• The Bulletin of The Korean Astronomical Society
• /
• v.44 no.1
• /
• pp.55.3-55.3
• /
• 2019

우리나라 최초의 우주탐사 프로그램인 Korea Pathfinder Lunar Orbiter (KPLO)는 1년의 임무기간동안 달과 달 주변의 우주환경에 대한 과학탐사 임무를 수행할 예정이다. 이를 위해서 1개에 기술 검증장비와 고해상도 카메라를 포함한 5개의 과학장비를 탑재할 예정이다. 이 중 고해상도 카메라인 LUTI(LUnar Terrain Imager)와 국내에서 개발한 3개의 과학탑재체(KGRS;감마선분광기, KMAG;자기장측정기, PolCam;광시야 편광카메라)가 획득한 과학자료는 일정기간(통상 1년)동안 비공개로 검보정이 이루어진 후 일반에게 공개(Public release)할 예정이다. 이러한 과학자료의 공개와 관리를 위해서 한국항공우주연구원은 KPLO 심우주 지상시스템 내에 과학자료의 공개 및 관리를 위한 KARI Planetary Data System(KPDS)을 개발하고 있다. KPDS는 미국 NASA의 PDS에서 개발하여 유럽, 일본 등에서 이미 행성탐사 과학자료의 표준으로 활용하고 있는 PDS4 표준을 준수하는 과학자료를 제공할 것이다. 본 발표를 통해서 KPDS의 운영개념과 과학자료 관리계획, 그리고 KPDS의 개발현황을 천문학계와 공유하여 KPLO에 의해서 획득된 과학자료가 많은 과학자들이 활용하여 높은 과학적 성과를 낼 수 있기를 기대한다.

• International journal of advanced smart convergence
• /
• v.10 no.1
• /
• pp.184-196
• /
• 2021

This study, in order to evaluate the safety of evacuation by comparing and analyzing the RSET according to the slope change of the ramp, which is a vertical evacuation route in case of fire in a high school building, Evacuation simulation was run the Pathfinder program changed the slope of the ramp to 10°, 15°, and 20° for each male students and female students. In the case of female students, it was analyzed that when the final RSET slope was 15°, 25.7 seconds were shorter than when 10°, and 4.2 seconds were shorter than when 20°. Male students also found that when the final RSET slope was 15°, 23.8 seconds were shorter than when 10°, and 5.4 seconds shorter than when 20°. It was analyzed that even if the number of participants was increased and the evacuation simulation was executed, the safety of evacuation could be improved when the slope of the slope is 15° as the RSET when the slope of the slope is 15° is shorter than that of 10° and 20°.

• The Bulletin of The Korean Astronomical Society
• /
• v.46 no.2
• /
• pp.55.4-55.4
• /
• 2021

한국천문연구원에서는 낮은 표면밝기(Low Surface Brightness; LSB)의 천체를 효율적으로 관측할 수 있는 소형(〉30cm) 광시야(〉1°×1°) 광학망원경 및 관측기술 개발을 통한 은하형성 규명 연구를 수행 중에 있다. 이번에 개발한 K-DRIFT pathfinder는 비축 자유곡면 3반사 망원경 시스템(Linear Astigmatism Free-Three Mirror System; LAF-TMS)으로 넓은 시야에서 고품질의 이미지를 효율적으로 얻을 수 있는 광학 설계를 적용하고, 배경 값 변동 요인을 분석하여 가까운 우주의 LSB 천체 관측에 최적화될 수 있도록 하였다. 이번 특별세션에서는 '왜 LSB 우주 탐사를 하고, K-DRIFT를 개발하는지?'에 대해서 소개하고, K-DRIFT pathfinder의 개발 과정, 보현산 천문대에서의 시험관측 결과 소개와 함께, LSB 천체 연구를 위한 맞춤형 시뮬레이션 개발 및 수행 내용을 소개한다.

• Fire Science and Engineering
• /
• v.29 no.3
• /
• pp.13-20
• /
• 2015

As building height is increased, more careful decisions about the required safe egress time is needed for evacuation. This study analyzed the influence of three training sessions on the vertical speed of evacuation in the high rise building. Evacuation experiments were done in a high-rise office building in Seoul, and we analyzed the vertical evacuation speed as a function of density using a camera. Controlled and uncontrolled total evacuation were compared using the Pathfinder simulation. The process of repeated training, changed the specific stair utilization rate from 6.3% to 39.5%. The vertical evacuation speed as a function of density was analyzed using the equation s = 1.004 ? 0.288D, which is very similar to the equation used in a different study. The total evacuation time of the special controlled total evacuation was reduced by about 25% compared to the simultaneous evacuation.

• Fire Science and Engineering
• /
• v.33 no.3
• /
• pp.84-90
• /
• 2019

In this study, a fire and evacuation inside an electronic equipment room in environmental energy facilities were conducted and evaluated using a numerical analysis method. In the fire simulation, the visual distance, temperature distribution, and CO concentration distribution were analyzed using FDS. Based on the results, the Pathfinder program, which is an evacuation simulation, was used to calculate the evacuation time of the occupants and derive an evacuation safety evaluation. As a result, the Available safe Egress time (ASET) of P-01 and P-05 was 203.3 and 398.6 s, respectively. For the Required safety Egress time (RSET) results, all evacuees were evacuated at all points and the safety of the evacuee was secured this simulation showed that the safety evaluation is based on the non - operation of the fire - fighting equipment to improve the safety, making it possible to secure better evacuation safety performance owing to the fire of other fire - fighting facilities.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.208.1-208.1
• /
• 2012

