• Nuclear industry
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• v.16 no.10 s.164
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• pp.70-74
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• 1996

인접국의 핵실험, 원전 사고, 인공 위성 추락 등으로 인한 방사선 비상 사태를 조기에 탐지하여 신속히 대처하기 위한 환경 방사능 감시망이 아시아 지역 공동으로 구축될 전망이다. 한국원자력안전기술원은 최근 우리 나라를 비롯, 중국$\cdot$인도$\cdot$인도네시아$\cdot$파키스탄 등 5개국 대표들이 참석한 가운데 $\ulcorner$방사선 안전에 관한 아시아 지역간 협력체 구축을 위한 자문단 회의$\lrcorner$를 열고, 아시아 지역 환경 방사능 공동 감시망 구축을 위해 각국의 환경 방사능 시료의 효과 분석, 환경 방사능 기초 자료망 구성 등의 사업을 벌이기로 했다. 그 경위와 추진 계획 등을 살펴본다.

• The Science & Technology
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• v.30 no.11 s.342
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• pp.26-27
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• 1997

시중에 유통되고 있는 미국산 수입쇠고기에서 O-157대장균이 검출되어 한ㆍ미간 무역마찰이 일고 있다. 문제된 병원성 대장균 O-157은 소ㆍ돼지 등의 내장에 서식하는 병균으로 82년 미국에서 처음 발견됐다. 이번 O-157사건은 수입병원체와의 싸움의 시작에 불과하다. 앞으로 당국은 검역체계를 강화하는 등 적극적인 대처가 시급하다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2017.11a
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• pp.88-90
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• 2017

현재 한국해양과학기술원에서는 선박비행체 탑재용 복합센서를 개발 및 시험 적용 중에 있다. 그러나 얻어진 영상 데이터를 통해서는 목표물에 대한 정확한 위치 정보를 파악할 수 없다. 또한 크기가 큰 물체도 거리가 멀면 영상에선 작아 보이기 때문에 목표물의 크기 또한 파악하기 힘들다. 이를 보완하기 위해 본 연구에서는 복합센서를 통해 획득한 영상에 대해 warping 및 기하보정, 선박 및 익수자 자동 탐지 알고리듬, 위치 및 계수 정보 산출에 대해 소개한다. 또한 실제 실험을 통해 해당 알고리듬을 검증하였다.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.682-685
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• 2010

KSLV-I 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 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 technical safety management program to ensure launch safety. In this paper, the analysis and contents of safety program are illustrated.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.25 no.2
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• pp.320-326
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• 2021

AVTE(Air Vehicle Test Equipment) is an equipment to inspect and check the status of on-board aircraft LRUs(Line Replacement Units) before and after flight for performing successful UAV(Unmanned Aerial Vehicle) missions. This paper suggests utilization of the AVTE as an operation support-equipment by implementing several critical functions for UAV-operation on the AVTE. The AVTE easily sets initialization(default) data and compensates for the installation and position errors of the LRUs which provide critical mission data and situation image with pilots without additional individual operation support-equipment. Major fault list and situation image data could be downloaded after flight using the AVTE in the event of UAV emergency situation or unusual occurrence on duty as well. We anticipate the suggested operational approach of the AVTE could dramatically reduce the cost and man power for design and manufacture of additional operation support equipment and effectively diminish workload of the operator.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.229-235
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• 2008

The ground flight termination system(GFTS) could be used for the termination of launch vehicle in flight motion when the launch vehicle deviates from the designated route due to the system malfunction or failure as well as the launch vehicle can't be tracked by the ground tracking system. This paper introduces the basic concept and design of the ground flight termination system to be used for KSLV launch mission in NARO space center. In order to design the optimal ground flight termination system for KSLV launch application, the operational concept reflected on the flight trajectory and system characteristics of KSLV launch vehicle should be considered. Moreover the RF link budget analysis, and the analysis for system availability and reliability are done. Based on the analysis above, the each subsystem of ground flight termination to transmit the termination signal in stable is designed for KSLV launch mission.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.6
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• pp.455-466
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• 2020

In this study, we built a thermal model for SNIPE 6U nano-satellite which has scientific mission for measuring science data in near Earth space environment and described thermal design based on the thermal model. And the validity of the thermal design was verified through the on-orbit thermal analysis. The thermal design was carried out mainly on the passive thermal control techniques such as surface finishes, insulators, and thermal conductors in consideration of the characteristics of the nano-satellite. However, the components with narrow operating temperature range and directly exposed to the orbital thermal environments, such as a battery and thrusters, are accomodated with heaters to satisfy the temperature requirements. On-orbit thermal analysis conditions are based on the basic orbital conditions of the satellite, and thermal analysis was performed for Normal mode, Launch & Early Orbit Phase (LEOP), Safehold mode, and Maneuver mode which are classified by the power consumption and the attitude of the satellite according to the mission scenario. The analysis results for each mode confirmed that every component satisfies the temperature requirement. In addition, the heater capacity and duty cycle of the battery and thruster were calculated through the analysis results of the Safehold mode.

