• Proceedings of the Korea Water Resources Association Conference
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• 2016.05a
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• pp.601-601
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• 2016

글로벌 위성 기반의 강수량 관측에 대한 역사는 1979년에 Arkin의 의해 제안된 IR방법에 의해 위성으로 부터 강우자료를 유도하는 개념이 도입된 이후 1987년 해양에서의 비교적 정확한 강수량 추정이 가능한 다중 채널의 마이크로파(MW) 복사계를 이용한 방법으로 위성강수 추정에 대한 연구가 활발히 진행되었다. 이 후 두 IR과 MW를 혼합한 방법에서, 또다시 1997년 TRMM위성의 PR(Precpipitation Radar)의 레이더를 이용하는 방법, 그리고 2014년 GPM 핵심 위성(GPM Core Observatory)에 탑재된 Dual PR에 의한 방법으로 위성강수의 정확도를 매우 높여가고 있다. 전지구강수관측위성(GPM, Global Precipitation Measurement Mission) 사업은 미국우주항공국(NASA)과 일본우주항공국(JAXA)의 주도로 전 지구 규모의 강수관측을 목적으로 시작되었으며, 추가 파트너로 프랑스의 CNES(French Centre National d'?tudes Spatiales), 인도의 ISRO(Indian Space Research Organisation), 미국 NOAA, 그리고 유럽연합의 EUMETSAT(European Organisation for the Exploitation of Meteorological Satellites)가 참여하고 있다. 본 연구는 2014년 4월 발사된 GPM핵심 위성의 발사에 따라 제공되는 GPM 위성강우 자료의 정확도 평가를 목적으로 하고 있다. GPM 데이터는 Level-1에서 Level-3까지 다양한 데이터를 제공하고 있으며 본 연구에서는 Level-3의 IMERG 데이터를 이용하여 위성강우의 정확도를 평가하였다. IMERG 위성강우자료는 GPM 위성군의 모든 수동 MW 데이터를 조합하여 강우량을 추정하는 데이터이다. 자료의 시간적 범위는 2015년 8월 18일~8월 20일이고 공간적 범위는 한반도 영역으로 하였으며, 자료의 정확도 평가를 위한 지상계측자료는 기상청 ASOS(Automated Synoptic Observing System)의 강수량 자료를 이용하였다. 자료분석 결과 GPM에서 제공되는 IMERG 데이터의 공간적 분포는 그림 1과 같이 전라도 지역에 많은 강수가 분포하는 것을 확인할 수 있다. 이 기간 동안의 기상청 ASOS 관측 강수량 기록은 전국적으로 1순위가 고창군 25.5mm, 2순위가 부안군 21.9mm, 3순위가 정읍 및 영광군이 19.0mm로 위성으로부터 관측된 값과 지상계측값의 공간적 분포가 매우 유사한 경향을 보이는 것으로 분석되었다. 향후 위성강우 및 지상계측강우의 시계열적 정확도와 총강우량 등의 정확도 평가를 수행할 계획이다.

• Journal of Aerospace System Engineering
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• v.15 no.5
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• pp.89-97
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• 2021

STEP Cube Lab-II (Cube Laboratory for Space Technology Experimental Project-II) is a 6U Cube satellite equipped with optical and infrared cameras for monitoring Mt. Paektu volcanic eruption signs and earth observation in the Korean peninsula. To guarantee successful mission operation of the cube satellite in orbit, thermal design is essential for the electronic equipment, and must be kept within the allowable temperature range during the mission period. Thus, it is necessary to analyze the predictable orbital thermal environment. The STEP Cube Lab-II is launched through the KSLV-II, however, the operation orbit has not been determined due to the unknown launch time. In this study, we performed a thermal analysis of the satellite and investigated the heat flux according to launch time to analyze the worst orbital conditions that could occur.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.4
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• pp.309-318
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• 2019

