• 한국세라믹학회지
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• 제42권5호
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• pp.304-307
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• 2005

The possible configurations of hydroxyl group in hexagonal hydroxyapatite were identified through molecular orbital calculation. The molecular orbital interaction between O and H in hydroxyl column was analyzed using charge variation and Bond Overlap Population (BOP). We supposed 5 kinds of O-H bond configurations as cluster types of I, II, III, IV, and V. Mulliken's population analysis was applied to evaluate ionic charges of O, H, P, and Ca ions, and BOPs (Bond Overlap Populations) in order to discuss the bond strength change by the atomic arrangement. The stability of each O-H bond configuration was analyzed using bond overlap and ionic charge.

• 대한치과기공학회지
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• 제26권1호
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• pp.35-40
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• 2004

In order to understand alloying effects on the corrosion resistance of Ti-(10$\sim$20)%Zr-(2$\sim$8%)Nb-0.2%Pd alloys, Polarization curves were measured at 5%HCI solution. The results were interpreted in terms of two parameters obtained by the molecular orbital calculation ; one is the bond order($B_{\circ}$) and the other is the metal d-orbital level($M_{d}$). $B_{\circ}$ is a measure of the strength of covalent bonds between titanium and alloying elements. $M_{d}$ is correlative with the electronegativity of elements. It was found that increasing of Zr and Nb with higher $B_{\circ}$ values showed a lower critical anodic current density in the polarization curve and hence higher corrosion resistance. On the other hand, increasing of Zr and Nb with higher $M_{d}$ values showed a higher corrosion resistance.

• Journal of Astronomy and Space Sciences
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• 제31권3호
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• pp.199-204
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• 2014

This paper intends to highlight the effect of the third-body in an inclined orbit on a spacecraft orbiting the primary mass. To achieve this goal, a new origin of coordinate is introduced in the primary and the X-axis toward the node of the spacecraft. The disturbing function is expanded up to the second order using Legendre polynomials. A double-averaged analytical model is exploited to produce the evolutions of mean orbital elements as smooth curves.

• Bulletin of the Korean Chemical Society
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• 제15권8호
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• pp.658-662
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• 1994

Ab initio and extended Huckel calculations have been applied to discuss the electronic structure, ring inversion barrier, and geometry of the $Cp_2TiS_3$ compound. The deformation of four membered ring in the planar geometry is originated from a second-order Jahn-Teller distortion due to the small energy gap between HOMO and LUMO on the basis of extended Huckel calculations. The puckered $C_s$ geometry is stabilized by the interaction of the $x^2-y^2$ metal orbital with the hybrid orbital in sulfur. Ab initio calculations have been carried out to explore the ring inversion process for the model $Cl_2TiS_3$ compound. We have optimized $C_s$ and $C_{2v}$ structures of the model compound at the RHF level. The energy barriers for the ring inversion are sensitive to the used basis set. With 4-31$G^*$ for the Cl and S ligands, the barriers are computed to be 8.41 kcal/mol at MP2 and 8.02 kcal/mol at MP4 level.

• Journal of Astronomy and Space Sciences
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• 제17권1호
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• pp.107-116
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• 2000

본 연구는 지구 공전 궤도 근처의 Leonid의 출현 빈도와 속도 등을 예측하기 위한 연구의 초기 단계로서 meteoroid에 대한 기초 자료 조사와 더붙어 기존에 알려져 있는 meteoroid 입자의 분출 속도 모텔과 섭동 모델로부터 meteoroid의 운동 방향과 속도를 컴퓨터로 계산하기 위한 프로그램을 개발하고 이것을Leonid stream에 적용해 보았다. 입자의 초기 속도 모델로는Jones의 분출속도 분포모델을 사용하였으며, meteoroid의 궤도 운동 모델에는 태양과 달, 지구를 비롯한 각 행성들의 섭동 모델이 포함되었다. 태양계 천체들의 Ephemeris를 구하기 위해 JPL (Jet Propulsion L Laboratory)의 SSD (Solar System Dynamics) Laboratory에서 개발된 DE405 Solar System E Ephemeris 데이터 파일을 사용하였다. 이외에 중요한 섭동 요소로써 태양 복사압을 고려하였으며, 적분 알고리즘으로는 8차 Runge-Kutta 방법을 사용하였다.

