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Liu, Ying,Davies, Jackie A.,Luhmann, Janet G.,Vourlidas, Angelos,Bale, Stuart D.,Lin, Robert P. IOP Publishing 2010 ASTROPHYSICAL JOURNAL LETTERS - Vol.710 No.1
<P>We describe a geometric triangulation technique, based on time-elongation maps constructed from imaging observations, to track coronal mass ejections (CMEs) continuously in the heliosphere and predict their impact on the Earth. Taking advantage of stereoscopic imaging observations from the Solar Terrestrial Relations Observatory, this technique can determine the propagation direction and radial distance of CMEs from their birth in the Corona all the way to 1 AU. The efficacy of the method is demonstrated by its application to the 2008 December 12 CME, which manifests as a magnetic cloud (MC) from in situ measurements at the Earth. The predicted arrival time and radial velocity at the Earth are well confirmed by the in situ observations around the MC. Our method reveals non-radial motions and velocity changes of the CME over large distances in the heliosphere. It also associates the flux-rope structure measured in situ with the dark cavity of the CME in imaging observations. Implementation of the technique, which is expected to be a routine possibility in the future, may indicate a substantial advance in CME studies as well as space weather forecasting.</P>
<i>SUZAKU</i>/WAM AND<i>RHESSI</i>OBSERVATIONS OF NON-THERMAL ELECTRONS IN SOLAR MICROFLARES
Ishikawa, Shin-nosuke,Krucker, Sä,m,Ohno, Masanori,Lin, Robert P. IOP Publishing 2013 The Astrophysical journal Vol.765 No.2
<P>We report on hard X-ray spectroscopy of solar microflares observed by the Wide-band All-sky Monitor (WAM), on board the Suzaku satellite, and by RHESSI. WAM transient data provide wide energy band (50 keV-5 MeV) spectra over a large field of view (similar to 2 pi sr) with a time resolution of 1 s. WAM is attractive as a hard X-ray solar flare monitor due to its large effective area (similar to 800 cm(2) at 100 keV, similar to 13 times larger than that of RHESSI). In particular, this makes it possible to search for high energy emission in microflares that is well below the RHESSI background. The WAM solar flare list contains six GOES B-class microflares that were simultaneously observed by RHESSI between the launch of Suzaku in 2005 July and 2010 March. At 100 keV, the detected WAM fluxes are more than similar to 20 times below the typical RHESSI instrumental background count rates. The RHESSI and WAM non-thermal spectra are in good agreement with a single power law with photon spectral indices between 3.3 and 4.5. In a second step, we also searched the RHESSI microflare list for events that should be detectable by WAM, assuming that the non-thermal power-law emission seen by RHESSI extends to >50 keV. From the 12 detectable events between 2005 July and 2007 February, 11 were indeed seen by WAM. This shows that microflares, similar to regular flares, can accelerate electrons to energies up to at least 100 keV.</P>
Alain P. Tchameni,Lin Zhao,Robert D. Nagre,Chao Ma 한국자원공학회 2017 Geosystem engineering Vol.20 No.6
This work compares the experimental results of the effects of drilled shale on the formulated oil-in-water emulsion drilling mud using biodiesel produced from waste vegetable oil (WVO) with white oil 5# at 140 °C. The concentration of drilled shale with particle sizes distribution between 80 and 100 mesh was varied from 0 to 16 wt./vol.%. The plastic viscosity, yield point, thixotropy, high-temperature–high-pressure (HTHP) filtration loss, coefficient of friction, and rate of drilled cuttings recovery were assessed. The biodiesel-in-water emulsion drilling mud (BEDM) exhibited better rheological behavior and stability compared to white oil-in-water emulsion drilling mud (WEDM) under the different conditions examined. BEDM demonstrated the lowest HTHP filtration volume with values ranging from 6 to13 cm3 compared to WEDM with 9–18 cm3 and water-based mud (WBM) of 12–25 cm3. Moreover, coefficients of friction of BEDM, WEDM, and WBM were 0.26, 0.35, and 0.75, respectively. BEDM had the highest drilled cuttings recovery rate of 79.60%, followed by WEDM with a rate of 72.80%, while WBM recorded the least (46.25%). Hence, the use of WVO biodiesel as additive in water-based mud can enhance the drilled shale tolerance of water-based drilling mud in an environmentally friendly manner.
