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公开(公告)号：KR1020120080005A
公开(公告)日：2012-07-16
申请号：KR1020110001413
申请日：2011-01-06
Applicant: 충남대학교산학협력단
Abstract: PURPOSE: A film cooling apparatus of a bi-propellant rocket engine and a testing method thereof are provided to simplify a system using hydrogen peroxide instead of cooling agents. CONSTITUTION: A film cooling apparatus(300) of a bi-propellant rocket engine comprises a body unit(310) and a distributing unit(320). A front end of the body unit is connected to a rear part of an injector, and an inflow path is formed on a side part of the body unit. Cooling agents are flow through the inflow path. The front end of the distributing unit is connected to the rear part of the body unit, and one end of the distributing unit is connected to the other end of the inflow path. A plurality of distribution passages are formed in the other end of the distributing unit. The distribution passages are radially formed on a circumference of the distributing unit.
Abstract translation: 目的：提供双推进剂火箭发动机的薄膜冷却装置及其测试方法，以简化使用过氧化氢代替冷却剂的系统。 构成：双推进剂火箭发动机的薄膜冷却装置（300）包括主体单元（310）和分配单元（320）。 主体单元的前端连接到喷射器的后部，并且流体通道形成在主体单元的侧部。 冷却剂流过流入路径。 分配单元的前端连接到主体单元的后部，并且分配单元的一端连接到流入路径的另一端。 多个分配通道形成在分配单元的另一端。 分配通道径向地形成在分配单元的圆周上。
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公开(公告)号：KR1020120055239A
公开(公告)日：2012-05-31
申请号：KR1020100116857
申请日：2010-11-23
Applicant: 충남대학교산학협력단
Abstract: PURPOSE: An injector of a bipropellant rocket engine is provided to improve the combustion efficiency by consistently supplying propellants to all sprayers. CONSTITUTION: An injector of a bipropellant rocket engine comprises a propellant feed port(10), a branching unit(20), a first propellant feeding unit, and a second propellant feeding unit. First propellants and second propellants are respectively supplied to one-side of the propellant feed port through a first and second flow passage and discharged to the other side. The branching unit comprises a first spraying hole, a second spraying hole, a third flow passage, and a fourth flow passage. The first and second spraying holes are penetrated into the one side and the other side. One end of the third flow passage is connected to the first flow passage and the other end is connected to the first spraying hole. One end of the fourth flow passage is connected to the second flow passage and the other end is connected to the second spraying hole. The second propellant feeding unit comprises a third and fourth spraying holes and a fifth flow passage. The third and fourth spraying holes are penetrated into the one side and the other side correspondently to each other. One end of the fifth flow passage is connected to the second spraying hole and the other end is connected to the third spraying hole. The first propellant feeding unit comprises a fifth spraying hole and a sixth flow passage. The fifth spraying hole is penetrated into the one side and the other side corresponding to the third spraying hole. The sixth flow passage is connected to the fourth spraying hole and the other end of the sixth flow passage is connected to the fifth spraying hole.
Abstract translation: 目的：提供双组元推进剂火箭发动机的喷射器，以通过持续向所有喷雾器供应推进剂来提高燃烧效率。 构成：双组元推进剂火箭发动机的喷射器包括推进剂进料口（10），分支单元（20），第一推进剂进料单元和第二推进剂进料单元。 第一推进剂和第二推进剂通过第一和第二流动通道分别供给到推进剂进料口的一侧并排放到另一侧。 分支单元包括第一喷射孔，第二喷射孔，第三流动通道和第四流动通道。 第一和第二喷孔穿透到一侧和另一侧。 第三流路的一端与第一流路连接，另一端与第一喷孔连接。 第四流路的一端与第二流路连接，另一端与第二喷射孔连接。 第二推进剂供给单元包括第三和第四喷射孔和第五流动通道。 第三和第四喷射孔相互渗透到一侧和另一侧。 第五流路的一端与第二喷射孔连接，另一端与第三喷射孔连接。 第一推进剂供给单元包括第五喷射孔和第六流路。 第五喷射孔贯穿到与第三喷射孔对应的一侧和另一侧。 第六流路与第四喷射孔连接，第六流路的另一端与第五喷射孔连接。
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公开(公告)号：KR101173040B1
公开(公告)日：2012-08-10
申请号：KR1020100116857
申请日：2010-11-23
Applicant: 충남대학교산학협력단
Abstract: 본 발명은 이원 추진제 로켓에 사용되는 인젝터에 관한 것으로, 더욱 상세하게는 과산화수소와 케로신을 주 추진제로 사용하는 이원 추진제 로켓에 적용되며, 적은 부피를 가지고 추진제를 모든 분사기에 일정하게 공급시키고 폭발의 위험성이 낮은 이원 추진제 로켓의 인젝터에 관한 것이다.
상기와 같은 구성에 의한 본 발명의 인젝터는 부피가 작아 다양한 로켓의 설계조건을 만족시킬 수 있는 효과가 있다. 또한, 모든 분사기에 추진제를 일정하고 균일하게 공급하기 때문에 연소 효율을 높일 수 있는 효과가 있다. 마지막으로 유로상의 정체구간 및 재순환 영역이 크게 줄어들기 때문에 폭발의 위험성이 매우 작아 안정적인 운용이 가능한 효과가 있다.
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