• Bulletin of the Korean Chemical Society
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• 제18권9호
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• pp.976-981
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• 1997

The magnetic susceptibilities of molybdenum ions with 4d1 electronic configuration in the octahedral crystal field were calculated on the basis of ligand field theory. The experimental magnetic susceptibilities for molybdenum ions, which are stabilized at the octahedral site in the perovskite lattice of Ba2ScMoⅤO6 and Sr2YMoⅤO6, were compared with the theoretical ones. We have tried to fit their temperature dependence of magnetic susceptibility with ligand field parameters, spin-orbit coupling constant ζSO, and orbital reduction parameter κ according to intermediate field coupling and strong field theory. Strong field coupling theory could not explain experimental curves without unrealistically large axial ligand field, since it ignores the mixing up between different state via spin-orbit interaction and ligand field. On the other hand, the intermediate field coupling theory could successfully reproduce experimental data in octahedral and trigonal ligand field. The fitting result demonstrates not only the fact that spin-orbit interaction is primarily responsible for the variation of magnetic behavior but also the fact that effective orbital overlap, enhanced by cubic crystal structure, reduces significantly orbital angular momentum as indicated by κ parameter.

• 한국항공우주학회지
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• 제32권3호
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• pp.45-50
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• 2004

위성의 성공적인 임무 수행을 위한 자세 안정화와 성능요구조건을 만족하기 위해서 반작용휠 제어로직의 설계가 중요하다. 실제 위성궤도 상에서 발생하는 여러 가지 불확실성으로 인해 지상실험을 통해 획득한 모델 파라미터 값들만으로 제어로직을 설계하는데 한계가 있다. 그러므로 위성이 궤도상에 있을 때의 반작용휠 입력 및 출력 데이터를 이용하여 모델 파라미터를 보정하고 자세제어기에 반영하는 것이 요구된다. 본 논문에서는 다목적실용위성의 Telemetry 데이터를 활용한 시스템인식 (System Identification)을 수행하였고, 이를 통한 반작용휠의 모델 파라미터를 추출한다. 또한, 반작용휠을 모델링 하고 또한 제어기설계에 사용된 모델 파라미터를 추출하여 지상실험 데이터와 비교분석한다.

• 천문학회보
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• 제36권2호
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• pp.93.2-93.2
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• 2011

Japan Aerospace Exploration Agency (JAXA) has measured space environment and its effects on spacecraft and astronaut since 1987. At present, we have operated space environment monitors onboard one GEO spacecraft, one QZO spacecraft, and two LEO spacecrafts. The obtained space environment data has been gathered into the Space Environment and Effects System database (SEES, http://sees.tksc.jaxa.jp/). In this presentation, measurement result of space environment in low earth orbit obtained by the Daichi satellite from 2006 through 2011 is reported as well as recent activities in space environment engineerings in JAXA. The Technical Data Acquisition Equipment (TEDA) on board the Daichi satellite (Advanced Land Observing Satellite: ALOS) had been operated in low earth orbit at 700 km altitude with 98 degree inclination from February 2006 until April 2011. The TEDA consists of the Light Particle Telescope and the Heavy Ion Telescope. The operation period of the Daichi satellite was through the solar-activity minimum period. The space radiation environment around the Daichi satellite had been almost stable. However, large solar flares followed by CMEs sometimes disturbed the space radiation environment in the orbit of the Daichi satellite. In addition, high speed solar wind often flowed and modulated the electron flux in the horn region. On the other hand, a little variation was seen in the SAA region.

• 핵의학기술
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• 제16권1호
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• pp.3-7
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• 2012