신유철,윤세영,이용석,전제헌,선종호,진호,이동훈,Robert P.LIN 한국항공우주학회 2012 한국항공우주학회 학술발표회 논문집 Vol.2012 No.4
경희대학교에서 제작 중인 초소형 위성 CINEMA(Cubesat for Ion, Neutron, Electron and MAgnetic field)의 자세제어 시스템은 V-slit 형태의 태양 센서와 3축 자력계인 MAGIC(MAGnetometer by Imperial College London)의 자세감지 센서와 2개의 토크 코일을 사용하는 자기 토커의 구동부로 이루어져 있다. 지상에서 CINEMA의 자세 제어를 검증하기 위해서는 센서와 구동부의 시뮬레이터를 이용한 자세 제어 시험이 요구된다. 본 연구에서는 CINEMA의 자세 제어 시스템을 시험하기 위한 태양 센서와 자력계의 시뮬레이터 및 구동부의 구현을 제안 하였다. 태양 센서와 자력계 센서의 시뮬레이터는 실제 CINEMA 하드웨어와 유사한 시험 환경의 구현을 제시하였다. 자세 제어 시뮬레이터의 설계 및 구현을 통하여 CINEMA 자세 제어 시스템을 검증 할 수 있을 것으로 기대된다. Attitude Control System of CINEMA is composed of attitude sensors of V-slit Sun sensor, 3-axis magnetometer(MAGIC : MAGnetometer by Imperial College London) and actuator of magnetic torquer which is used by torque coil. To verify the Attitude Control System of CINEMA, simulator of attitude sensors and actuator is required. This study proposed realization of simulator for Sun sensor, magnetometer and actuator. The simulator for Sun sensor and magnetometer is similar to real one. Design and implementation of simulator for attitude control can make it possible to verify the Attitude Control System of CINEMA.
윤세영,김용호,윤지원,선종호,진호,이동훈,Robert. P. Lin,Thomas R. Immel,Jerry Kim 한국항공우주학회 2012 한국항공우주학회 학술발표회 논문집 Vol.2012 No.4
위성의 초기운용은 정상임무 운용을 위해 필수적으로 수행되는 단계이다. 대부분의 위성 임무에서는 이 단계에서 태양 전지판 전개, 자세 안정화, 탑재체 보정 작업, 지상국과의 첫 교신 등을 수행하여 정상임무 운용을 위한 위성 시스템의 안정화를 목표로 한다. 본 연구에서는 초소형 인공위성 임무인 TRIO-CINEMA(TRiplet Ionospheric Observatory -Cubesat for Ion, Neutral, Electron, and Magnetic fields)의 초기 운용 계획을 세부적인 단계로 기술하고, 각 단계의 성공 여부를 판단할 수 있는 기준을 제시하였다. 제시된 초기 운용을 위성의 탑재 컴퓨터에 적용하고, 지상 시스템과의 연동 시험을 통해 목표의 약78%를 달성한 것을 확인하였다. Initial operation is essential stage to perform normal mission operation. In this stage, most of satellite missions try to conduct deployment of solar panel or antennae, attitude stabilization, calibration of scientific instruments, first contact to ground station and etc. to stabilize the spacecraft system for normal operation. This research details the specific steps of initial operational plan for pico-satellites mission TRIO-CINEMA and presents detailed criteria for success of each step. The suggested initial operation applied to on-board computer of TRIO-CINEMA, and in the rehearsal of initial operation with ground support equipment, 78% of goals was accomplished.
Thermal Analysis of TRIO-CINEMA Mission
유제건,진호,선종호,정윤황,David Glaser,이동훈,Robert P. Lin 한국우주과학회 2012 Journal of Astronomy and Space Sciences Vol.29 No.1
Thermal analysis and control design are prerequisite essential to design the satellite. In the space environment, it makes satellite survive from extreme hot and cold conditions. In recent years CubeSat mission is developed for many kinds of purpose. Triplet Ionospheric Observatory (TRIO)–CubeSat for Ion, Neutral, Electron, MAgnetic fields (CINEMA) is required to weigh less than 3 kg and operate on minimal 3 W power. In this paper we describe the thermal analysis and control design for TRIO-CINEMA mission. For this thermal analysis, we made a thermal model of the CubeSat with finite element method and NX6.0 TMG software is used to simulate this analysis model. Based on this result, passive thermal control method has been applied to thermal design of CINEMA. In order to get the better conduction between solar panel and chassis, we choose aluminum 6061-T6 for the material property of standoff. We can increase the average temperature of top and bottom solar panels from -70°C to -40°C and decrease the average temperature of the magnetometer from +93°C to -4°C using black paint on the surface of the chassis, inside of top & bottom solar panels, and magnetometer.