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In vivo 783-channel diffuse reflectance imaging system and its application
Yang, Joon-Mo,Han, Yong-Hui,Yoon, Gilwon,Ahn, Byung Soo,Lee, Byung-Cheon,Soh, Kwang-Sup The Optical Society 2007 Applied Optics Vol.46 No.23
<P>A fiber-based reflectance imaging system was constructed to produce in vivo absorption spectroscopic images of biological tissues with diffuse light in the cw domain. The principal part of this system is the 783-channel fiber probe, composed of 253 illumination fibers and 530 detection fibers distributed in a 20x20 mm square region. During illumination with the 253 illumination fibers, diffuse reflected lights are collected by the 530 detection fibers and recorded simultaneously as an image with an electron multiplying CCD camera for fast data acquisition. After signal acquisition, a diffuse reflectance image was reconstructed by applying the spectral normalization method we devised. To test the applicability of the spectral normalization, we conducted two phantom experiments with chicken breast tissue and white Delrin resin by using animal blood as an optical inhomogeneity. In the Delrin phantom experiment, we present images produced by two methods, spectral normalization and reference signal normalization, along with a comparison of the two. To show the feasibility of our system for biomedical applications, we took images of a human vein in vivo with the spectral normalization method.</P>
만성 바이러스간염 환자에서 간탄력도 측정을 이용한 간섬유화 진단
강준구 ( Joon Koo Kang ),정재연 ( Jae Youn Cheong ),조성원 ( Sung Won Cho ),조진희 ( Jin Hui Cho ),박진선 ( Jin Sun Park ),김영배 ( Yeong Bae Kim ),김동준 ( Dong Joon Kim ),황성규 ( Seong Gyu Hwang ),양진모 ( Jin Mo Yang ),박영년 대한간학회 2007 Clinical and Molecular Hepatology(대한간학회지) Vol.13 No.4
전준탁(Joon-Tak Jun),강휘원(Hui-Won Kang),양명석(Myung-Seog Yang) 한국항공우주학회 2015 韓國航空宇宙學會誌 Vol.43 No.1
본 논문은 램프의 수명저하 없이 1,000℃이상의 초고온 급속가열 환경을 지속적으로 모사할 수 있고 기존 사용해온 열하중 부가장치 대비 내구성과 신뢰성이 향상된 열하중 부가장치를 개발하여 초고속 비행체 날개의 구조 건전성 평가에 적용, 그 활용가능성을 수록한 내용이다. 본 시험을 통하여 초고온의 운용환경에 노출되는 비행체 날개의 공력가열에 의한 강성저하를 정량적으로 예측할 수 있었으며, 향후 비약적인 증가추세에 있는 공력가열온도를 경험하게 되는 극초음속 비행체에 대한 고온환경에서의 구조 강도특성 평가가 가능해짐으로써 시험 신뢰성 향상과 함께 고온구조강도시험 수행능력을 한 단계 도약시킬 수 있는 계기가 되었다. This paper describes test result of the Supersonic Wing Structure and the utility of thermal test equipment, which is possible to heat rapidly and continuously above 1,000℃, the durability and reliability of which are improved compared with the existing equipment. Through the test, we could predict the amount of strength reduction of the wing due to aerodynamic heating, caused by exposure of high temperature. Recently the aerodynamic heating temperature of the supersonic flying object is rapidly increased. It is possible to carry out the High Temperature Strength est on the hypersonic speed flying object with the newly designed thermal test equipment. Because of that, we can upgrade the High Temperature Strength Structure Test technique and test reliability.