• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.1-6
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• 2004

One of the mechanical system engineer's tasks of satellite design and development is to make the control plan, keep track and estimate the characteristics of system mass properties. As the design phases are going on, mass properties related activities also transit as like a data collection, system mass property estimation and measurement. Fidelity of mass properties database should be confirmed through measurement test. In this paper the control plan and estimation of system mass properties are explained by the actual data and experience of the development of satellite and the fidelity of mass properties database was confirmed through measurement test.

• Journal of Astronomy and Space Sciences
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• v.20 no.4
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• pp.375-382
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• 2003

One of the mechanical system engineer's tasks of a satellite design and development is to make the control plan, keep track and estimate the characteristics of system mass properties. As the design phases are go, mass properties related activities also transit as like a data collection, system mass property estimation and measurement. Fidelity of mass properties database should be confirmed through measurement test. In this paper the control plan and estimation of system mass properties are explained by the actual data and experience of the development of satellite and the fidelity of mass properties database was confirmed through measurement test.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.191.2-191.2
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• 2012

저궤도 위성을 설계함에 있어 시스템 수준에서 수행하는 질량특성의 계산은 위성을 구성하는 각각의 구성품에 대한 정보를 종합하여 전체 시스템의 특성을 예측하는 작업이다. 질량특성에 대한 요구조건은 발사체로부터 설정되는데 요구조건 항목은 탑재체질량, 무게중심 그리고 관성모멘트에 관한 것이다 또한, 자세제어면에서 추력에 의한 토크에 따른 무게 중심 등이며 최근 위성의 고기동화 요구에 따라 기동요구조건 및 자세구동장치의 용량에 따라 결정된다. 특히 위성의 궤도형상 관성모멘트는 위성 동특성을 표시하므로 이를 사용하여 제어시뮬레이션을 수행하는 자세제어계에 주요 입력 데이터로 활용된다. 본 논문에서는 저궤도 위성의 질량특성 요구조건을 검증하기 위해 수행한 질량특성 예측과 질량특성 측정 시험에 대해서 기술하고자 한다.

• Journal of the Earthquake Engineering Society of Korea
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• v.1 no.3
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• pp.29-35
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• 1997

The megastructure combined with the modular concept is an effcient structural system adequate for ultra-tail buildings for the future. An ingeneous structural control system can be developed by separating the internal subframe in one or many modules from the external megaframe, thus taking advantage of the effect of tuned mass dampers without adding any aditional mass. This so called mega-subcontrol system is generally modeled by a 20DF system for parametric study and for finding optimal values of the parameters. In this study the equation of motion for the system is obtained frist and the preconditions for the simplified modeling are investigated. Finally the optimal value for the subsreucture strffness is fomputed with given mass and damping ratios and transfer functions for responses are abtained for white noise ground exitation to verify the effectiveness of the mega-subcontrol system.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.28 no.5B
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• pp.475-483
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• 2008

2D finite element model for analysis of transport of accidentally released pollutants in the flow was developed by SUPG method, and the mass balance of this model was checked though two example problems: line source and point source problem in the straight channel and unidirectional 2D flow field, respectively. All the test cases were simulated with both SUPG and conventional Galerkin method to compare the accuraccy of the numerical mass balance. Test results show that the model with SUPG can adequately conserve the released mass though simulation than the model using Galerkin method, so the developed model verified to be appropriate to solve this accidental mass release problem.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.178.2-178.2
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• 2012

정지궤도위성은 발사체에서 위성이 분리된 이후 천이궤도로부터 원하는 목표궤도로 궤도전이를 해야 한다. 또한 임무기간동안 궤도상에서 다양한 교란을 겪게 되며 이로 인해 시간이 증가함에 따라 위성의 위치가 변화하게 된다. 정지궤도위성은 이러한 궤도전이 및 궤도상 위치변화를 제어하기 위한 추진시스템을 장착하고 임무기간에 걸쳐 요구되는 추진제를 탑재해야 한다. 위성의 설계 초기에는 추정되는 위성의 건조질량을 기반으로 하여 궤도전이와 궤도상 임무에 필요로 하는 추진제 버짓을 계산하고 이를 토대로 하여 위성 시스템 설계를 진행한다. 또한 발사체별로 발사체의 성능과 발사장에 따라 근지점고도와 발사 경사각이 모두 상이하므로 발사체가 정해지지 않은 상태에서 발사체별 추진제 버짓을 계산, 비교하고 추진 시스템의 탱크가 이를 모두 수용할 수 있는지 분석하는 것이 중요하다. 본 논문에서는 정지궤도복합위성의 추정 건조질량과 임무분석을 통해 주어진 ${\Delta}V$와 각 발사체별 궤도전이에 필요한 ${\Delta}V$를 바탕으로 하여 발사체별 추진제버짓을 계산하였고 이를 비교검토 하였다. 이후 이러한 기본 자료를 바탕으로 하여 정지궤도복합위성 추진시스템의 추진제 수용가능 여부, 건조질량 증가 여유 등 기본설계를 진행할 수 있다.

