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公开(公告)号：KR101520817B1
公开(公告)日：2015-05-18
申请号：KR1020130152008
申请日：2013-12-09
Applicant: 한국항공우주연구원
Abstract: 본발명의로켓이송장치는, 로켓엔진을이송하기위한로켓엔진이송장치로서, 상기로켓엔진이송장치는, 하부각 모서리부위에캐스터가설치되고, 일측에손잡이가설치된바디; 상기바디상에승강가능하게설치되는베이스; 상기베이스상에서전,후이동가능하게설치되는전후이동부재; 상기전후이동부재상에서좌우이동가능하게설치되는좌우이동부재; 및상기좌우이동부재상에서회전가능하게설치되며, 로켓엔진이안착되는안착부재;를포함하며, 상기베이스를바디로부터승강시키기위한승강수단을더 포함하되, 상기승강수단은, 상기바디의내부에승강용핸들에의해회전가능하게설치되며, 웜휠을갖는구동축; 상기구동축과제1 베벨기어에의해직교하게연결되어, 상기구동축과함께연동회전되는동력전달축; 상기동력전달축과제2 베벨기어에의해직교하게연결되어상기동력전달축과연동회전되며, 웜휠을갖는종동축; 상기바디내의각 모서리에설치된채, 상기구동축및 종동축의회전동력에의해승강되면서상기베이스를승강시켜주는스크류잭을포함하고있는복수의승강블록으로구성됨에따라,로켓엔진을로켓의몸체또는로켓엔진실험설비에정확하게장착하기위해, 높이조절, 전후좌우위치조절및 기울기조절등을용이하게시행할수 있는장점을얻을수 있다.
Abstract translation: 火箭发动机的转移装置技术领域本发明涉及一种火箭发动机的输送装置，其特征在于，具备：把手固定在一侧的主体和安装在各个角部的脚轮; 安装在身体上的基座; 前后可动构件; 安装在前后可动部件中的左右可动部件; 以及安装构件，其中所述火箭发动机被安装在可移动地安装在所述左右可动构件中，所述可移动构件还包括用于从所述主体升高基座的升降装置。 构造成多个升降块的升降装置包括：驱动轴，其具有由手柄可移动地安装以在所述主体内部升高的蜗轮; 动力传递轴，其与所述驱动轴一起旋转，与所述驱动轴正交连接;以及第一锥齿轮; 驱动轴，其具有与动力传递轴一起旋转的蜗轮，与动力传递轴正交连接;第二锥齿轮; 以及螺钉千斤顶，其通过驱动轴和从动轴的旋转动力而被安装在主体的每个角部中，从而将火箭准确地安装在火箭发动机或火箭发动机测试设备上，可以获得优点 作为高度调整，可以容易地进行向前调整，向后调整，右调整，左调整，倾斜调整等。
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公开(公告)号：KR101410812B1
公开(公告)日：2014-06-27
申请号：KR1020120148141
申请日：2012-12-18
Applicant: 한국항공우주연구원
Abstract: Disclosed is a pressurized fluid-conveying system to convey a high rate of fluid which comprises: a fluid tank (110) including a fluid supply pipe (112) which has an inside space (111), whereby fluid is stored formed therein, and is connected to a fluid supply source (S) and a fluid supply line (L1) to receive fluid and to inject the fluid into the inside space (111), and a fluid conveying pipe (113) connected to a fluid conveying line (L2) which conveys the fluid stored in the inside space outside; a first pressure sensor (120) mounted on one side of the fluid tank which measures the pressure in the inside space (111); a gas supply pipe (130) inserted into the upper part of the fluid tank (110) by penetrating, arranged in the inside space (111), connected to a gas tank (131) whereby gas is pressurized and stored, and to a gas supply line (L3) supplied with gas which pressurizes the fluid stored in the inside space (111) by injecting gas into the inside space (111); and an automatic valve (140) arranged on the gas supply line (L3) which performs an opening and closing operation according to a value measured by the first pressure sensor (120) and controls pressure in the inside space (111) by controlling the rate of gas injected through the gas supply pipe (130) into the inside space (111).
