• Journal of Aerospace System Engineering
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• v.18 no.3
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• pp.27-33
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• 2024

According to the success of the Nuri Space Launch Vehicle (KSLV-II) and the development goal of the next generation space launch vehicle (KSLV-III), it is expected that the domestic geostationary satellite capability will be increased from (1 to 3.7) ton. Also, it is predicted that substantial ability of about 1 ton can be provided for the space exploration of the Moon, Mars, asteroids, etc. The Goheung space launch site is optimized for sun-synchronous small satellites, and due to the essential precondition that the launch trajectory does not impinge another country's sovereign airspace, it is not satisfactory as a geostationary satellite launching site. Its latitude also requires more energy to shape the rotating orbital plane from the initial injection status. This results in a decreasing factor of economic feasibility, including the operating complexity. Therefore, in parallel with the development of a next generation space launch vehicle, the practical process for acquisition of oversea land or sea space launch site near the Earth's equator and research for the optimization of orbiting methods of geostationary satellite injection must be continued.

• Proceedings of the Optical Society of Korea Conference
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• 2003.02a
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• pp.98-99
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• 2003

2005년 국산 소형위성 발사체에 탑재되어 발사 될 예정으로, 과학기술위성2호의 개발이 2002년 10월부터 시작되었다. 과학기술위성2호는 약 100kg의 소형위성으로, 경사각 60～80$^{\circ}$의 300km x 1500km 타원궤도에 발사될 것으로 예상되고 있으며, 라만-a태양촬영망원경(LIST, Larman-a Imaging Solar Telescope)과 레이저정밀거리측정용 반사경이 각각 주 및 부 탑재체로 탑재될 예정이다. 위성레이저정밀거리측정(SLR, Satellite Laser Ranging)이란 위성간의 거리를 가장 정확하게 측정할수 있는 축지학적 기술이다. (중략)

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.2
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• pp.35-42
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• 2020

Recently the reusable launch vehicle is being a major trend in the worldwide space market, because a few commercial companies, especially SpaceX, are trying to cut down the launch price through developing and succeeding the reusable launch vehicles. However, there is still a big controversy about whether in view point of the launch cost which is more favorable between expendable and reusable. Therefore, a study and close examination is required for the launch cost in the early development phase of the reusable launch vehicle. In this study the sensitivity analysis is performed with respect to the major cost parameters which have great effects on the launch cost and price. The standard vehicle of this sensitivity analysis is the expendable vehicle having a payload 20 tons. The cost estimation relationships used in this calculation are referred from the commonly proven cost models such as TRANSCOST. The major cost parameters chosen in this study are as follows: development cost, production cost, refurbishment cost, and maximum reusable number.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.4
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• pp.106-113
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• 2002

In spacecraft system, structure subsystem has the mission of supporting all the components safely under various space environmental conditions. The safety of spacecraft structure is finally verified from the coupled load analysis, which is a branch of load analysis which combines the launch vehicle and satellite. This study introduces the optimization algorithm to reduce the weight of spacecraft structure under launch environmental conditions directly. The acceleration responses are obtained by the introduction of coupled load analysis, which lead to check the failure of spacecraft structural members. The results show a 12% saving of structural weight and this saving is mainly driven by the thickness of honeycomb core, which strongly affects the natural frequencies of platforms and panels.

• Journal of Space Technology and Applications
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• v.2 no.2
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• pp.67-80
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• 2022

The missile early-warning satellite systems have been developed and upgraded by some space-developed nations, under the inevitable trend that the space is more strongly considered as another battle field than before. As the key function of such a satellite-based early warning system, the prediction algorithm of the missile flight trajectory is studied in the paper. In particular, the evolution computation, receiving broad attention in the artificial intelligence area, is applied to the proposed prediction method so that the global optimum-like solution is found avoiding disadvantage of the previous non-linear optimization search tools. Moreover, using the prediction simulator of the launch vehicle flight trajectory which is newly developed in C# and Python, the paper verifies the performance and the feature of the proposed algorithm.

