向装置的上部和下部; 和固定在二次空间下部的安全阀（13）。 减压阀安装在第一空间和第二空间之间。
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公开(公告)号：KR1020040044638A
公开(公告)日：2004-05-31
申请号：KR1020020072725
申请日：2002-11-21
Applicant: 한국항공우주연구원
IPC: B64G5/00
Abstract: PURPOSE: A pneumatic separation valve for injecting and discharging high pressure gas is provided to separate automatically and safely by pneumatic pressure in an emergency with supplying pneumatic gas before launching the rocket after charging gas, and to prevent failure from high pressure by using the O-ring installation part optimally. CONSTITUTION: A pneumatic separation valve is composed of a projectile side body(1) mounting a projectile piston(8) supported by a spring(10); a ground side body(2) mounting a ground piston(8') supported by a spring(10') and a fixing ball(5) in a ball hole; and a support case(4) displaced by remote control with forming a solenoid valve(7) outside the ground side body. Piston seals(6') are formed in the front parts of the pistons to open and close the passages, and a ball groove is formed in the projectile piston to place the fixing ball. The support case is moved backward and separated from the fixing ball by injecting pneumatic gas with the solenoid valve. An O-ring(3) is installed in the contact portion of the projectile side body and the ground side body to restrict high pressure.
Abstract translation: 目的：提供高压气体注入和排出的气动分离阀，在紧急情况下通过气动压力自动分离，在充气后发射火箭时提供气动气体，并通过使用O- 环安装部分最佳。 构成：气动分离阀由安装由弹簧（10）支撑的弹丸活塞（8）的射弹侧体（1）组成。 将由弹簧（10'）支撑的地面活塞（8'）和固定球（5）安装在球孔中的地侧主体（2） 以及通过远程控制而移位的支撑壳体（4），其在地侧主体外部形成电磁阀（7）。 活塞密封件（6'）形成在活塞的前部，以打开和关闭通道，并且在弹丸活塞中形成球槽，以将固定球放置。 通过与电磁阀注入气动气体，支撑壳向后移动并与固定球分离。 O型环（3）安装在射弹侧体和地侧体的接触部分，以限制高压。
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公开(公告)号：KR1020020049431A
公开(公告)日：2002-06-26
申请号：KR1020000078600
申请日：2000-12-19
Applicant: 한국항공우주연구원
IPC: B64G5/00
Abstract: PURPOSE: A pressure reducing valve-preventing impact of vibration is provided to remove hunting performance of a valve by installing an orifice and to prevent impact transferred a piston by mounting an impact isolating film. CONSTITUTION: A pressure reducing valve for preventing impact from vibration comprises a first space(1) connected to a reservoir tank; a secondary space(2) maintaining established pressure; a spring(3) mounted on an upper portion of a piston(4); an isolating film(5) isolating impact by being protruded on a lower portion of a piston chamber(5'); an orifice(6) controlling pressure by being installed on a lower portion of the isolating film; a valve disk(9) formed on a lower portion of a sheet(8); a spring(11) contained in the valve disk; a long guide(10) contacted to the valve disk by being arranged on a lower portion of the sheet; low frictional disk guides(12,12') mounted on upper and lower portions of the long guide; and a relief valve(13) fixed on a lower portion of the secondary space. The pressure-reducing valve is mounted between the first space and the second space.
Abstract translation: 目的：提供减震阀 - 防止振动的冲击，通过安装孔口来消除阀的振荡性能，并通过安装防撞隔离膜来防止活塞撞击。 构成：用于防止振动冲击的减压阀包括连接到贮存罐的第一空间（1）; 二级空间（2）维持建立的压力; 安装在活塞（4）的上部的弹簧（3）; 隔离膜（5）通过突出在活塞室（5'）的下部上而隔离冲击; 通过安装在隔离膜的下部来控制压力的孔口（6）; 形成在片材（8）的下部的阀盘（9）; 包含在阀盘中的弹簧（11）; 通过布置在片材的下部与阀盘接触的长引导件（10） 安装在长引导件的上部和下部的低摩擦盘引导件（12,12'）; 以及固定在所述副空间的下部的安全阀（13）。 减压阀安装在第一空间和第二空间之间。
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