심근관류 SPECT의 영상획득 방법에는 Body contour와 Circular 방식이 있고, 환자와 검출기 사이의 거리를 줄이기 위해 Body contour 방식을 주로 사용한다. 그러나 이중(Dual) 검출기 장비에서 수직방식으로 검출기를 설정하여 영상을 획득하는 경우에는 환자와 검출기 사이의 거리가 Body contour 방식이 Circular 방식에 비해 더 증가하는 경향이 있다. 본 연구의 목적은 이중 검출기 장비에서 수직방식으로 검출기를 설정하여 영상을 획득하는 경우, Body contour 방식과 Circular 방식에서 환자와 검출기 사이의 거리를 비교하고, 거리에 따라 영상에 미치는 영향을 파악하여 영상의 질을 높이기 위한 방안을 제시하고자 시행하였다. 실험에 사용된 장비는 GE INFINIA Gamma Camera와 Anthropomorphic torso 모형에 심장 모형을 삽입하여 영상을 획득하였고, 2011년 8월 본원에서 심근관류 SPECT를 시행한 환자 40명을 대상으로 하였다. 모형 제작은 실제 환자조건과 동일하게 하기 위하여 심근에 74 kBq (0.22 mCi)/cc, 폐에 2.59 kBq ($60{\mu}Ci$)/cc, 연부조직에 11.1 kBq (2.2 mCi)/cc의 201-Tl을 주입하여 제작하였고, 영상획득 조건은 회전각 $6^{\circ}$, 50 sec/frame으로 환자와 동일한 조건으로 하였다. 영상획득 방식에 따른 차이를 확인하기 위해 Body contour와 Circular 방식으로 영상을 획득하여 환자와 검출기 사이의 거리를 각각 측정하여 비교하였고, 정상군과 비 정상군의 영상을 육안 분석하였다. 거리에 따라 영상에 미치는 영향을 확인하기 위해, 모형 실험에서 Circular 방식으로 회전반경을 18.8, 21.8, 23.8, 25.8, 28.8 cm 로 다르게 설정하여 영상을 획득하였고, 각 영상에서 심첨(Apex)에 관심영역을 설정하여 반치폭을 비교하였다. 모형 실험 결과, Body contour를 이용한 실험에서 산출된 반치폭은 6.23 mm이고, Circular mode에서 18.8, 21.8, 23.8, 25.8, 28.8 cm의 회전반경으로 산출된 반치폭은 각각 5.41, 6.24, 6.33, 6.42, 6.93 mm이다. 환자 데이터에서 Body contour의 회전반경이 -3.5 cm ~ 9.5 cm으로 차이를 보였고, Circular mode에 비해 평균 2.5 cm 더 큰 차이를 보였다. 본 연구를 통해, INFINIA 장비에서 Circular mode가 Body contour를 사용한 영상 획득 방법보다 낮은 반치폭을 보였다. 비록 INFINIA장비의 두 가지 영상 획득 방식에 대한 비교였지만, INFINIA장비를 이용한 심근관류 검사에서는 Circular mode 의 영상 획득 방식이 더 적합하다고 사료된다.

• International Journal of Aeronautical and Space Sciences
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• 제1권2호
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• pp.30-42
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• 2000

On-orbit thermal environment test of KOMPSAT was performed in early 1999. An analysis of the test data are addressed in this paper. For the thermal-environmental simulation of spacecraft bus, an artificial heating through the radiator zones and onto some critical heat-dissipating electronic boxes was made by Absorbed-heat Flux Method. Test data obtained in terms of temperature history were reduced into flight heater duty cycles and converted into the total electrical power required for spacecraft thermal control. Verification result of flight heaters dedicated to the bus thermal control is presented. Additionally, an exhaustive heating-control process for maintaining the spacecraft thermally safe and for realistic simulation of the orbital-thermal environment during the test are graphically shown. Qualitative suggestions to post-test model correlation are given in consequency of the analysis.

• 항공우주기술
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• 제1권1호
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• pp.65-71
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• 2002

다목적 실용위성의 자세제어계 mode는 크게 Sun, Maneuver, Science Mode로 나누어진다. 이중 Manuever Mode는 다시 Attitude Hold submode 와 Δ-V Burn submode로 나누어진다. 본 논문은 지상으로 송신된 playback 데이터를 이용하여 자세제어계 Maneuver Mode의 동작상태를 주로 분석하였다. Maneuver Mode중 attitude hold submode에서의 nadir pointing performance, 그리고 Δ-V Burn submode에서의 pitch/ roll 90도 maneuver 후 추력기 점화 과정에 대한 성능 분석을 수행하였으며 자세제어계 서브시스템 설계 규격을 만족함을 검증하였다.