• Journal of Korean Medical classics
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• v.19 no.2 s.33
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• pp.46-52
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• 2006

${\ulcorner}$황제내경(黃帝內經)${\lrcorner}$ 내함한의학이론(內含韓醫學理論) 기중삼응삼양적내용비상난(其中三陰三陽的內容非常難) 기원인사(其原因是)${\ulcorner}$황제내경(黃帝內經)${\lrcorner}$ 중삼음삼양적내용비상복집(中三陰三陽的內容非常複雜), 특별시삼음삼양적시간배속매편화일양(特別是三陰三陽的時間配屬每篇不日樣) 본론문통과관우(本論文通過關于子) ${\ulcorner}$황제내경(黃帝內經)${\lrcorner}$ 중삼음삼양적시간배속진행연구(中三陰三陽的時間配屬進行硏究), 득출여하결론(得出如下結論), 운기지주기순서춰시오행(목화토금수)순서(運氣之主氣順序就是五行(木火土金水)順序), 저설명주기변화주요근거형지변화(這說明主氣變化主要根據形之變化), 운기지객기순서취시기지대(運氣之客氣順序就是氣之大小)(일양(一陽)${\longrightarrow}$이양(二陽)${\longrightarrow}$삼양(三陽)${\longrightarrow}$일음(一陰)${\longrightarrow}$이음(二陰)${\longrightarrow}$삼음(三陰))${\longrightarrow}$, 저설명객기변화주요근거기지변화(這說明客氣變化主要根據氣之變化) ${\ulcorner}$소문맥해(素問脈解)${\lrcorner}$ 적삼음삼양월별배속시음관(11월:태음)(的三陰三陽月別配屬是陰關(11月:太陰)${\longrightarrow}$양관(1월:태양)(陽關(1月:太陽)${\longrightarrow}$음합(3월:궐음)(陰闔(3月:厥廠)${\longrightarrow}$양합(5월:양명)(陽闔(5월:陽明))${\longrightarrow}$음추(7월:소음)(陰樞(7月:少陰)${\longrightarrow}$양추(9월:소양)(陽樞(9月少陽). 태양소음시음양세력적기초(太陽少陰是陰陽勢力的基礎), 소이상위표리(所以相爲表裏). 소양소음시음양세력적중간(少陽少陰是陰陽勢力的中間), 소이사위표리(所以杞爲表裏) 태음궐음시음양세력적전성기(太陰歐陰是陰陽勢力的全盛期), 소이상위표리(所以相爲表裏) 차료리적의사반영경락류주(此表養的意思反映經絡流注). 태음양명경류주신체전면(太陰陽明經流注身體前面), 태양소음경류주신체후면( 太陽少陰經流注身體後面 ), 소양궐음경류주신체측면(少陽厥陰經流注身體側面). ${\ulcorner}$령추경맥(靈樞經脈)${\lrcorner}$적12경맥류주순서시태음양면경(的12經脈流注順序是太陰陽明經)${\longrightarrow}$소음태양경(少陰太陽經)${\longrightarrow}$궐음소양경적표리경락위주(厥陰少陽經的表裏經絡爲主). 수선매기류주태음양명경적이유(首先脈氣流主太陰陽明經的理由), 취시후천수곡정미화호흡대기결합이형성경맥지기(就是後天水穀精微和呼吸大氣結合而形成經服之氣). 지후맥기류주소음태양경(之後脈氣流注少陰太陽經), 설명순행태음양명경적후천영양물질전입한열경락이위신(說明盾行太陰陽陽明經的後天營養物質轉入寒熱經絡而爲寫薪), 기차맥기순해궐음소양경적(其次脈氣盾行厥陰少陽經的), 인위한열경락지화기피궐음소양경지풍기조절이후조절조습경락(因爲寒熱經絡之火氣被厥陰少陽經之風氣調節而後調節操濕經絡), 비여작반시(比如作飯時), 화기취시소음태양경(火氣就是少陰太陽經), 풍기취시궐음소양경(風氣就是厥陰少陽經), 정내지반취시태음양명경.(鼎內之飯就是太陰陽明經). ${\ulcorner}$령추음양계일월(靈樞陰陽緊日月)${\lrcorner}$ 적삼음삼양월별배속주요시추관합합관추순서(的三陰三陽月別配屬主要是樞關闔闔關樞順序). 저양배서적원인시개문화관문과정(這樣排序的原因是開門和關門過程). 재춘하(在春夏), 양경락지맥기여개문관문과정(陽經絡之脈氣如開門關門過程), 수착추관합합관추순서순행(隨看樞關闔闔關樞順序盾行), 재추동(在秋冬), 음경락지맥기여개문폐문과정(陰經絡之脈氣如開門閉門過程), 수착추관합합관추순행(隨看樞關闔闔關樞盾行).

• Journal of the Korea Concrete Institute
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• v.27 no.2
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• pp.103-113
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• 2015

This paper studies impact performance of wire-mesh and steel fiber-reinforced concrete based on high-velocity impact experiments using hard spherical balls. In this experimental study, panel specimens were tested with various parameters such as steel fiber volume fraction, presence/absence of wire mesh, panel thickness, impact velocity, and aggregate size for the comparison of impact resistance performance for each specimen. While improvement of the impact resistance for reducing the penetration depth is barely affected with steel fiber volume fraction, the impact resistance to scabbing and perforation is improved substantially. This was due to the fact that the steel fiber had bridging effects in concrete matrix. The wire mesh helped minimizing the crater diameter of front and back face and enhanced the impact resistance to scabbing and perforation; however, the wire mesh did not affect the penetration depth. The wire mesh also reduced the bending deformation of the specimen with wire mesh, though some specimens had splitting bond failure on the rear face. Additionally, use of 20 mm aggregates is superior to 8 mm aggregates in terms of penetration depth, but for reducing the crater diameter on front and back faces, the use of 8 mm aggregates would be more efficient.