• Journal of Nuclear Fuel Cycle and Waste Technology(JNFCWT)
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• v.12 no.2
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• pp.135-151
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• 2014

It is very important to properly understand such "Transport Pathways" elements as "Pipe" and "Cell" pathways in commercial GoldSim Transport Module (GTM) for developing higer quality models and programs for performance assessment of complex radioactive waste repositories. With an illustrative case under an earthquake scenario, by which an increasement in the groundwater flow rate occurs though the geological medium, ways of avoiding possible modeling errors in the nuclide transport modeling in the radioactive waste repository system for its safety assessment by utilizing such pathways are discussed and a proper usage of the pathways is proposed.

• Journal of Energy Engineering
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• v.20 no.1
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• pp.30-35
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• 2011

To clarify the hydraulic and thermal characteristics of ice slurry which made from 6.5% ethylene glycol-water solution flow in the double tube and plate type heat exchanger, experimental studies were performed. The mass flux and ice fraction of ice slurry were varied from 800 to 3500 kg/$m^2s$(or 7 to 17 kg/min) and from 0 to 25%, respectively. Through the experiment, it was found that the measured pressure drop and heat transfer rate increase with the mass flux and ice fraction; however the effect of ice fraction appears not to be significant at high mass flux region. At the region of low mass flux, a sharp increase in the pressure drop and heat transfer rate were observed depends on mass flux.

• Korean Journal of Remote Sensing
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• v.37 no.6_2
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• pp.1793-1801
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• 2021

From 2015 to June 2020, the backscattering coefficients of 532 and 1064 nm measured using LIDAR and the depolarization ratio at 532 nm were used to separate the backscattering coefficient at 532 nm as three types as PM₁₀, PM_2.5-10, PM_2.5 according to particle size. The mass extinction efficiency (MEE) of three types was calculated using the mass concentration measured on the ground. The overall mean values of the calculated MEE were 5.1 ± 2.5, 1.7 ± 3.7, and 9.3 ± 6.3 m²/g in PM₁₀, PM_2.5-10, and PM_2.5, respectively. When the mass concentration of PM₁₀ and PM_2.5 was low, higher than average MEE was calculated, and it was confirmed that the MEE decreased as the mass concentration increased. When the MEE was calculated for each type according to the mixing degree of Asian dust, PM_2.5-10 was twice at pollution aerosol as high as 2.1 ± 2.8 m²/g, compare to pollution-dominated mixture, dust-dominated mixture, and pure dust of 1.1 ± 1.8, 1.4 ± 3.3, 1.1 ± 1.5 m²/g, respectively. However, PM_2.5 MEE showed similar values irrespective of type: 9.4 ± 6.5, 9.0 ± 5.8, 10.3 ± 7.5, and 9.1 ± 9.0 m²/g. The MEE of PM₁₀ was 5.6 ± 2.9, 4.4 ± 2.0, 3.6 ± 2.9, and 2.8 ± 2.4 m²/g in pollution aerosol (PA), pollution-dominated mixture (PDM), dust-dominated mixture (DDM), and pure dust (PD), respectively, and increased as the dust ratio value decreased. Even if the same type according to the same mass concentration or Asian dust mixture was shown, as the PM_2.5/PM₁₀ ratio decreased, the MEE of PM_2.5-10 decreased and the MEE of PM_2.5 showed a tendency to increase.

• Journal of the Korean Vacuum Society
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• v.3 no.2
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• pp.173-178
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• 1994

박막성장을 위한 초고진공 응용시스템을 제작하고 이것의 특성을 사중극질량분석계로 측정하였 다. 초고진공 시스템을 박막성장에 활용하기 위해서는 챔버 뿐만 아니라 펌프, 이온게이지, 전자총 등도 베이킹이 요구되었다. 또한 이온게이지와 전자총은 적어도 박막성장 20분전에 탈가스를 하여야함을 알 았다. 이 시스템으로 달성된 진공도는 7x10-11 torr이었다.