Abstract translation: 公开了一种用于输送高速率流体的加压流体输送系统，其包括：流体箱（110），其包括具有内部空间（111）的流体供应管（112），由此流体存储在其中，并且是 连接到流体供应源（S）和流体供应管线（L1）以接收流体并将流体注入到内部空间（111）中;以及流体输送管（113），其连接到流体输送管线（L2） 其将存储在内部空间中的流体传送到外部; 第一压力传感器（120），其安装在所述流体箱的一侧，其测量所述内部空间（111）中的压力; 气体供给管（130），其通过贯穿插入在所述内部空间（111）中的与所述气体罐（131）连接的气体（131）而被插入到所述流体罐（110）的上部， 供应管线（L3），其供应有通过将气体注入到内部空间（111）中而对存储在内部空间（111）中的流体加压的气体; 以及配置在所述气体供给管线（L3）上的自动阀，其根据由所述第一压力传感器（120）测量的值进行打开和关闭操作，并通过控制所述内部空间（111）的压力来控制所述内部空间 的气体从气体供给管道（130）喷射到内部空间（111）中。
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公开(公告)号：KR1020130075938A
公开(公告)日：2013-07-08
申请号：KR1020110144266
申请日：2011-12-28
Applicant: 한국항공우주연구원
Abstract: PURPOSE: An apparatus and method for super-cooling a pressurized cryogenic liquid are provided to reduce the vaporization of the super-cooled liquid caused by temperature rise and to decrease the vapor pressure of the liquid when transporting the liquid to a demand place, thereby preventing the cavitation of a pump. CONSTITUTION: An apparatus for super-cooling a pressurized cryogenic liquid includes a storage tank part (200), a pressurizing part (210), a liquid inlet/outlet part (230), a condition measuring part (240), a control part (260), and an inert gas feeding part (250). The storage tank part stores the high pressure and cryogenic liquid. The pressurizing part injects an inert gas for pressurization into the storage tank part in order to increase pressure inside the storage tank part. The liquid inlet/outlet charges the storage tank part with the liquid, or discharges the liquid from the storage tank part. The condition measuring part measures the condition of the liquid. The control part determines the kind of an inert gas for injection, which is injected inside the storage tank part, in order to super-cool the liquid according to the measured condition of the liquid. The inert gas feeding part injects the determined injectable inert gas inside the storage tank part. [Reference numerals] (200) Storage tank part; (210) Pressurizing part; (220) Gas exhausting part; (230) Liquid inlet/outlet part; (240) Temperature measuring; (242) Temperature measuring module; (244) Water level measuring module; (250) Inactive gas producing part; (252) Inactive gas cooling module; (260) Control part
Abstract translation: 目的：提供一种用于超冷却加压低温液体的设备和方法，以减少由温度升高引起的过冷却液体的蒸发，并在将液体运送到需求位置时降低液体的蒸气压，从而防止 泵的气蚀。 构成：用于超冷却加压低温液体的装置包括储罐部分（200），加压部分（210），液体入口/出口部分（230），条件测量部分（240），控制部分 260）和惰性气体供给部（250）。 储罐部分储存高压和低温液体。 为了增加储罐部内部的压力，加压部将用于加压的惰性气体注入储罐部。 液体入口/出口用液体对储罐部分充电，或者从储罐部分排出液体。 条件测量部件测量液体的状态。 控制部分确定注入到储罐部分内的惰性惰性气体的种类，以便根据液体的测量条件对液体进行超冷却。 惰性气体供给部将确定的可注入惰性气体注入储罐部分内。 （附图标记）（200）储罐部分; （210）加压部件; （220）排气部分; （230）液体入口/出口部分; （240）温度测量; （242）温度测量模块; （244）水位测量模块; （250）非活性气体生成部件; （252）非活性气体冷却模块; （260）控制部分
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公开(公告)号：KR101122026B1
公开(公告)日：2012-03-09
申请号：KR1020090114645
申请日：2009-11-25
Applicant: 한국항공우주연구원
Abstract: 본발명은가스발생기연소시험을위한후류가스처리장치에관한것이다. 가스발생기연소시험을위한후류가스처리장치는연결치구, 액체질소공급장치를포함한다. 연결치구는가스발생기와소음저감장치사이에설치되어외부기체유입을차단한다. 액체질소공급장치는상기연결치구의내부로액체질소를공급한다. 연결치구를설치함으로써가스발생기연소시험시 소음저감장치내부로흡입되는공기를막아공기중의산소가소음저감장치내부에서미연의후류가스와혼합되어폭발이일어나는위험을방지하고, 액체질소공급장치를통해연결치구의내부로비활성인액체질소및 물을공급함으로써비활성인액체질소가기체질소로기화, 혼합되어후류가스의재점화가능성을줄이고액체질소와물이소음저감장치내부온도를낮추어가스발생기연소시험의안정성을증가시켜준다.