The Ultra Fast Flash Observatory (UFFO) pathfinder is a payload system on-board the Russian satellite Lomonosov, scheduled to be launched in 2013. The main purpose of the UFFO pathfinder is to observe the early photons from Gamma-Ray Bursts. It consists of two instruments. The first instrument is the UFFO Burst Alert X-ray Trigger telescope (UBAT) for the fast-trigger and detection of GRB location, and the second is the Slewing Mirror Telescope (SMT) for the observation of the UV/optical afterglow from the GRB located by the UBAT. It will provide the first-ever systematic study of UV/optical emission far earlier than 1 sec after trigger. We will present the design, fabrication and the preliminary performance of the UBAT.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.207.2-207.2
• /
• 2012

The Ultra Fast Flash Observatory (UFFO) pathfinder consists of the UFFO Burst Alert X-ray Trigger telescope (UBAT) and the Slewing Mirror Telescope (SMT). They are controlled by the UFFO Data Acquisition system (UDAQ). The UBAT triggers Gamma-Ray Bursts(GRBs) and sends the position information to the SMT. The SMT slews the motorized mirror rapidly to the GRB position to take the UV/Optical data within a second after trigger. The UDAQ controls each instrument, communicates with the satellite, collects the data from UBAT and SMT, and transfers them to the satellite. Each instrument uses its own field programmable gates arrays (FPGA) for low power consumption and fast processing, and all functions are implemented in FPGAs without using microprocessors. The entire electronics system of the UFFO pathfinder including architecture, control, and data flow will be presented.

• Advances in aircraft and spacecraft science
• /
• v.7 no.3
• /
• pp.229-249
• /
• 2020

This paper is the logical follow-up of four papers by the author on the subject "aerodynamics in Mars atmosphere". The aim of the papers was to evaluate the influence of two Mars atmosphere models (NASA Glenn and GRAM-2001) on aerodynamics of a capsule (Pathfinder) entering the Mars atmosphere and also to verify the feasibility of evaluating experimentally the ambient density and the ambient pressure by means of the methods by McLaughlin and Cassanto respectively, therefore to correct the values provided by the models. The study was carried out computationally by means of: i) a code integrating the equations of dynamics of an entry capsule for the computation of the trajectories, ii) two Direct Simulation Monte Carlo (DSMC) codes for the solution of the 2-D, axial-symmetric and 3-D flow fields around the capsule in the altitude interval 50-100 km. The computations verified that the entry trajectories of Pathfinder from the two models, in terms of the Mach, Reynolds and Knudsen numbers, were very different. The aim of the present paper is to continue this study, considering other aerodynamic problems and then to provide a contribution to a long series of papers on the subject "aerodynamics in Mars atmosphere". More specifically, the present paper evaluated and quantified the effects from the two models of: i) chemical reactions on aerodynamic quantities in the shock layer, ii) surface temperature, therefore of the contribution of the re-emitted molecules, on local (pressure, skin friction, etc.) and on global (drag) quantities, iii) surface recombination reactions (catalyticity) on heat flux. The results verified that the models heavily influence the flow field (as per the shock wave structure) but, apart from the surface recombination reactions, the effects of the different conditions on aerodynamics of the capsule are negligible for both models and confirmed what already found in the previous paper that, because of the higher values of density from the NASA Glenn model, the effects on aerodynamics of a entry capsule are stronger than those computed by the GRAM-2001 model.

• Journal of the Korea Society for Simulation
• /
• v.25 no.3
• /
• pp.41-51
• /
• 2016

In this study, we propose an improved Floor Field Model(FFM) that considers the physical characteristics of pedestrians, i.e., body size, shape, and posture. Also we analyse limits of FFM and features of improved model compared with existing evacuation simulation models. FFM is a typical microscopic pedestrian model using CA, but it does not reflect the physical characteristics of pedestrians. Because of this, FFM is difficult to modeling phenomena such as collision, friction between pedestrians. As a result, FFM calculates a very short evacuation time when compared with the other models. We performed a computational experiment to compare improved model with other models such as FFM, Simulex, Pathfinder in an actual campus building. We carried out a comparison of evacuation aspect according to the change in number of evacuees. Also we compared evacuation aspect by exit. Finally, we confirmed that improved model reflects physical phenomena which were not reflected in FFM. Especially, experimental results were very similar to the Simulex.

• Journal of Astronomy and Space Sciences
• /
• v.38 no.3
• /
• pp.185-192
• /
• 2021

This technical paper deals the practical transformation algorithms between several lunar reference frames which will be used for Korea pathfinder lunar orbiter (KPLO) flight operation. Despite of various lunar reference frame definitions already exist, use of a common transformation algorithm while establishing lunar reference frame is very important for all members related to KPLO mission. This is because use of slight different parameters during frame transformation may result significant misleading while reprocessing data based on KPLO flight dynamics. Therefore, details of practical transformation algorithms for the KPLO mission specific lunar reference frames is presented with step by step implementation procedures. Examples of transformation results are also presented to support KPLO flight dynamics data user community which is expected to give practical guidelines while post processing the data as their needs. With this technical paper, common understandings of reference frames that will be used throughout not only the KPLO flight operation but also science data reprocessing can be established. It is expected to eliminate, or at least minimize, unnecessary confusion among all of the KPLO mission members including: Korea Aerospace Research Institute (KARI), National Aeronautics and Space Administration (NASA) as well as other organizations participating in KPLO payload development and operation, or further lunar science community world-wide who are interested in KPLO science data post processing.