The thermal design of the Lunar Terrain Imager (LUTI) on the Korean Pathfinder Lunar Orbiter (KPLO) was performed and the soundness of the thermal design was verified by thermal analysis. The thermal environment of the lunar mission orbit should be reflected in the thermal design because the IR radiation of the lunar surface is important, unlike the earth orbit. The components or modules exposed to the outside of the satellite are insulated with MLI as much as possible, but the camera tube and the radiator are functionally exposed, so the thermal shield using the concept of radiation shape factor is mounted on the front to mitigate IR radiation. The IR emissivity is important in the front side of the radiator that receives little solar radiation, and components that are susceptible to thermal deformation such as the tube use a radiation heater to minimize the temperature gradient. Through the investigation of computational results, it was confirmed that the thermal design of LUTI is stable in various situations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.11
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• pp.934-943
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• 2018

In these days, demand for agile spacecraft is gradually increasing, due to the fact that agile spacecraft can improve mission capability. In this paper, an attitude control logic based on reaction wheels that can enhance agility of spacecraft is proposed. Three methods are suggested, and all three or part of them can be integrated to the existing attitude control system. First, a feedforward/feedback controller is introduced, and its pros and cons are provided, compared to the conventional feedback controller. Second, an attitude command generation method that fully utilizes torque/momentum capacities of reaction wheels is proposed. Third, a torque (current) control mode for internal wheel control is introduced. Numerical results verify that the settling time can be significantly reduced by employing the feedforward/feedback control method, especially for large angle maneuver.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.6
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• pp.489-496
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• 2021

The X-band frequencies for transmitting the data from earth observation satellites are limited, so a number of satellites share the frequency bands. In order for multiple satellites to utilize same or adjacent frequency bands, International Telecommunication Union - Radiocommunication (ITU-R) limits power flux density (PFD), which overcomes the interferences among multiple satellites. However, even under the regulation, the interference effect needs to be analyzed when multiple satellites are connected to communicate with multiple ground stations (GSs) located close to each other. In this paper, the interference effect is analyzed based on signal to interference plus noise ratio (SINR) when two low earth orbit (LEO) satellites operating in different orbits are connected to communicate with randomly located two GSs in Korean peninsula. From the analysis results, it is confirmed that there can be interferences during 365 days operation even if the satellites meet PFD requirement, but the periods under interference effects are short and the interference can be foreseen.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.2
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• pp.155-166
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• 2021

In this paper, design study of a small two-stage launch vehicle is undertaken for the dedicated launch of the Compact Advanced Satellite 500 (CAS500)-class satellite into the Low Earth Orbit (LEO) by modifying the second and third stages of the Korean Space Launch Vehicle II (KSLV-II). Since the KSLV-II has three stages, velocity increment is newly distributed for the two-stage small launch vehicle. For this end, the staging design is carried out for the design parameters such as stage mass ratios, structural coefficients and engine options for each stage followed by trajectory analysis. Investigation of the results provides the combination of design parameters for the small launch vehicle for the dedicated launch of 500 kg-class satellite into LEO.

• Journal of Space Technology and Applications
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• v.1 no.1
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• pp.49-63
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• 2021

The exploration of the solar system is carried out through various payloads, and accordingly, many research results are emerging. We tried to apply deep-learning as a method of studying the bodies of solar system. Unlike Earth observation satellite data, the data of solar system differ greatly from celestial bodies to probes and to payloads of each probe. Therefore, it may be difficult to apply it to various data with the deep-learning model, but we expect that it will be able to reduce human errors or compensate for missing parts. We have implemented a model that detects craters on the lunar surface. A model was created using the Lunar Reconnaissance Orbiter Camera (LROC) image and the provided shapefile as input values, and applied to the lunar surface image. Although the result was not satisfactory, it will be applied to the image of the permanently shadow regions of the Moon, which is finally acquired by ShadowCam through image pre-processing and model modification. In addition, by attempting to apply it to Ceres and Mercury, which have similar the lunar surface, it is intended to suggest that deep-learning is another method for the study of the solar system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.12
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• pp.867-875
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• 2022