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Patent Agency Ranking
公开(公告)号：KR1020090077248A
公开(公告)日：2009-07-15
申请号：KR1020080003087
申请日：2008-01-10
Applicant: 한국항공우주연구원
CPC classification number: F02K9/97 , B23P15/008 , F02K9/64
Abstract: A nozzle manufacturing method of a combustor is provided to reduce time and manufacture cost and remove partial defects, necking, and instability of material. A nozzle manufacturing method of a combustor comprises: a step(a) preparing an outer cover of a cylindrical shape being made of stainless steel material and an inner cover of the cylindrical shape being made of copper alloy material; a step(b) processing the outer cover, and cutting the outer cover in order to be bisected in an axial direction to form an inner cover insertion part; a step(c) processing the inner cover in order to have the same external diameter as the inside diameter of the inner cover insertion part; a step(d) inserting the inner cover into the inner cover insertion part and assembling the outer cover and the inner cover; a step(e) brazing the cut part of the outer cover; and a step(f) processing the outer cover in order to have the final contour the outside shape of the outer cover.
Abstract translation: 提供了一种燃烧器的喷嘴制造方法，以减少时间和制造成本并消除材料的部分缺陷，颈缩和不稳定性。 燃烧器的喷嘴制造方法包括：（a）制备由不锈钢材料制成的圆筒形的外盖和由铜合金材料制成的圆筒形的内盖; 步骤（b）处理外盖，切割外盖以在轴向方向上二等分以形成内盖插入部; 步骤（c）处理内盖以具有与内盖插入部的内径相同的外径; 步骤（d）将内盖插入内盖插入部并组装外盖和内盖; 步骤（e）钎焊外盖的切割部分; 以及步骤（f）处理所述外盖以使所述最终轮廓具有所述外盖的外部形状。
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公开(公告)号：KR1020090076514A
公开(公告)日：2009-07-13
申请号：KR1020080002508
申请日：2008-01-09
Applicant: 한국항공우주연구원
CPC classification number: F02K9/64 , F05D2230/90 , F05D2300/611
Abstract: A regenerative-cooling combustion chamber for a liquid-propellant rocket engine coated by nickel and chrome and a coating method thereof are provided to improve abrasion resistance, heat resistance, and corrosion resistance by forming an electroless nickel layer and an electrolysis chrome layer inside a combustion chamber. A regenerative-cooling combustion chamber for a liquid-propellant rocket engine coated by nickel and chrome comprises: a combustion chamber inner coat(130) equipped with a cooling channel; and a combustion chamber outer coat(110) coupled with the single-side of the combustion chamber inner coat. The electroless nickel layer and the electrolysis chrome layer are successively coated on the other side of the combustion chamber inner coat. The thickness of the electroless nickel layer is 150~250 micron. The thickness of the electrolysis chrome layer is 100~200 micron.
Abstract translation: 提供了一种用镍和铬涂覆的液体推进剂火箭发动机的再生冷却燃烧室及其涂覆方法，以通过在燃烧中形成无电镀镍层和电解铬层来改善耐磨性，耐热性和耐腐蚀性 室。 用于由镍和铬涂覆的液体推进剂火箭发动机的再生冷却燃烧室包括：配备有冷却通道的燃烧室内涂层（130） 以及与燃烧室内涂层的单侧联接的燃烧室外涂层（110）。 无电解镍层和电解铬层依次涂覆在燃烧室内涂层的另一侧。 化学镀镍层的厚度为150〜250微米。 电解铬层的厚度为100〜200微米。
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公开(公告)号：KR1020090067763A
公开(公告)日：2009-06-25
申请号：KR1020070135524
申请日：2007-12-21
Applicant: 한국항공우주연구원
Abstract: A regeneration cooling channel simulated sample of a rocket combustor is provided to confirm whether caulking occurs due to reaction of copper alloy and hydrocarbon fuel and whether the copper alloy is damaged through simulated samples and use the confirmation result to manufacture a regeneration cooling channel of the rocket combustor. A regeneration cooling channel simulated sample of a rocket combustor includes a copper alloy tube(110), a stainless steel tube(120) and a power connector(130). The copper alloy tube is formed by wire-cutting an inner flow path(110a). The stainless steel tube is formed by wire cutting and has a diameter such that the copper alloy tube is inserted into the stainless steel tube. At least one temperature sensor mounting slot(120a) for sensing the surface temperature of the copper alloy tube is formed. The power connector is combined with both ends of the stainless steel tube.
