• 한국콘텐츠학회논문지
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• 제7권12호
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• pp.139-144
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• 2007

안와 림프종의 치료에 가장 효과적인 치료법인 방사선 치료는 안구 질환의 증가로 인해 계속 늘어나는 추세이다. 항암화학요법과 치료 기술의 비약적인 발전으로 치료 및 예후가 좋아지고는 있지만 백내장, 안구건조, 망막병증 등의 부작용이 발생되고 있다. 이에 본 연구에서는 안와 림프종의 방사선치료 시 백내장 발생의 방어수단으로써 Lens Shielding Device(이하 LSD)를 고안 제작하였고 이의 제작방법과 방사선 차폐 정도에 대해 알아보았다. 안구 표면에 해당하는 깊이에서 TLD의 측정결과는 3개의 평균값이 5.7%로 나타났고 관심부위인 수정체의 위치에서는 TLD 4.2%, markus chamber 5.1%의 선량값을 나타내었다. 본 연구에서 안와에 발생한 림프종의 방사선 치료로 인한 부작용을 예방하기 위해 제작한 LSD는 치료 중 조사받게 되는 총 30Gy의 선량 중에서 5%에 해당하는 약 1.5Gy의 방사선량만이 수정체와 각막에 영향을 미치는 것으로 확인되어 백내장의 역치선량인 2Gy와 임상적으로 백내장이 발생된다고 보고된 5Gy보다 적은 선량이 조사됨을 알 수 있었다. 방사선 치료 시 발생할 수 있는 여러 부작용의 예방에 유용한 기구임을 확인하였고 환자의 안구와 일치되도록 개인별로 제작하여 착용 시 이물감에 의한 불편을 줄일 수 있을 뿐만 아니라 치료 시 고정 또한 매우 용이함을 검증하였다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2008년도 International Symposium on Remote Sensing
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• pp.220-223
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• 2008

A camera system for the satellite application performs the mission of observation by measuring radiated light energy from the target on the earth. As a development stage of the system, the signal level analysis by estimating the number of electron collected in a pixel of an applied CCD is a basic tool for the performance analysis like SNR as well as the data path design of focal plane electronic. In this paper, two methods are presented for the calculation of the number of electrons for signal level analysis. One method is a quantitative assessment based on the CCD characteristics and design parameters of optical module of the system itself in which optical module works for concentrating the light energy onto the focal plane where CCD is located to convert light energy into electrical signal. The other method compares the design\ parameters of the system such as quantum efficiency, focal length and the aperture size of the optics in comparison with existing camera system in orbit. By this way, relative count of electrons to the existing camera system is estimated. The number of electrons, as signal level of the camera system, calculated by described methods is used to design input circuits of AD converter for interfacing the image signal coming from the CCD module in the focal plane electronics. This number is also used for the analysis of the signal level of the CCD output which is critical parameter to design data path between CCD and A/D converter. The FPE(Focal Plane Electronics) designer should decide whether the dividing-circuit is necessary or not between them from the analysis. If it is necessary, the optimized dividing factor of the level should be implemented. This paper describes the analysis of the electron count of a camera system for a satellite application and then of the signal level for the interface design between CCD and A/D converter using two methods. One is a quantitative assessment based on the design parameters of the camera system, the other method compares the design parameters in comparison with those of the existing camera system in orbit for relative counting of the electrons and the signal level estimation. Chapter 2 describes the radiometry of the camera system of a satellite application to show equations for electron counting, Chapter 3 describes a camera system briefly to explain the data flow of imagery information from CCD and Chapter 4 explains the two methods for the analysis of the number of electrons and the signal level. Then conclusion is made in chapter 5.

• 천문학회보
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• 제42권1호
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• pp.40.3-41
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• 2017