The preliminary mission analysis of a lunar lander, which is mounted on the upper stage of a Korean space launch vehicle, is performed when landing on the moon through a trans-lunar injection maneuver after being injected into the earth's low orbit by th launcher in this paper. Both direct landing and orbital landing methods, which have each advantage and disadvantages, are applied and their transfer orbit characteristics are analyzed according to the launch date when launching in lunar October 2030. We also analyzed the launch dates which satisfying eclipse conditions, solar elevation conditions, and tracking time intervals such as the US lunar lander Surveyor-1. The obtained results show that the most appropriate launch date is the 4th day of lunar October in case of direct landing method, and the 3rd day in case of indirect landing method, since the argument of perigee of the trans-lunar injection orbit and eclipse conditions are favorable in the dates.

• Korean Journal of Childcare and Education
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• v.10 no.6
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• pp.223-241
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• 2014

The objective of this study was to plan a direction for the connection of the area of inquiry in daily life between infants and young children in Korea based on the analysis of the early learning standards for infants aged 0~2, and young children aged 3~4/5 in 17 different states in America. The problem of the study is as follows: What is the content area of cognitive development, science and mathematics of early learning standards regarding age? The data used in this study was collected from a total of 17 states in America in which 12 states classify infants and young children as aged 0~2 and 3~4/5 respectively and 5 states do not classify the age groups. The results obtained from the analysis of the given issues are as follows. First, in the case of the five states that showed the group aged 0~4/5, the contents related to the area of inquiry in daily life of the early learning standards were included in the mathematics and science and a part of these contents were also included in cognitive developments. In the case of the 12 states that classified the groups aged 0~2 and 3~4/5 respectively, the group aged 0~2 included cognitive developments and the group aged 3~4/5 includes mathematics and science. Second, the contents related to the area of inquiry in daily life of the early learning standards in the five states that showed the single group aged 0~4/5 include the contents in order of scientific idea, biology, physics, and the earth and space. In the 12 states that classify different age groups. Third, in the case of the states that separate age groups, the group aged 0~2 include the contents of number and operation, geometry and space while the group aged 3~4/5 include the contents of number and operations, geometry and space, and measurement. The implications of this study was that it is necessary to take into account the linking between development and characteristics of the subjects.

• Journal of Astronomy and Space Sciences
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• v.22 no.3
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• pp.329-352
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• 2005

Long term observations of full-disk Lyman-o irradiance have been made by the instruments on various satellites. In addition, several sounding rockets dating back to the 1950s and up through the present have measured the $Lyman-{\alpha}$ irradiance. Previous full disk $Lyman-{\alpha}$ images of the sun have been very interesting and useful scientifically, but have been only five-minute 'snapshots' obtained on sounding rocket flights. All of these observations to date have been snapshots, with no time resolution to observe changes in the chromospheric structure as a result of the evolving magnetic field, and its effect on the Lyman-o intensity. The $Lyman-{\alpha}$ Imaging Solar Telescope(LIST) can provide a unique opportunity for the study of the sun in the $Lyman-{\alpha}$ region with the high time and spatial resolution for the first time. Up to the 2nd year development, the preliminary design of the optics, mechanical structure and electronics system has been completed. Also the mechanical structure analysis, thermal analysis were performed and the material for the structure was chosen as a result of these analyses. And the test plan and the verification matrix were decided. The operation systems, technical and scientific operation, were studied and finally decided. Those are the technical operation, mechanical working modes for the observation and safety, the scientific operation and the process of the acquired data. The basic techniques acquired through the development of satellite based solar telescope are essential for the construction of space environment forecast system in the future. The techniques which we developed through this study, like mechanical, optical and data processing techniques, could be applied extensively not only to the process of the future production of flight models of this kind, but also to the related industries. Also, we can utilize the scientific achievements which are obtained throughout the project And these can be utilized to build a high resolution photometric detectors for military and commercial purposes. It is also believed that we will be able to apply several acquired techniques for the development of the Korean satellite projects in the future.