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Candida parapsilosis 돌연변이주에 의한 Xylitol 생산의 배지조건 최적화
오덕근,윤상현,김정민,김상용,김정회 한국미생물생명공학회 ( 구 한국산업미생물학회 ) 1996 한국미생물·생명공학회지 Vol.24 No.4
Candida parapsilosis ATCC 22019 돌연변이주를 사용하여 xylitol 생산에 영향을 주는 배지성분의 최적화를 수행하였다. Xylose 50 g/l 배지에서 여러 가지 질소원이 xylitol 생산에 미치는 영향을 살펴본 결과 xylitol 생산에는 무기질소원으로는 (NH_4)_2SO_4가 좋았으며 유기질소원으로는 yeast extract가 가장 좋았다. 무기염으로 KH_2PO_4 ad MgSO_4·7H_2O를 선정하여 최적화를 수행하였고 그 결과 최적배지로 xylose of 50 g/l, yeast extract of 5 g/l, (NH_4)_2SO_4 of 5 g/l, KH_2PO_4 of 5 g/l, MgSO_4·7H_2O of 0.2 g/l로 결정하였다. 최적배지를 사용하여 발효조에서 64시간 배양하였을 때 xylose는 모두 소모되었으며 최종 균체농도와 xylitol 생산량은 각각 7.6 g/l와 37 g/l을 얻었다. 이때, xylose로 부터 xylitol의 전환수율 74%이었고, xylitol의 생산성은 0.58 g/l-hr이었다. 최적배지에서 총 첨가된 xylose에 대한 xylitol의 생산수율 80.7%에 해당되었고 xylitol의 생산성은 0.94g/l-hr에 해당되었다. Medium optimization for xylitol production from xylose by Candida parapsilosis ATCC 22019 mutant was performed. Effect of various nitrogen sources on xylitol production was investigatied. Of inorganic nitrogenous compounds, ammonium sulfate was effective for xylitol production and yeast extract was the most suitable orangic nitrogen nutrient for enhancement of xylitol production. Effect of inorganic salts such as KH_2PO_4 ad MgSO_4·7H_2O on xylitol production was also studied. Optimal medium was selected as xylose of 50 g/l, yeast extract of 5 g/l, (NH_4)_2SO_4 of 5 g/l, KH_2PO_4 of 5 g/l, MgSO_4·7H_2O of 0.2 g/l. In a fermentor by using the optimal medium, a final xylitol concentration of 37 g/l could be obtained from 50 g/l of xylose with a xylitol yield of 74% and a xylitol productivity of 0.58 g/l-hr. At 300 g/l xylose, fermentation was also carried out and then a final xylitol concentration of 242 g/l was obtained at 272 hours. It was corresponding to xylitol yield of 80.7% and xylitol productivity of 0.58 g/l-hr.
특수교육진흥법 규정의 분석과 해석 (2) : 주요 내용 및 절차 사항을 중심으로 Focusing on the Major Contents and Procedures
한현민,오세웅 국립특수교육원 2003 특수교육연구 Vol.10 No.2
본 연구는 특수교육진흥법의 규정을 체계적으로 분석·검토함으로써 그 개정의 방향을 제시하는데 목적이 있다. 본 연구에서는 1994년 특수 교육진흥법을 중심에 두고 이 법률이 특수교육에 관해 규정한 주요 내용과 절차 사항을 비판적으로 분석·검토하고, 이를 1977년 특수교육진흥법 규정과도 비교·논의하였다. 구체적으로 특수교육진흥법의 주요 규정을 특수교육의 성격과 범위(의무교육, 무상교육, 위탁교육, 공교육, 적절한 교육), 특수교육대상자의 선정과 배치(진단·평가, 심사, 선정, 배치), 특수교육대상자의 교육(개별화교육계획의 수립, 특수교육의 실시, 치료교육의 실시) 등 세 영역으로 대별하여 분석·해석한 다음, 1994년 개정 특수교육진흥법에 직·간접적인 영향을 미친 미국의 장애인교육법(IDEA: Individuals with Disabilities Education Act)과도 비교·논의하였다. 이러한 규정점토와 논의를 통해, '한국' 특수교육의 발전을 위한 법개정의 대안을 제안하였다. The present study was undertaken to systematically analyze and examine the provisions of the Special Education Promotion Law (SEPL) and ultimately to recommend the directions for the future revision of the law. The major contents and procedures regulated by the law amended in 1994 on the Korean special education were critically discussed and were compared with the law enacted in 1977. In the study, the major articles of the law were examined in terns of three important areas. First the discussion on the nature and the scope of special education included compulsory and/or free education, consigning special education to private special education institute, public education, and appropriate education. Second, the selection and placement procedures of the children with disabilities were reviewed. including diagnosis and evaluation, judgment, and selection of the children with disabilities, and their placement in the schools. Finally, the educational processes with the children with disabilities were analyzed and interpreted in the three aspects of individualized education planning, special education, and therapeutic education delivery. In addition, these contents and procedures were compared with the 1997 amendments of Individuals with Disabilities Education Act (IDEA) had directly and indirectly influenced the law revised in t994. Through these regulation examination and theoretical interpretation, the alternatives for the revision of the law were presented to further develop 'Korean' special education.