• Journal of Information Processing Systems
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• 제20권1호
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• pp.131-147
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• 2024

A routing strategy based on traffic prediction and dynamic cache allocation for satellite nodes is proposed to address the issues of high propagation delay and overall delay of inter-satellite and satellite-to-ground links in low Earth orbit (LEO) satellite systems. The spatial and temporal correlations of satellite network traffic were analyzed, and the relevant traffic through the target satellite was extracted as raw input for traffic prediction. An improved gradient boosting regression tree algorithm was used for traffic prediction. Based on the traffic prediction results, a dynamic cache allocation routing strategy is proposed. The satellite nodes periodically monitor the traffic load on inter-satellite links (ISLs) and dynamically allocate cache resources for each ISL with neighboring nodes. Simulation results demonstrate that the proposed routing strategy effectively reduces packet loss rate and average end-to-end delay and improves the distribution of services across the entire network.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2003년도 Proceedings of ACRS 2003 ISRS
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• pp.1197-1199
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• 2003

ROCSAT-2 mission is to daily image over Taiwan and the surrounding area for disaster monitoring, land use, and ocean surveillance during the 5-year mission lifetime. The satellite will be launched in December 2003 into its mission orbit, which is selected as a 14 rev/day repetitive Sun-synchronous orbit descending over (120 deg E, 24 deg N) and 9:45 a.m. over the equator with the minimum eccentricity. National Space Program Office (NSPO) is developing a ROCSAT-2 Image Processing System (IPS), which aims to provide real-time high quality image data for ROCSAT-2 mission. A simulated ROCSAT-2 image, based on Level 1B QuickBird Data, is generated for IPS verification. The test image is comprised of one panchromatic data and four multispectral data. The qualification process consists of four procedures: (a) QuickBird image processing, (b) generation of simulated ROCSAT-2 image in Generic Raw Level Data (GERALD) format, (c) ROCSAT-2 image processing, and (d) geometric error analysis. QuickBird standard photogrammetric parameters of a camera that models the imaging and optical system is used to calculate the latitude and longitude of each line and sample. The backward (inverse model) approach is applied to find the relationship between geodetic coordinate system (latitude, longitude) and image coordinate system (line, sample). The bilinear resampling method is used to generate the test image. Ground control points are used to evaluate the error for data processing. The data processing contains various coordinate system transformations using attitude quaternion and orbit elements. Through the qualification test process, it is verified that the IPS is capable of handling high-resolution image data with the accuracy of Level 2 processing within 500 m.

• Journal of Astronomy and Space Sciences
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• 제32권4호
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• pp.367-377
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• 2015

Atmospheric drag force is an important source of perturbation of Low Earth Orbit (LEO) orbit satellites, and solar activity is a major factor for changes in atmospheric density. In particular, the orbital lifetime of a satellite varies with changes in solar activity, so care must be taken in predicting the remaining orbital lifetime during preparation for post-mission disposal. In this paper, the System Tool Kit (STK$^{(R)}$) Long-term Orbit Propagator is used to analyze the changes in orbital lifetime predictions with respect to solar activity. In addition, the STK$^{(R)}$ Lifetime tool is used to analyze the change in orbital lifetime with respect to solar flux data generation, which is needed for the orbital lifetime calculation, and its control on the drag coefficient control. Analysis showed that the application of the most recent solar flux file within the Lifetime tool gives a predicted trend that is closest to the actual orbit. We also examine the effect of the drag coefficient, by performing a comparative analysis between varying and constant coefficients in terms of solar activity intensities.

• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2006년도 International Symposium on GPS/GNSS Vol.2
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• pp.251-254
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• 2006

A precise real-time method of using the IGS ultra rapid products (IGU) and the GPS broadcast ephemeris to calculate the VRS orbit corrections was presented here which was suited for GPS/VRS reference station network based positioning. Test data acquired from both the SGRSN (Sichuan GPS Reference Station Network) and SCIGN (Southern California integrated GPS network) were used to evaluate the performance of the modeling techniques. The new method was proven to be more precise and reliable compared with the existing conventional network-based orbit error interpolation method. It was shown that 0.004ppm relative accuracy was reached, namely the influence from the orbit bias for the RTK positioning within 100km area can be of sub-millimeter level.