• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.3
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• pp.89-95
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• 2015

Performance test was conducted for an oxidizer pump and a fuel pump for a 7 ton class rocket engine, by using water. The pumps were driven by an electric motor. The hydrodynamic performance and the suction performance were measured at flow ratio of the design and off-design conditions. Head-flow curve, efficiency-flow curve, and head-cavitation number curve were obtained. It is confirmed that the pumps can satisfy the design requirements of hydrodynamic performance in terms of the head and the efficiency. The pumps also satisfied the design requirements of suction performance.

• Proceedings of the Korean Society of Food and Cookery Science Conference
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• 2005.05a
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• pp.126-126
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• 2005

• Proceedings of the Korean Information Science Society Conference
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• 2005.11b
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• pp.748-750
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• 2005

본 논문에서는 능동적인 상호협력으로 목적에 맞는 서비스를 제공하는 컴퓨팅 환경에서 가장 중요한 역할을 하게 될 문맥(Context)을 중점적으로 설명한다. 문맥은 정보를 주고받는 기본 단위가 될 것이며 이를 위한 표준이 갖추어야 할 요구사항과 이것을 수용할 수 있는 기술적 토대(XML, XML Schema, RDF, Ontology Language)를 소개 한다.

• Proceedings of the Korea Inteligent Information System Society Conference
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• 2005.11a
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• pp.171-173
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• 2005

커뮤니티 컴퓨팅은 유비쿼터스 컴퓨팅 환경을 기반으로 다양한 요구와 이를 수용하기 위한 서비스 혹은 개체를 나열하는 것 에서부터 이들 간 일시적으로 협력하고 주어진 상황을 효과적으로 인지할 뿐만 아니라 다수의 장치가 협력 관계를 추구하는 컴퓨팅 모델이다. 본 논문은 커뮤니티 모델과 미들웨어의 아키텍처를 확립하기 위한 요구사항과 구조에 대하여 논한다.

• Journal of Satellite, Information and Communications
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• v.12 no.4
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• pp.106-109
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• 2017

저궤도 위성의 배터리는 일반적으로 임무 및 식 구간에서의 부족한 전력 공급을 위해서 사용 되며, 버스 전압에 연결되어 있는 경우 출력 필터의 일부 기능을 담당하게 된다. 따라서 배터리의 주요 설계 요인은 전력 요구 분석을 통해 에너지 균형조건을 맞추기 위한 설계가 일반적이고, 배터리를 이용한 출력 전력 필터의 역할은 설계의 요인에 포함 되지 않는다. 하지만, 배터리는 전력 공급의 역할이외에도, 출력 전류의 변동이 극심하거나, 주기적으로 일정한 출력 변동을 발생하는 로드 등에 대한 필터 역할로써도 사용이 가능하다. 출력 커패시터를 배터리로 대체 할 경우 inrush 전류의 감소 및 추가적인 보호회로의 설계의 불필요 등의 장점을 가지고 있다. 배터리를 위성의 전력 공급을 위한 목적으로 사용하는 경우에는 전력 요구 분석을 통한 설계가 타당하나, 출력 로드 변동에 따른 영향을 줄이기 위해 필터로써 배터리를 사용하는 경우에는 사이즈 및 임피던스에 대한 추가적인 분석이 요구 된다. 따라서 본 논문에서는 저궤도 위성에서의 출력 전력 필터로 배터리를 이용한 설계 방안 및 성능 분석을 수행 하였다.

• 대한예방의학회:학술대회논문집
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• 2001.10a
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• pp.222-223
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• 2001

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.78-81
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• 2009

A series of hydraulic tests of a fuel pump are performed using water at a room temperature. The pump is under development for 75-ton class liquid rocket engines of the open-loop gas generator type. According to the test results, the fuel pump satisfies its design requirement and its head and efficiency at the design flowrate are higher than the expected value by the computational analysis. Also, it is found that the pressure at the rear bearing outlet is higher than expected because the inlet of bypass pipe line is narrow. Furthermore, the flowrate of the secondary flow is estimated using the pressure difference of the elbow of the bypass pipe line.

• Aerospace Engineering and Technology
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• v.8 no.1
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• pp.26-31
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• 2009

Three Lox pumps and one fuel pump are manufactured for turbopump real-propellent tests and water tests of the pumps are performed in order to estimate the performance characteristics of the pumps. According to the test results, the test region(flow ratio, cavitation number) of the pumps at the water tests cover the operating region at the real-propellent tests and also all the pumps satisfy the design requirement. The head of the Lox pumps shows a 2% difference among them due to the internal geometry, but the efficiency and overall cavitation performance are almost same. It is found that the fuel pump has a similar head and efficiency compared with the previous model of the same internal geometry, while it has a little inferior cavitation performance.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.2
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• pp.56-61
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• 2011

Performance test of a full-scale turbopump assembly for a 75 ton class liquid rocket engine was carried out at full speed. Model fluid was used as a working medium: liquid nitrogen for the oxidizer pump, water for the fuel pump, and hot air for the turbine. The turbopump was operated stably, satisfying the performance requirements. Head coefficient and flow coefficient of the pumps remained constant at the speed-increasing period. In terms of performance characteristics of pumps and turbine, the results from the turbopump assembly test showed a good agreement with those from the turbopump component tests.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.27-32
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• 2010

Performance test of a full-scale turbopump assembly for a 75 ton class liquid rocket engine was carried out at full speed. Model fluid was used as a working medium: liquid nitrogen for the oxidizer pump, water for the fuel pump, and hot air for the turbine. The turbopump was operated stably, satisfying the performance requirements. Head coefficient and flow coefficient of the pumps remained constant at the speed-increasing period. In terms of performance characteristics of pumps and turbine, the results from the turbopump assembly test showed a good agreement with those from the turbopump component tests.