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디지털 텍스타일 프린팅에서 Color Management System이 프린터-모니터간 Color 재현성에 미치는 영향
박순영,전동원,박윤철,이범수,박영환,Park, Soon-Young,Jeon, Dong-Won,Park, Yoon-Cheol,Lee, Beom-Soo,Park, Young-Hwan 한국섬유공학회 2009 한국섬유공학회지 Vol.46 No.2
The digital textile printing (DTP) has several advantages such as proper system for production of small amount, quick response system (QRS), and manufacturing of textile goods by various printing designs. However, it still has problems of color reproduction and control. Generally, color gamut of RGB (red, green, blue) system is wider than that of CMYK (cyan, magenta, yellow, black); therefore, the colors seen in the monitor is different from the colors that appear in the printed output. The color management system (CMS) has been used for improving reproduction and control of printing color. This study was investigated the effects on the appearance of colors in printouts through CMS application such as color gamut, printability and color difference. The results were obtained as follows: first, Color gamut volume with dot gain 49% was decreased to 31.1% in comparison with dot gain 10%; Second, K/S value increased as the dot gain increased; third, the resolution of printer does not have so much effect on printability with light color when dot gain 10 and 20%; and fourth, by using CMS including calibration and profiling process, it was possible to reproduce monitor's color with DTP and reduce the standard deviation of $\Delta$E between monitor's color and printed color with DTP from 5.27 to 2.92.
박순영,남창호,문인상,설우석,Park, Soon-Young,Nam, Chang-Ho,Moon, In-Sang,Seol, Woo-Seok 한국항공우주연구원 2005 항공우주기술 Vol.4 No.2
액체로켓 엔진시스템 개발에 있어서 시동부터 정상상태까지의 시동특성은 안정된 시동의 재현성을 확보하여 신뢰도를 높이는 것과 과도상태의 시간을 단축하는 두 가지 목표를 만족하는 방향으로 전개된다고 할 수 있다. 특히 우리나라와 같이 액체로켓 엔진 개발의 초기단계에서는 엔진시스템 시험의 경험이 없어, 시동에서 정상상태까지 과연 어느 정도의 시간이 필요할 것인가에 대한 예측이 힘들 수밖에 없다. 본 연구에서는 터보펌프 공급식 액체로켓 엔진의 각 구성품의 모델을 구성하여 시동 과도 해석을 수행할 수 있는 프로그램을 완성하였다. 이 프로그램을 이용하여 25톤급 가스발생기 사이클 엔진에 대한 시동 특성을 조사하여 시동에서 정상상태에 이르는 시간을 계산하였으며, 비정상 상태의 엔진시스템의 동특성을 밝힐 수 있었다. There are two definite objects for developing the startup transient of liquid rocket engine. One is to achieve the repeatability of startup to ensure higher reliability, and the other is to reduce the time of the startup transient. Typically in the initial phase of engine development as we are currently opposing, it is hard to estimate engine startup time due to the lack of experiences. In this work, a startup transient analysis tool was developed with the introduction of the mathematical model for each component of pump-fed liquid rocket engine system. Startup transient was investigated for a 25 ton class gas generator cycle engine to find necessary time for reaching steady state from startup and this enabled to reveal dynamic characteristics of the engine.