• 대한원격탐사학회지
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• 제15권2호
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• pp.119-130
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• 1999

현재 전 세계적으로 많은 위성관제 및 위성영상데이터 수신처리 지상국에서 저궤도 위성의 추적 및 위성과의 통신을 위하여 NORAD 궤도데이터를 사용하고 있다. 공신력있는 북미우주방위사령부(NORAD)에서는 거의 매일 주기로 수천개의 지구 주회 물체를 관측하여 그 궤도데이터를 인터넷을 통해 전 세계로 공개하고 있으며, 이 데이터를 사용한 위성 궤도 예측은 지상국에서 위성과 통신하기에 충분한 추적정확도를 제공한다. 하지만 고해상도 지구관측 위성의 임무수행을 위해서는 위성의 위치결정 정확도의 중요성 때문에 평균 궤도정보인 NORAD 데이터를 사용하는 대신 자체 위성 관측 및 추적시스템을 운영한다. 우리별 3호의 지상국인 경우 자체 위성 추적시스템이 없는 관계로 위성과의 통신 뿐 아니라 영상촬영 및 처리를 위한 궤도정보를 NORAD 데이터에 의존하고 있다. 본 논문에서는 이러한 NORAD 데이터를 이용하여 위성의 위치를 예측 또는 결정함으로써 고해상도 지구관측 위성이 원하는 지역을 얼마나 정확히 촬영할 수 있는지, 그리고 생성되는 영상 카탈로그의 위치는 실제 촬영된 위치와 얼마나 달라질 수 있는지를 실험, 분석한다.

• 한국해안해양공학회지
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• 제4권4호
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• pp.187-200
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• 1992

Taylor 정리를 이용하여 평균위치에서의 Eulerian유속으로부터 수립자의 시간에 따른 Lagrangian 운동궤적을 결정하는 방법이 제안되었다. 이 방법을 Stokes 유한진폭파이론에 적용하여 고차 파성분을 포함하는 수립자의 운동궤적과 질양이동속도를 결정하였다. Stokes 5차파이론의 적용 결과, 평균위치에서의 Eulerian 유속으로부터 결정한 수립자의 운동궤적은 자유수면 부근을 제외하고는 5차파이론에 의한 순간속도에 의해 계산된 값과 매우 좋은 일치를 보여주었다. Stokes 5차파 이론에 의한 질양이동속도는 종전의 2차파이론에 의한 질양이동속도보다 전수심에서 작은 값을 보여준다.

• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2006년도 International Symposium on GPS/GNSS Vol.1
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• pp.141-144
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• 2006

The deviations in the injection orbital parameters, resulting from launcher dispersions, need to be estimated and used for autonomous satellite operations. For the proposed small satellite mission of the university there will be two GPS receivers onboard the satellite to provide the instantaneous orbital state to the onboard data handling system. In order to meet the power requirements, the satellite will be sun-tracking whenever there is no imaging operation. For imaging activities, the satellite will be maneuvered to nadir-pointing mode. Due to such different modes of orientation the geometry for the GPS receivers will not be favorable at all times and there will be instances of poor geometry resulting in no output from the GPS receivers. Onboard the satellite, the orbital information should be continuously available for autonomous switching on/off of various subsystems. The paper presents the strategies to make use of small arcs of data from GPS receivers to compute the mean orbital parameters and use the updated orbital parameters to calculate the position and velocity whenever the same is not available from GPS receiver. Thus the navigation message from the GPS receiver, namely the position vector in Earth-Centered-Earth-Fixed (ECEF) frame, is used as measurements. As for estimation, two techniques - (1) batch least squares method, and (2) Kalman Filter method are used for orbit estimation (in real time). The performance of the onboard orbit estimation has been assessed based on hardware based multi-channel GPS Signal simulator. The results indicate good converge even with short arcs of data as the GPS navigation data are generally very accurate and the data rate is also fast (typically 1Hz).

• 한국광학회:학술대회논문집
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• 한국광학회 2004년도 하계학술발표회
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• pp.58-59
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• 2004

• Journal of Astronomy and Space Sciences
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• 제12권2호
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• pp.265-274
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• 1995

The purpose of perigee kick motor firing is to place a satellite into transfer orbit and that of apogee kick motor firing is to place the satellite into geosynchonous orbit in order to increase the semi-major axis of the transfer orbit and reduce the inclination of the transfer orbit. Because apogee motor firing is always accompanied with injection errors, the satellite is not placed into geosynchonous orbit but into a near-geosynchonous orbit, also knows as a drift orbit. Thus, the orbital maneuver to correct drift orbit into gteosynchonous orbit is required, this maneuver is called the station acquisition. For reduction of expenditure and performance of mission, we estimate $\Delta$V budget and required fuel allowance for station acquisition. As the uncertainty of drift orbit by injection error of perigee and apogee kick motor firing prevents us from obtaining exact $\Delta$V budget, statistical Monte Carlo simulation technique is used in order to get optimal $\Delta$V budget and required fuel allowance with a probability of 99%. With respect to Korea satellite launched by Delta-2 launch vehicle in 1995, Monte Carlo analysis is used in order to get various orbital parameters, $\Delta$V budget and required fuel allowance for station acquisition with a probability of 99%.