• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.371-375
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• 2006

A computational work has been performed to investigate the aerodynamics of a projectile which is launched from a ballistic range. A moving coordinate method for a multi-domain technique is employed to simulate unsteady projectile flows with a moving boundary. The variation of a virtual mass and the shape of projectile are added to the axisymmetric unsteady Euler equation systems. The present computational results properly predict the velocity, acceleration, drag histories and the major flow characteristics of the projectile.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.6
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• pp.567-575
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• 2011

The development of space launch vehicle is an important step to advance to developed countries in the space area. It is also so risky due to necessity of huge costs and longer development period. The accuracy of cost estimation is important to develop a space launch vehicle successfully and efficiently. It is also necessary to estimate production and operation cost in order to develop commercial space launch vehicle possessing competitiveness. In this paper, Korean factors to be able to reflect the current state of workforce, average working hours and technology readiness level in Korea were analyzed to estimate production and operation cost of space launch vehicles that are developed in Korea. Korean factors have been applied to production and operation cost estimation of KSLV-II based on TRANSCOST. We evaluated the competitiveness level of KSLV-II as the commercial launch vehicle in the commercial launch services market by comparing with cost per flight of foreign launch vehicles.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.26-29
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• 2017

KARI has been conducting R&D for independent development of KSLV-II since 2010. Vehicle holding device is a device for vertically standing SLV on the launch pad of launch complex and fixing the lower part of vehicle in order to firmly fix vehicle so that SLV does not fall from an external load such as a wind load. When thrust generated after the 1st stage engine ignition of SLV must exceed the takeoff weight of vehicle, and holding device should be quickly released so that it does not interfere with takeoff of vehicle like other ground equipment at the beginning of the launch. Pyro-valve is one of the key components constituting VHD, and it should have high reliability and quick response characteristics with similar functional parts applied to launch vehicle separation device and satellite separation device. Through this paper, I intend to broaden the overall understanding of the development process of pyro-valve for VHD and KSLV-II.

• Defense and Technology
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• no.8 s.150
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• pp.36-39
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• 1991

일본의 우주개발 사업기구로는 우주개발사업단(NASDA)과 통신.방송위성기구 등이 있다. NASDA는 준 정부기관으로 우주개발활동을 책임지고 있으며, N-I 우주발사체 개발에 이어 1987년에 N-II 발사체의 개발을 성공적으로 수행하였다. NASDA는 1990년대 후반에 소요될 대용량의 인공위성발사 및 점증하는 우주개발활동에 사용하기 위해 차세대 발사체로서 결제적이며, 신뢰도가 높은 H-II 발사시스템을 개발하고 있다

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.154.1-154.1
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• 2012

조립 완료된 엔진시스템을 발사체 스테이지에 장착하기 위한 제반 사항에 대한 프로세서의 개념을 정리하였다. 엔진을 발사체 스테이지에 장착함에 있어서 주의해야 할 안전규칙, 다음으로 엔진을 이송하고 발사체 스테이지 조립장에서의 포장 해제, 입고 검사, 보존 방법 등 엔진을 스테이지에 장착하기 이전의 준비단계로 엔진 장착 준비 단계, 이후 엔진을 장착하는데 필요한 요구조건과 과정중에 수행되는 시험인 기밀시험, 전기 시험 등에 대한 내용이 포함된 엔진 장착 단계, 또한 엔진을 스테이지로부터 분리해야 할 경우 따라야 할 개괄적인 절차를 포함한 엔진 탈거 및 보관 과정에 대한 내용을 포함한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.2
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• pp.138-151
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• 2018

In this study, development information and technologies for reusable launch vehicles were surveyed. We investigated the reusable launch vehicles developed in various countries and analyzed their recovery technologies. In particular, we focus on the technologies of the Falcon 9 of SpaceX and the New Shepard of Blue Origin, which have succeeded in several flight experiments. Moreover, we explain the control algorithms for each flight condition. Finally, we discuss the reusable technologies that can be applied to the Korean Space Launch Vehicle to reduce the launch cost.

• Aerospace Industry
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• s.107
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• pp.24-25
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• 2010

최근 나로호 발사 실패와 천리안 발사 성공 등 국내 우주개발에 희비가 엇갈렸다. 특히 자력 발사로 관심을 모았던 나로호 발사가 실패하면서 온 국민은 우주개발에 대한 어려움을 다시 한번 실감했다. 이번호에서는 국내 위성 및 발사체 개발현황을 살펴본다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.86-89
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• 2005

A computational work has been performed to investigate the aerodynamics of a projectile which is launched from the two-stage light gas gun. A moving coordinate method for a multi-domain technique is employed to simulate unsteady projectile flows with a moving boundary. The effect of a virtual mass is added to the axisymmetric unsteady Euler equation system. The computed results reasonably capture the major flow characteristics which we generated in launching the projectile supersonically, such as the interaction between the shock wave and the blast wave, the interaction between the vortical flow and the barrel shock, and the steady under-expanded jet. The present computational results properly predict the velocity, acceleration, and drag histories of the projectile.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.192-198
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• 2005

SI(System Integration) process in KSLV-I development project is integrate whole assemblies which was submitted to system integration supervising team to one complete launch vehicle with proper quality control through test and verification and launch KSLV-I. It is not a one or a few teams' separate job but overall comprehensive job which request all related function group and manufacturing companies' voluntary cooperation. This paper was intended to provide entire SI process outline to whole related function groups and manufacturing companies for better cooperation in SI process and will be revised through continuos discussion among SI supervising group, whole function groups and manufacturing companies.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.157-164
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• 2007

For a GPS antenna to normally receive GPS satellite signals during full flight mission of a satellite launch vehicle, it should be installed on skin of the vehicle. The surface of a launch vehicle is drastically heated up due to aerodynamic heating effect during flight, so that the GPS antenna mounted on surface of the launch vehicle is directly exposed to extremely hot temperature environment. Hot temperature test specification of the GPS antenna, therefore, is severer than inner components. This paper describes that procedures and results of performance analysis of the GPS antenna for KSLV-I under hot temperature environment. The GPS antenna was not deformed physically and inner LNA(Low Noise Amplifier) operated normally without performance degradation.