Oh, Hyun-Ung,Ha, Heon-Woo,Kim, Taegyu,Lee, Jong-Kwang The Korean Society for Aeronautical and Space Scie 2016 International Journal of Aeronautical and Space Sc Vol.17 No.4
A MEMS solid propellant thruster array shall be operated within an allowable range of operating temperatures to avoid ignition failure by incomplete combustion due to a time delay in ignition. The structural safety of the MEMS thruster array under severe on-orbit thermal conditions can also be guaranteed by a suitable thermal control. In this study, we propose a thermal control strategy to perform on-orbit verification of a MEMS thruster module, which is expected to be the primary payload of the STEP Cube Lab mission. The strategy involves, the use of micro-igniters as heaters and temperature sensors for active thermal control because an additional heater cannot be implemented in the current design. In addition, we made efforts to reduce the launch loads transmitted to the MEMS thruster module at the system level structural design. The effectiveness of the proposed thermo-mechanical design strategy has been demonstrated by numerical analysis.
Oh, Hyun-Ung,Lee, Myeong-Jae,Kim, Taegyu Hindawi Limited 2017 International journal of aerospace engineering Vol.2017 No.-
<P>A tilting calibration mechanism is periodically deployed to view the reference temperature target during on-board calibration of a spaceborne imaging sensor and stowed after calibration. In the present work, we have proposed a new design strategy using a shape memory alloy (SMA) spring as an actuator that provides a fail-safe function to prevent the blocking of the main optical path when the mechanical driving part of the mechanism is stopped at a certain position during on-board calibration. Although a launch locking device was not considered in the design, this approach makes it possible to impose mechanical constraints on the driving part of the mechanism in severe launch vibration environments. The effectiveness of the proposed design was experimentally validated by a deploying and stowing function test and launch vibration environment tests such as a sine burst test, a random vibration test, and a pyroshock simulating impulse shock test. The test results demonstrated that the mechanism fulfills all the required functions for on-board calibration. The use of an SMA spring actuator was proved effective for implementing the dual function of a fail-safe in an emergency phase and a mechanical constraint on the driving part of the mechanism in severe launch vibration environment.</P>
Ung-Kyu Choi,Hyun Su Ryu,Hyun Tae Kim,Sun Mi Yun,Su-Jin Lee,Jae Dek Choi,Young-Hyun Hwang,Soo Young Choi,Oh-Shin Kwon 한국식품과학회 2008 Food Science and Biotechnology Vol.17 No.5
This study was conducted to identify the differences in proteomic characteristics of ‘Agakong’, recombinant inbred line, and its parental genotypes ‘Eunhakong’ (Glycine max) and ‘KLG10084’ (G. soja). The isoflavone content of ‘Agakong’ was 3 times higher than that of its parental lines. A combined high-throughput proteomic approach was employed to determine the expression profile and identity of proteins using 2-dimensional gel electrophoresis and matrix-assisted laser desorption ionization time-of-flight (MALDI-TOF) mass spectrometry. The overall distribution patterns of proteins are quite similar, but lots of protein spot intensities varied among the genotypes. A total of 41 proteins, representing significant difference in the quantities of protein among the lines, were successfully identified. Among them, more than 50% of the proteins identified were subunits of glycinin and β-conglycinin, 2 major storage proteins. This study showed that the proteomic analysis could help to define specific changes in protein level and composition, which can occur in the generation of new soybean varieties.
Hyun-Ung Oh,Heon-Woo Ha,Taegyu Kim,Jong-Kwang Lee 한국항공우주학회 2016 International Journal of Aeronautical and Space Sc Vol.17 No.4
A MEMS solid propellant thruster array shall be operated within an allowable range of operating temperatures to avoid ignition failure by incomplete combustion due to a time delay in ignition. The structural safety of the MEMS thruster array under severe on-orbit thermal conditions can also be guaranteed by a suitable thermal control. In this study, we propose a thermal control strategy to perform on-orbit verification of a MEMS thruster module, which is expected to be the primary payload of the STEP Cube Lab mission. The strategy involves, the use of micro-igniters as heaters and temperature sensors for active thermal control because an additional heater cannot be implemented in the current design. In addition, we made efforts to reduce the launch loads transmitted to the MEMS thruster module at the system level structural design. The effectiveness of the proposed thermo-mechanical design strategy has been demonstrated by numerical analysis.