• Journal of the Korean Society of Propulsion Engineers
• /
• v.16 no.6
• /
• pp.92-97
• /
• 2012

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The oxidizer supply system modeling using AMESim was performed based on the results of the detailed design, and the oxidizer supply characteristics was analyzed in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.502-506
• /
• 2012

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The oxidizer supply system modeling using AMESim was performed based on the results of the detailed design, and the oxidizer supply characteristics was analyzed in this paper.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.16 no.4
• /
• pp.87-92
• /
• 2012

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The fuel supply system modeling using AMESim was performed based on the results of the detailed design, and the fuel supply characteristics was analyzed in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2003.05a
• /
• pp.193-196
• /
• 2003

The KSR-III developed by KARI is the first rocket vehicle which is adopting the liquid propellant rocket engine system in Korea and its flight test was successfully done last year. KSR-III is a sounding rocket class launch vehicle, but there is a sense to accomplish design, manufacture, performance test and finally its flight test by domestic technology. In this paper, the authors are intended to introduce the multi-purpose test facility(PTA-II Test Facility) which is constructed for the variety of tests on KSR-III feeding system(single component tests, verification tests, cold flow tests and combustion tests) and its test results.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.12 no.6
• /
• pp.56-65
• /
• 2008

• 전기의세계
• /
• v.44 no.7
• /
• pp.24-28
• /
• 1995

현재 우리나라를 포함하여 개발도상국의 전력기기 생산 업체는 R&D 사업을 꾸준히 추진하여 왔으나, 기술력 부족과 연구 개발 과정에서 필요로 하는 연구시험설비의 부족으로 자체 기술개발은 거의 불가능하였다. 그 결과 선진 기술을 도입하여 모방하는 수준에 머무르고 있었으며, 진정한 의미의 연구개발은 현실적으로 어려운 실정이다. 이러한 현실을 극복하고 자체기술로 기기개발을 유도하여 경쟁력 우위를 꾸준히 확보하기 위해서는 끊임없는 연구노력이 필요하며 이를 뒷받침 할 연구시험회로 건설은 필연적이라 하겠다. 우리나라 유수의 전력기기 제조업체에서도 1) 자체기술로 고유 모델기기를 개발하여 경쟁력 우위를 지속적으로 확보하고, 2) 개발 완료 단계의 제품으로 타 기관, 타 회사의 시험 설비를 이용한 종합적인 성능평가보다, 개발과정에서 기기특성을 정확히 파악하여 인적 물적 손실을 최소화하고, 3) 기 개발된 제품의 품질개선, 원가절감을 꾸준히 이룩하기 위하여 건설 되어야 할 단락 연구시험회로에 대하여 살펴보기로 한다.

• 월간 기계설비
• /
• s.246
• /
• pp.58-71
• /
• 2011

건축물 외벽에 노출해 설치토록 유지해 온 국내 도시가스사업법 가스배관 설치기준의 개정 논의가 본격화됐다. 한국가스안전공사는 지난 해 12월 16일 서울지역본부에서 정책 기술자문위원 8명이 참석한 가운데 '건축물 가스배관 설치기준 개선 공동연구'에 대한 착수회의를 갖고 본격적인 개정작업에 돌입했다. 연구기간은 내년 2011년 10월까지 총 11개월이며 이 연구에는 한국가스안전공사, 한국가스학회, 한국건설생활환경시험연구원, (주)삼천리 등 4개 기관이 참여하여, 안전성 검증과 설치기준, 시공매뉴얼 등을 마련하게 된다. 한국가스안전공사의 '건축물 가스배관 설치기준 개선 공동연구' 추진은 그동안 대한설비건설협회 가스설비공사협의회(위원장 이효련)의 지속적인 건의사항으로, 이 연구가 마무리되면 앞으로 일본, 영국 등 선진국과 같이 가스배관의 건축물 내 매몰 시공이 가능해질 것으로 보인다.

• Proceedings of the KSME Conference
• /
• 2002.08a
• /
• pp.263-266
• /
• 2002

The KSR-III developed by KARI is the first rocket vehicle which is adopting the liquid propellant rocket engine system in Korea. Not only the engine itself, but also the propellant feeding system is one of the most important component in liquid rocket vehicle. In this paper, the authors are intended to introduce the multi-purpose test facility(PTA-II Test Facility) which is constructed for the variety of tests on KSR-III feeding system(single component tests, verification tests, cold flow tests and combustion tests). With the results of these tests, we can identify the characteristics of rocket feeding system and decide the optimum setting values of feeding system for the successful flight.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.18 no.5
• /
• pp.43-53
• /
• 2014

Shock tunnels are known to be capable of simulating flow-field environments of supersonic and hypersonic flights. They have been operated successfully world-wide for almost half a century. As a consequence of the strong interest in hypersonic vehicles in Korea, attention has been given on this type of facility and so an intermediate-sized shock tunnel has lately been built at KAIST. In the light of this, this paper presents our tunnel performance and some of the model scramjet test data. The freestream flow used in this work replicates a supersonic combustor environment for a Mach 5.7 flight speed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.627-630
• /
• 2009

Ejector system can induce the secondary flow or affect the secondary chamber pressure by both shear stress and pressure drop which are generated in the primary jet boundary. Ejectors are widely used in a range of applications such as a turbine-based combined-cycle propulsion system and a high altitude test facility for rocket engine, pressure recovery system, desalination plant and ejector ramjet etc. The primary interest of this study is to set up an configuration and operating conditions for an ejector in the condition of sonic and subsonic. Experimental and theoretical investigation on the sonic and subsonic ejectors with a converging-diverging diffuser was carried out. Numerical simulation was adopted for an optimal geometry design and satisfying the required performance. Also, some ejectors with a various of nozzle throat and mixing chamber diameter were manufactured precisely and tested for the comparison with the calculation results.