• Journal of Korea Technology Innovation Society
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• v.3 no.2
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• pp.61-77
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• 2000

우리 나라는 90년대에 들어서 향후 2015년까지 세계 10위권의 선진우주국에 진입한다는 우주개발중장기목표를 설정하고 중간 추진단계로서 2005년까지 국내기술에 의한 저궤도위성 및 발사체를 개발한다는 목표를 세우고 있다. 그리고 이를 위한 구체적인 시행 프로그램으로서 KSR-I및 KSR-II사업을 추진하여 성공적으로 완료하였으며, 이제 2002년까지 KSR-III사업으로 3단형 액체추진로켓을 개발 중에 있다. 현재 세계 우주 발사체 시장은 저궤도위성의 수요가 급증함으로서 전 세계적으로 저가의 우주발사체 개발을 서두르고 있으며, 우주선진국들은 경쟁적으로 기술혁신을 추진하고 있다. 그러나 개발도상국가들이 이에 참여하는데 있어서는 G7선진국들이 이미 마련한 MTCR(Missile Technology Control Regime)규제에 의거 기술이전 및 부품수입이 어렵기 때문에 자력에 의한 발사체 개발이 불가피하다. 본 고에서는 우주발사체 주요 선개발국 8개국의 기술혁신 과정과 정책 및 추진체계 등을 분석하고, 국내 발사체 개발에 참여하고 있는 주요 7개 민간기업을 대상으로 실시한 설문조사와 현장 실태조사를 바탕으로 기술혁신을 촉진하는 구체적인 정책대안 및 목표년도에 성공적인 발사를 위한 개선방안을 제시하였다.

• The Proceeding of the Korean Institute of Electromagnetic Engineering and Science
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• v.22 no.3
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• pp.3-16
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• 2011

천리안 위성은 4개 정부 부처 공동 사업으로, 통신 서비스, 해양 기상 관측 서비스 제공을 목적으로 개발된 복합 위성으로, 그중 통신 서비스를 담당하는 통신 탑재체는 방송통신위원회 출연으로 한국전자통신연구원(ETRI)가 주관, 개발하여 성공한 순수 국산 개발품으로, 위성 발사 성공 후 시험 검증을 거쳐 현재 정상 운용 중에 있다. 우주 인증 획득을 목적으로 개발한 통신 탑재체는 위성 스위칭 중계기와 다중 빔 안테나로 구성되었으며, 구성 부품들인 능동 부품과 수동 부품들은 대부분 국내 연구진에 의해 설계, 제작 시험 검증되어 중계기 및 안테나 시스템 종합화, 통신 탑재체 및 위성체 우주 환경 시험을 성공적으로 수행되었다. 위성 발사 성공 후에, 정지 궤도상에서의 통신 탑재체 궤도내 시험을 완료를 통해 순수국산 개발된 통신 탑재체의 설계 제작 기술에 대한 정지 궤도 우주환경에서도 정상 동작됨을 입증하였다. 통신 탑재체는 다양한 우주 조건에서의 다양한 기술 확보와 차세대 멀티미디어 위성 서비스 개발에 활용하고자 한다. 본 논문은 통해기 통신 탑재체 설계 제작 시험 기술을 소개하고, 활용 계획에 대해 언급하고자 한다.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.198-203
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• 2010

KSLV-I, a.k.a. Naro is the 1st Korean satellite launch vehicle, which was launched at Naro space center by Korea Aerospace Research Institute (KARI) in AUG. 2009, and JUN. 2010. Although the missions of 1st and 2nd launch of KSLV-I - inject the space craft into the designated orbit - were not successful, safety of launch vehicle was accomplished through the cooperation with the Russian partner Khrunichev Space Research and Production Center (KhSC). Both parties co-developed the safety management program to ensure launch safety. In this paper, the analysis and contents of safety program are illustrated.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.4
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• pp.1-9
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• 2019

Recently, in the space market, there has been a rapid reduction of the launch price. The major reason is that a few commercial companies, especially SpaceX, began to enter into the space market about ten years ago, which has changed the space market from monopolization to competition, and accelerated the adoption of commercial efficiency in the technology and management. Also, the successful landing and recovery of a first stage in 2016 by SpaceX proved to be a prelude to opening a new era of reusable launch vehicles, and SpaceX declared the groundbreaking launch price through using the reusable launch vehicle. This study calculates the total launch cost required to put a certain satellite into the LEO, compares the launch cost in three cases with different payload weights, and reviews the impacts of the payload on the cost effectiveness of a reusable vehicle. The total launch cost is divided into 6 subsections cost, namely development cost, production cost, refurbishment cost, operation cost, fixed-cost of factory and launch site, and insurance cost. The cost estimation relationships used in the calculation are taken from the commonly proven cost models such as TRANSCOST.

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.82-86
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• 2011

This paper presents an RF Electric field assessment at 2.290 [GHz] inside launcher PROTON M/Breeze M long fairings, produced by COMS TM. COMS intentional RE due to TM ON under fairing has been assessed considering PROTON M / BREEZE M fairing characteristics. As fairings of all launchers present similar sizes, a similar E-field level under fairing is expected for the other launchers. As a result, the RE level under faring is compliant with COMS RS limits, but is not compliant with RS requirements of the launcher PROTON M/Breeze M.