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전우철(Oo-Chul Jun),전승문(SeungMoon Jun),유구현(Gu-Hyun Ryu),김준(Joon Kim) 한국항공우주학회 2005 韓國航空宇宙學會誌 Vol.33 No.4
새로 개발된 ECM 포드의 비행 적합성 시험을 위한 외부 장착물 비행 시험용 계측 포드를 설계하였다. 비행시험 요구도 분석결과 하중, 진동환경 및 공력 가열적 측면에 대한 측정이 요구되었다. 비행하중 측정을 위하여 1) ECM 포드 무게 중심점에 3축 선형 가속도계, 3축 각속도계, 및 2축 경사계, 2) 장착 걸쇠(Lug)에 스트레인 게이지 8채널, 3) 장착볼트의 하중 측정을 위한 STRAINSERT<SUP>®</SUP> 볼트 2개를 장착하였다. 비행 진동 환경 측정을 위한 3축 선형가속도계와 공력가열에 의한 영향을 분석하기 위한 4개의 열전쌍을 장착하였다. 기동특성 파악을 위하여 항공기의 고도, 속도, 하중배수, 자세등의 신호를 KF-16 MIL-STD-1553B로부터 추출 할 수 있는 버스 모니터(Bus Monitor)를 장착하였다. 획득된 자료는 모두 PCM화 되어 디지털테이프에 기록되도록 하였다. 지상 기능시험으로 계측 포드의 정상작동을 확인하였다. A design of the instrumented pod for the newly developed ECM(Electronic Counter Measure) pod compatibility flight test is presented. A requirement study asks the measurement of load, vibration, and aerodynamic heating. Following sensors are designed for the flight load data evaluation; 1) 3 linear accelerometers, 3 angular rate sensors, and 2 inclinometers at the center of gravity 2) 8 channel strain gages at the lugs, 3) 2 STRAINSERT<SUP>®</SUP> bolts to measure the tensile load. The 3 triaxial linear accelerometers are installed to measure the vibration environment and 4 thermocouples are installed. Finally, a bus monitor is installed to extract the aircraft parameters such as altitude, speed, load factor and attitude from the W-mux of KF-16 MIL-STD-1553B. All the data are recorded in digital tape by PCM(Pulse Coded Modulation) stream. The functional test assures the normal operation of the instrument pod design.
Simulation of CO2 removal with aqueous sodium glycinate solutions in a pilot plant
박진원,Seungmoon Lee,Ho-Jun Song,Seung-Kwan Yoo,Sanjeev Maken,Seonwook Kim,Jae Goo Shim,Kyung-Ryong Jang 한국화학공학회 2008 Korean Journal of Chemical Engineering Vol.25 No.1
In this paper, density, viscosity, surface tension and vapor pressure of aqueous sodium glycinate solutions of different mass fractio ns (0.1-0.5) at different temperatures (20-100 oC) were simulated using Pro/II (version 6.01), acommercial process simulator, and compared with corresponding experimentally measured data. It was found that simulated data of physicochemical properties compared well with corresponding experimental data. We have also predicted concentration of CO2 with each ideal stage in an absorber/stripper tower
Analysis and Test of Hydrodynamic Ram in Welded Metallic Water Tanks
Kim, Jong Heon,Kim, Chun-Gon,Jun, Seungmoon The Korean Society for Aeronautical and Space Scie 2015 International Journal of Aeronautical and Space Sc Vol.16 No.1
Analysis and test of hydrodynamic ram in welded metallic tanks containing water were performed to investigate the phenomena and to understand the effects on the resulting structural behavior. Arbitrary Lagrange-Euler coupling method was used for the analysis of the fluid-structure interaction occurring in the hydrodynamic ram, where the projectile, tank, and water are exchanging load, momentum, and energy during the traveling of the projectile through the water of the tank. For a better representation of the physical phenomena, modeling of the welded edges is added to the analysis to simulate the earlier weld line fracture and its influence on the resulting hydrodynamic ram behavior. Corresponding hydrodynamic tests were performed in a modified gas gun facility, and the following panel-based examinations of various parameters, such as displacement, velocity, stress, and energy, as well as hydrodynamic ram pressure show that the analysis and test are well correlated, and thus the results of the study reasonably explain the characteristics of the hydrodynamic ram. The methodology and procedures of the present study are applicable to the hydrodynamic ram assessment of airframe survivability design concepts.
Analysis and Test of Hydrodynamic Ram in Welded Metallic Water Tanks
Jong Heon Kim,Chun-Gon Kim,Seungmoon Jun 한국항공우주학회 2015 International Journal of Aeronautical and Space Sc Vol.16 No.1
Analysis and test of hydrodynamic ram in welded metallic tanks containing water were performed to investigate the phenomena and to understand the effects on the resulting structural behavior. Arbitrary Lagrange-Euler coupling method was used for the analysis of the fluid-structure interaction occurring in the hydrodynamic ram, where the projectile, tank, and water are exchanging load, momentum, and energy during the traveling of the projectile through the water of the tank. For a better representation of the physical phenomena, modeling of the welded edges is added to the analysis to simulate the earlier weld line fracture and its influence on the resulting hydrodynamic ram behavior. Corresponding hydrodynamic tests were performed in a modified gas gun facility, and the following panel-based examinations of various parameters, such as displacement, velocity, stress, and energy, as well as hydrodynamic ram pressure show that the analysis and test are well correlated, and thus the results of the study reasonably explain the characteristics of the hydrodynamic ram. The methodology and procedures of the present study are applicable to the hydrodynamic ram assessment of airframe survivability design concepts.
Flight Test Measurement and Assessment of a Flapping Micro Air Vehicle
Jong Heon Kim,Chan Yik Park,Seungmoon Jun,Dae Keun Chung,Jong Rok Kim,Hee Chul Hwang,Bret Stanford,Philip Beran,Gregory Parker,Denny Mrozinski 한국항공우주학회 2012 International Journal of Aeronautical and Space Sc Vol.13 No.2
Flight test of flapping micro air vehicles (FMAVs) is carried out using an instrumented measurement system to obtain various engineering parameters and hence to assess the flight performance of the vehicles through the data investigation. An indoor flight test facility equipped with a motion capture system and tracking cameras is used for the work presented in this paper. Maneuvers including straight-level flight, ground flapping, takeoff and landing are tested. Spatial position and orientation data are obtained from the retro-reflective tracking markers attached to the vehicles. Subsequent test analysis is carried out by generating performance parameters from raw data and then assessing the flight performance by comparison of the vehicles. The main findings of this work confirm that the test method and procedures presented here enable the systematic numerical data measurement and assessment of the flying performances of these vehicles, and show the applicability for the test and evaluation of general flapping MAVs.