Abstract translation: 提供火箭燃烧器的再生冷却通道模拟样品，以确认铜合金和碳氢燃料的反应是否发生堵缝，以及铜合金是否通过模拟样品损坏，并使用确认结果制造火箭的再生冷却通道 燃烧室。 火箭燃烧器的再生冷却通道模拟样品包括铜合金管（110），不锈钢管（120）和电源连接器（130）。 铜合金管通过线切割内部流路（110a）而形成。 不锈钢管通过线切割形成，并且具有使铜合金管插入不锈钢管的直径。 形成用于感测铜合金管的表面温度的至少一个温度传感器安装槽（120a）。 电源连接器与不锈钢管的两端相结合。
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公开(公告)号：KR100808675B1
公开(公告)日：2008-02-29
申请号：KR1020060131867
申请日：2006-12-21
Applicant: 한국항공우주연구원
CPC classification number: B23P15/008 , F02K1/00 , F02K9/64 , F02K9/97
Abstract: A method for manufacturing a regenerative cooling nozzle is provided to protect a nozzle expansion portion from deformation by performing bulging processes through multiple stages. A method for manufacturing a regenerative cooling nozzle includes a first step(S1) of forging a material for manufacturing an inner structure of the nozzle, a second step(S2) of performing heat treatment onto the forged material and furnace cooling, a third step(S3) of inspecting the organism of the material, a fourth step(S4) of manufacturing an inner structure having an outer surface with a cooling channel by using the inspected material, a fifth step(S5) of bulging one end of the inner structure, and a sixth step(S6) of brazing the inner structure and an outer structure of the nozzle and performing a process for ease of welding. The heat treatment is performed for 20 to 30 minutes at the temperature of 800 to 1030 deg.C. In the fourth step, the inner structure has an outer surface with a plurality of channel ribs for formation of a cooling channel. In the fifth step, a plurality of tapered bulging jigs are sequentially introduced into one end of the inner structure for bulging in accordance with the tapered degree of the bulging jigs.
Abstract translation: 提供一种制造再生式冷却喷嘴的方法，以通过多级执行凸出加工来保护喷嘴膨胀部不发生变形。 再生式冷却喷嘴的制造方法包括：锻造用于制造喷嘴内部结构的材料的第一工序（S1）;对锻造材料进行热处理的第二工序（S2）和炉冷却，第三工序 S3），通过使用被检查材料制造具有冷却通道的外表面的内部结构的第四步骤（S4），使内部结构的一端膨胀的第五步骤（S5） 以及钎焊内部结构和喷嘴的外部结构的第六步骤（S6），并且执行易于焊接的处理。 在800〜1030℃的温度下进行20〜30分钟的热处理。 在第四步骤中，内部结构具有外表面，其具有用于形成冷却通道的多个通道肋。 在第五步骤中，根据凸起夹具的锥度顺序地将多个锥形凸起夹具引入内部结构的一个端部，用于凸出。
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公开(公告)号：KR1020060076550A
公开(公告)日：2006-07-04
申请号：KR1020040115009
申请日：2004-12-29
Applicant: 한국항공우주연구원
IPC: F02K9/62
Abstract: 본 발명은 액체로켓 연소기의 분사기형 배플에 관한 것으로, 특히 연소기의 분사헤드 분사면에 설치되어 연소실 내에서 추진제의 연소시 발생하는 고온, 고압의 조건에서 자체 내부냉각기능을 가지고 있어 파손되지 않으며, 액체연료와 산화제의 분사기능을 가지고 있어 연소효율을 높이면서도, 종래의 배플이 갖는 연소안정화를 이룰수 있는 액체로켓의 연소기의 분사기형 배플에 관한 것이다.
상기한 목적을 달성하기 위한 본 발명의 제 1특징은 액체로켓의 연소기 분사헤드의 분사면에 설치되어 연소실의 일부를 구획하는 배플에 있어서, 상기 배플은 액체연료와 산화제를 연소실로 분사시키는 다수의 분사기가 분사헤드의 분사면에 돌출되게 설치되어 연소실의 일부를 구획하도록 상기 다수의 분사기가 분사헤드 분사면상의 중앙부에 환형의 격벽을 이루도록 설치되며, 또한 다수의 분사기가 상기 환형의 격벽 외주로 방사형의 격벽을 이루도록 설치되는 액체로켓 연소기의 분사기형 배플에 있다.
액체로켓엔진, 로켓, 연소실, 연소안정화장치, 내부냉각
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