• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.41-44
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• 2007

Ground test facility for the hypersonic propulsion system was designed, constructed and performance test was conducted. The design point was selected using quasi，1-Dimensional CFD analysis before the conceptual design for construction of hypersonic facility After that, specific designs for performance and components were completed using unit analysis CFD code and performance tests were conducted for the various operation conditions.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.3
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• pp.87-99
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• 2001

Technical status and prospect of the subsonic airbreathing propulsion system composed of jet engine fuel feeding system and air intake for missile application is described herein, including analysis of some present airbreathing missiles. Comprehension on this can be applicable both to blow deeply about the same type missiles and to get some basic idea of unmanned air vehicle's and light aircraft's propulsion system.

• Journal of Advanced Marine Engineering and Technology
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• v.18 no.2
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• pp.1-17
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• 1994

잠수함추진방식은 크게 원자력 추진과 재래식 추진으로 나눌수 있다. 최근에는 재래식 추진방식과 하이브리드 개념으로 운용될 수 있는 AIP(Air Independent Propulsion)방식도 활발히 연구되고 있다. AIP추진으로는 폐회로 디젤기관추진(Closed Cycle Diesel Engine Propulsion), 연료전지추진(Fuel Cell Propulsion), 스터링기관추진(Stirling Engine Propulsion) 및 폐회로터빈추진(Closed Cycle Turbin Propulsion) 등이 있다. 이러한 잠수함 추진체계에 대해 앞으로 크게 세부분으로 나누어 그 현황과 발전추세를 살펴보고자 한다. 즉, 초기의 순수전기추진방식으로 불리는 재래식 추진체계, 재래식 추진방식의 한계를 극복하기 위해 최근 활발히 연구되고 있는 외기와 무관한 추진장치인 폐회로 추진체계, 그리고 궁극적으로는 에너지의 문제로 귀착되어 거의 무한대의 에너지원을 가지고 있는 원자력 추진체계로 구분하여 그 현황과 발전내용을 살펴 봄으로써 잠수함추진체계의 국내연구 개발방향정립에 조금이나마 보탬이 되었으면 합니다. 또한 차세대 추진장치로 불리는 전자유체 추진방식에 대해서는 한국박용기관 학회지 1993년 4월호 "박용전자유체(MHD) 추진장치"를 참조하시기 바랍니다.조하시기 바랍니다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.573-576
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• 2010

The propulsion systems such as upper stages of launch vehicles, orbiters, spacecrafts have to operate in the zero gravity environment. Because the flight condition where the vehicle undergoes is different from the normal gravity state, many studies have been being in progress. Fluid behavior in the zero gravity condition is differently shown in the normal gravity state because the importance of the intermolecular force, such as adhesion, cohesion, and surface tension is enlarged. In this paper, we investigate the characteristic of fluid behavior and describe effects and problems on the liquid propulsion system due to these fluid behavior. We also check which studies are in progress in order to solve these problems.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.79-82
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• 2005

The hybrid rocket has been known for over 50 years. It is safe and cheap but wasn't widely used for the deficit of low regression rate. However, the hybrid rocket propulsion system will replace a lot of fields of missiles, rockets and propulsion systems of launch vehicles with new development of paraffin based solid fuel composition

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.8
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• pp.695-701
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• 2016

Spacecraft propulsion system is a kind of rocket engine that has been developed from the end of 1950s for attitude control and orbit maintenance of satellite. Since the spacecraft propulsion system has to be used for a relatively long time, therefore, stability of propellant and life of thruster could be very important factor for propulsion system design. Recently, green propellant propulsion and all electrical propulsion system have became very important issue, and we also need a development according to well organized plan. In this paper, we will introduce the development status, key technologies and development prospect of spacecraft propulsion system.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.6
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• pp.81-90
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• 2015

In order to know the characteristics of the hypersonic air-breahting engine, high altitude and Mach number ground test is necessary. Therefore, high pressure and high temperature condition should be simulated to do ground test of the hypersonic air-breathing engine. In this paper, the hypersonic air-breathing engine ground test facility of the Korea Aerospace Research Institute was introduced and the composition and characteristics were described.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.402-405
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• 2009

Present review introduces the constant volume combustion (CVC)-based hypersonic propulsion system development program recently initiated by DARPA for the hypersonic cruse vehicle (HCV).

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.3
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• pp.70-77
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• 2014

In this paper, the development of unique model of the 2.75 inch rocket propulsion system is described. Recently developed korean 2.75 inch rocket propulsion system shows the improvement of a flame stability resulted from a change in the configuration of propellant grain, and of an incidental ignition protection function using the EMI(electromagnetic interference) filter on ignition system. Moreover it is shown that a directional flight stability is improved by increasing the number of fins and changing the nozzle configuration. Static firing test and thermal shock test were conducted for the validation before flight, and flight test of 210 rounds of rockets was conducted to verify the trajectory uniformity. In addition, intellectual property issues can be overcome with the unique korean 2.75 inch rocket motor as well as the performance improvement.

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