• Journal of Aerospace System Engineering
• /
• v.11 no.5
• /
• pp.56-64
• /
• 2017

A high altitude long endurance aircraft which carries out missions of environmental research communication relay or ground surveillance, should have the capacity to cruise in the stratosphere at a relatively low speed for a long dwell time without the necessity of refueling. When one considers the propulsion system for such an aircraft, a reciprocating engine with a serial turbo-charger system to boost rarefied ambient air up to sea level condition, would represent an good, informed and practical choice regardless of the cruising altitude of the aircraft. In this paper, high altitude long endurance aircraft developed by overseas research groups and research trends, regarding multi-stage turbocharger systems, are introduced.

• Journal of the Korean Institute of Gas
• /
• v.10 no.4 s.33
• /
• pp.41-46
• /
• 2006

A study was conducted to investigate the problem caused by the mechanical particles in LOX system during operating and testing propulsion system, especially concentrated on effects of contaminants accumulation and transfer in LOX system. Several methods for system operation decreasing accidents caused by oxidizer Beakage and contaminants accumulation was investigated. These methods can be applied to LOX system and other propellants system in liquid propellants propulsion system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.05a
• /
• pp.268-271
• /
• 2010

Hypersonic engine test facility with ejector system was tested. Ejector system was designed by revised EJSIMP code. The performance of the ejector system was predicted by numerical analysis. As a result, ejector system satisfied the facility design requirement. Based on the pressure level, the facility was successfully started at Mach 3.5 and 20km altitude condition.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.598-602
• /
• 2017

Korea Aerospace Research Institute has been developing 3-stage launcher KSLV-II, which can inject 1.5-ton satellite into sun synchronous orbit (SSO). For development process, Test Launch Vehicle(TLV) adopting the $2^{nd}$ and $3^{rd}$ stage of KSLV-II will be scheduled to launch in 2018. The propulsion system of TLV is composed of $2^{nd}$ stage engine system (ground type) and propellant supply system including LOX, Kerosene tanks. Until now, system integration of engineering model of TLV and delivery of qualification model have been done. In this paper, the product assurance activities for propulsion system KSLV-II will be illustrated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2000.11a
• /
• pp.17-17
• /
• 2000

초음속 비행체 및 극음속 성층권 비행체용 추진기관으로의 사용이 검토되고 있는 차세대 추진기관들을 산화제 공급방식에 따라 공기흡입 엔진, 로켓 엔진 및 복합사이클 엔진으로 분류하여 엔진의 구성방식 및 추진특성들을 기술하였다. 공기흡입 엔진은 저고도에서의 성능이 우수하고 재사용이 가능 하지만 공기 밀도가 낮은 고 고도 영역에서의 성능이 좋지 않으며 로켓 엔진은 넓은 고도영역에서 사용이 가능한 반면 낮은 비추력 및 고비용 발사체계 등과 같은 단점들을 가지고 있다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2000.11a
• /
• pp.8-8
• /
• 2000

하이드라진 단기액체엔진을 장착하고 궤도에서 임무를 수행하고 있는 다목적실용 위성 추진시스템 궤도비행 초기운용 자료에 근거하여 추진제 소모율을 산정 한다. 추진시스템은 위성의 궤도각과 비행고도 조정을 위한 속도증분($\Delta$V) 및 자세제어를 위한 추력을 발생시킨다. 단기액체 추진시스템에서 추진제 소모량은 추력기 밸브의 개폐시간에 비례하고 추력 생성 효율은 추진제의 연소기 유입압력에 종속한다. 일정질량의 가압 기체 압력에 의해 연료를 공급하는 추진시스템에서 잔류 추진제 량의 감소는 연소기 유입압력의 감소를 유발하고 추진기관의 효율을 저하시키는 요인으로 작용하여 임무말기로 진행함에 따라 동일한 운동량 생성에 보다 많은 연료소모가 이루어진다.(중략)

• Aerospace Engineering and Technology
• /
• v.3 no.2
• /
• pp.65-71
• /
• 2004

Development of space launch system is a national project which requires massive cost and endows the pride of the nation. To acquire the successful launch, the reliability of main system and components should be needed. In addition, reliable propulsion system sways the reliability of main system and is the necessary article for the success of project. In this study, the method called "design for reliability" is introduced, which is required to develop the highly reliable propulsion system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2003.10a
• /
• pp.31-34
• /
• 2003

To trace the working point of pressure-fed rocket propulsion system, direct analogy model was suggested, by which propellant mass flow rate and combustion chamber pressure were calculated from propellant tank pressures, levels and flight acceleration. In this paper, the analysis of KSR-III flight test results was taken by example, and it can be described that working point transition tendency of pressure-fed rocket propulsion system can be calculated by this direct analogy model.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1204-1204
• /
• 2017

• 한국IT서비스학회:학술대회논문집
• /
• 2005.05a
• /
• pp.205-214
• /
• 2005

보건복지부는 "보건복지 내부업무 포탈 및 EAM시스템 구축" 이라 명명된 Enterprise Portal 프로젝트를 공공기관 최초로 추진하여 기존의 정보시스템들이 업무 및 지식 기반 하에 유기적으로 상호 연계 및 연동되는 체계적이고 확장성이 뛰어난 포탈시스템으로 구축하였다. 본 논문에서는 보건복지부 정보화 비전 및 추진 현황에 대한 설명과 EP(Enterprise Portal)시스템 도입의 개념 및 장점에 대해 기술하고, 보건복지부가 Enterprise Portal 시스템을 도입하게 된 추진 배경과 기존 시스템(전자결재, 지식관리, 문서관리, 커뮤니티, 게시판, 검색)에 어떻게 적용하였는지에 대해 설명하고자 한다. 아울러 Enterprise Portal 시스템의 적용으로 인한 실제적 효과 및 고려해야 할 문제점에 대해 기술함으로써 향후 Enterprise Portal 시스템을 도입하고자 하는 공공기관/기업체에 추진 방안 및 대응 방안을 제시하고자 한다.