Korea Astronomy and Space Science Institute The observation of particles and waves using a single satellite inherently suffers from space-time ambiguity. Recently, such ambiguity has often been resolved by multi-satellite observations; however, the inter-satellite distances were generally larger than 100 km. Hence, the ambiguity could be resolved only for large-scale (> 100 km) structures while numerous microscale phenomena have been observed at low altitude satellite orbits. In order to resolve those spatial and temporal variations of the microscale plasma structures on the topside ionosphere, SNIPE mission consisted of four (TBD) nanosatellites (~10 kg) will be launched into a polar orbit at an altitude of 700 km (TBD). Two pairs of satellites will be deployed on orbit and the distances between each satellite will be from 10 to 100 km controlled by a formation flying algorithm. The SNIPE mission is equipped with scientific payloads which can measure the following geophysical parameters: density/temperature of cold ionospheric electrons, energetic (~100 keV) electron flux, and magnetic field vectors. All the payloads will have high temporal resolution (~ 16 Hz (TBD)). This mission is planned to launch in 2020. The SNIPE mission aims to elucidate microscale (100 m-10 km) structures in the topside ionosphere (below altitude of 1,000 km), especially the fine-scale morphology of high-energy electron precipitation, cold plasma density/temperature, field-aligned currents, and electromagnetic waves. Hence, the mission will observe microscale structures of the following phenomena in geospace: high-latitude irregularities, such as polar-cap patches; field-aligned currents in the auroral oval; electro-magnetic ion cyclotron (EMIC) waves; hundreds keV electrons' precipitations, such as electron microbursts; subauroral plasma density troughs; and low-latitude plasma irregularities, such as ionospheric blobs and bubbles. We have developed a 6U nanosatellite bus system as the basic platform for the SNIPE mission. Three basic plasma instruments shall be installed on all of each spacecraft, Particle Detector (PD), Langmuir Probe (LP), and Scientific MAGnetometer (SMAG). In addition we now discuss with NASA and JAXA to collaborate with the other payload opportunities into SNIPE mission.

• Journal of Astronomy and Space Sciences
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• 제26권4호
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• pp.439-450
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• 2009

2006년 상반기동안 GOES 10에 의해 관측된 > 2MeV의 전자에너지 채널에서 반복되는 상대론적 전자 증가 이벤트(GREE, Geosynchronous Relativistic Electron Event)가 4회 있었다. 이 현상들은 모두 코로나 구멍(Coronal hole)에서부터 나온 고속 태양풍(HSS, High Speed Solar Wind Stream)과 관련된 것으로 여겨진다. 약 27일 주기를 갖는 이 4회의 전자 증가 현상은 플럭스가 점점 증가하는 형태를 보인다. 현재까지 알려진 상대론적 전자 증가 현상의 주요 원인으로는 다음의 요소들이 언급되어 왔다: (1) 코로나 구멍과 관련된 태양풍 속도, (2) Pc5 ULF 파동, (3) 행성간 자기장(IMF, Interplanetary Magnetic Field) Bz의 남쪽 성 분, (4) 자기 부폭풍(substorm)의 발생, (5) 증가된 휘슬러 모드 코러스 파동(whistler mode chorus wave)과 (6)동압력(dynamic pressure). 따라서 이 논문에서는 2006년 상반기 동안 앞에서 언급한 6가지 현상 들을 분석하여 어느 요소가 상대론적 전자 증가 현상의 플럭스와 가장 가까운 연관성이 있는지 알아보고자 한다.

• Journal of Astronomy and Space Sciences
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• 제35권3호
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• pp.195-200
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• 2018

The present paper describes the design of a Solid State Telescope (SST) on board the Korea Astronomy and Space Science Institute satellite-1 (KASISat-1) consisting of four [TBD] nanosatellites. The SST will measure these radiation belt electrons from a low-Earth polar orbit satellite to study mechanisms related to the spatial resolution of electron precipitation, such as electron microbursts, and those related to the measurement of energy dispersion with a high temporal resolution in the sub-auroral regions. We performed a simulation to determine the sensor design of the SST using GEometry ANd Tracking 4 (GEANT4) simulations and the Bethe formula. The simulation was performed in the range of 100 ~ 400 keV considering that the electron, which is to be detected in the space environment. The SST is based on a silicon barrier detector and consists of two telescopes mounted on a satellite to observe the electrons moving along the geomagnetic field (pitch angle $0^{\circ}$) and the quasi-trapped electrons (pitch angle $90^{\circ}$) during observations. We determined the telescope design of the SST in view of previous measurements and the geometrical factor in the cylindrical geometry of Sullivan (1971). With a high spectral resolution of 16 channels over the 100 keV ~ 400 keV energy range, together with the pitch angle information, the designed SST will answer questions regarding the occurrence of microbursts and the interaction with energetic particles. The KASISat-1 is expected to be launched in the latter half of 2020.

• 한국자기학회지
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• 제18권6호
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• pp.211-216
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• 2008

Si이 체심입방구조(body centered cubic; bcc) Fe에 불순물로 포함된 경우에 Fe의 전자구조와 자성에 미치는 영향을 스핀-궤도 상호작용(spin-orbit coupling, SOC)을 고려한 제일원리방법을 통하여 연구하였다. Si 불순물의 효과를 기술하기 위하여 27개의 원자가 포함된 bcc Fe 초격자 구조를 고려하였다. 제일원리방법은 전전자 총퍼텐셜선형보강평면파(all-electron full-potential linearized augmented plane wave, FLAPW) 방법을 일반기울기 근사(generalized gradient approximation, GGA) 하에서 계산하였다. 스핀-궤도 상호작용은 스핀대각항 만을 고려한 이차변분방법을 이용하여 자체충족적으로 계산하였다. SOC를 고려하지 않은 강자성(ferromagnetic, FM) 상태의 경우 Si 불순물의 경우에는 $-0.143{\mu}B$의 스핀 자기모멘트가 계산되었으며, Fe 원자가 Si 불순물에서 멀어지면서 각각 $2.214{\mu}B$, $2.327{\mu}B$, 및 $2.354{\mu}B$의 값을 얻었다. 그러나, SOC를 고려한 경우 Si 불순물의 스핀 자기모멘트는 $-0.144{\mu}B$로 계산되어 SOC의 효과가 크지 않았으나, Fe 원자의 경우 각각 $2.189{\mu}B$, $2.310{\mu}B$, 및 $2.325{\mu}B$로 계산되어 SOC를 고려한 경우 스핀 자기모멘트 값이 줄어드는 것을 알 수 있었다. 총전하 및 스핀밀도의 비교와 상태밀도의 비교를 통하여 이러한 현상은 Si 불순물에 의한 영향을 가리는데 참여하는 Fe 원자의 $t_{2g}$ 전자 궤도의 변형의 효과로서 SOC를 고려할 때만 얻을 수 있다.

• 대한전기학회:학술대회논문집
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• 대한전기학회 1992년도 하계학술대회 논문집 B
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• pp.588-592
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• 1992

The electrons, which are accelerated to nearly light speed from LINAC(Linear Accelerator), put into Storage Ring. And this electrons circulate in an ultra high vacuum chamber and their orbit is controlled by the electromagnets such as DIPOLE, QUADRUPOLE, SEXTUPOLE & CORRECTION MAGNET. Among them, the dipole magnet is to bend the electron and to produce Synchrotron Radiation(S.R). This paper describes the key point during manufacturing of this magnet, and introduce the field measurement results of the HEECO's successful prototype.

• 한국자기학회지
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• 제21권1호
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• pp.1-4
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• 2011

정육면체 전이금속 산화물 FeO, MnO의 자기적 상호작용을 제1원리의 범밀도함수법을 이용하여 계산하였다. 그 결과, 모두 초교환작용으로 인해 반강자성적 상호작용이 가장 낮은 에너지를 가지고 있었다. 자기이방성은 반강자성 스핀 배열의 FeO 클러스터에서만 발견되었다. 그 원인은 <111> 방향으로 각운동량을 가지는 3d down-spin 전자의 스핀-궤도 결합에 기인하였다.

• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 2007년도 추계학술대회 논문집
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• pp.309-310
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• 2007

Spacecrafts such as most of commercial satellites that are operating in the geostationary orbit can be subjected to intense irradiation by charged particles. The surface made of dielectric materials can therefore become probable sites for damaging electrostatic discharges. Thanks to a specially equipped chamber, the spatial environment can be reproduced experimentally in the laboratory. In this paper, the behavior of high energy electrons injected in polymers such as PolyMethylMetaAcrylate (PMMA) and Kapton is studied. Results obtained by surface potential technique, pulse-electro acoustic device and a cell based on the split Faraday cup system are analyzed and discussed.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2007년도 제38회 하계학술대회
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• pp.1990-1991
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• 2007

Spacecrafts such as most of commercial satellites that are operating in the geostationary orbit can be subjected to intense irradiation by charged particles. The surface made of dielectric materials can therefore become probable sites for damaging electrostatic discharges. Thanks to a specially equipped chamber, the spatial environment can be reproduced experimentally in the laboratory. In this paper, the behavior of high energy electrons injected in polymers such as PolyMethylMetaAcrylate (PMMA) and Kapton is studied. Results obtained by surface potential technique, pulse-electro acoustic device and a cell based on the split Faraday cup system are analyzed and discussed.