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Bio-based chiral dopants having an isohexide skeleton for cholesteric liquid crystal materials
Shin, Seunghan,Seo, Jae Won,Cho, Jin Ku,Kim, Sangyong,Cha, Jaeryung,Gong, Myoung Seon The Royal Society of Chemistry 2012 Green chemistry Vol.14 No.4
<P>Chiral dopants were synthesized from bio-based epimeric isohexides (glucose-derived isosorbide and mannose-derived isomannide) and their phase transition behaviors and abilities for developing cholesteric liquid crystal (CLC) films were examined with a consideration of the core structure. In spite of lower reactivity of the <I>endo</I> hydroxy group of isomannide caused by the steric hindrance and intermolecular hydrogen bonding, final synthetic yields of chiral dopants bearing an isomannide core (64.5% for IH-2 and 65.0% for IH-4) did not show conspicuous difference compared with chiral dopants bearing isosorbide (68.4% for IH-1 and 74.0% for IH-3). On the other hand, in phase transition behaviors, chiral dopants bearing an isomannide core showed lower crystalline and melting temperatures than IH-1, IH-3 despite of the same substituents. The helical twisting power (HTP) of chiral dopants bearing isosorbide (IH-1 and IH-3) was higher than that of chiral dopants bearing isomannide (IH-2 and IH-4). The calculated HTPs of IH-1 and IH-3 were 26.6 and 42.1 μm<SUP>−1</SUP>, respectively. In the case of IH-3, the helical pitch length of CLC could be adjusted to reflect visible light by controlling its amount and showed best performance in the range 5.0 to 7.0 mol%. In contrast to IH-1 and IH-3, it was found that IH-2 and IH-4 could not induce CLC films that reflect visible light.</P> <P>Graphic Abstract</P><P>Chiral dopants were synthesized from bio-based isohexides and applied to cholesteric liquid crystal materials. <IMG SRC='http://pubs.rsc.org/services/images/RSCpubs.ePlatform.Service.FreeContent.ImageService.svc/ImageService/image/GA?id=c2gc16261j'> </P>
김승한(SeungHan Kim),김성룡(SeungRyong Kim),김성혁(SungHyuk Kim),김채형(ChaeHyung Kim),서대반(DaeBan Seo),우성필(SeongPil Woo),유병일(ByungIl Yu),소윤석(YoonSeok So),이광진(KwangJin Lee),이승재(SeungJae Lee),이정호(JungHo Lee),임지혁(Ji 한국추진공학회 2016 한국추진공학회 학술대회논문집 Vol.2016 No.12
한국형발사체 1단 엔진 개발을 위한 엔진시스템 시험으로 액체산소-케로신을 추진제로 하는 75 톤급 액체로켓엔진의 연소 시험이 수행되었다. 한국형발사체 1단용 75 톤급 엔진시스템 시호기를 이용하여 연소기, 터보펌프, 가스발생기, 파이로 구성품 및 공급계 부품을 포함하는 엔진시스템 연소시험 결과를 소개한다. 액체산소-케로신 추진제 엔진시스템의 시동 절차를 개발하기 위해 실추진제를 이용한 연소 조건에서의 엔진시스템의 시동 및 점화, 정상 구간 작동, 종료가 성공적으로 수행되었다. 75톤급 엔진 연소시험 결과는 한국형발사체 1단용 엔진시스템 설계 개선에 활용될 예정이다. As a first phase of the 75 tonf LOx/Kerosene liquid rocket engine development for KSLV-II first Stage Engine, hot firing test of 75 tonf engine are performed. The results of firing test on first stage 75-tonf engine system including combustion chamber, turbopump, gas generator, propellant supply system are presented. For the development of startup sequence of LOx-Kerosene engine system, engine startup using pyrostarter, ignition of gas generator, steady operation and engine shutdown is successfully performed. The results of hot firing test of 75 tonf thrust engine system will be used for the determination of startup sequence of 75 tonf engine system for KSLV-II first Stage.
김승한(SeungHan Kim),김성룡(SeungRyong Kim),김성혁(SungHyuk Kim),김채형(ChaeHyung Kim),서대반(DaeBan Seo),우성필(SeongPil Woo),유병일(ByungIl Yu),소윤석(YoonSeok So),이광진(KwangJin Lee),이승재(SeungJae Lee),이정호(JungHo Lee),임지혁(Ji 한국추진공학회 2017 한국추진공학회 학술대회논문집 Vol.2017 No.5
한국형발사체 1단 엔진 개발을 위한 엔진시스템 시험으로 액체산소-케로신을 추진제로 하는 75 톤급 액체로켓엔진의 연소 시험이 수행되었다. 한국형발사체 1단용 75 톤급 엔진시스템을 이용한 개발연소 시험 현황을 연소기, 터보펌프, 가스발생기, 파이로 구성품 및 공급계 부품을 포함하는 엔진시스템 연소 시험 결과를 포함하여 소개한다. 액체산소-케로신 추진제 엔진시스템의 시동 및 점화, 정상구간 작동, 종료가 안정적으로 수행되었으며, 엔진 연소 시험 중 엔진 추력 제어 시스템의 검증 시험도 성공적으로 수행되었다. 75 톤급 엔진 연소시험 결과는 한국형발사체 1단용 엔진시스템 설계 검증 및 성능 평가에 활용될 예정이다. As a development test of the 75-tonf LOx/Kerosene liquid rocket engine for KSLV-II first Stage Engine, hot firing test of 75-tonf engine are performed. The current status of development test on first stage 75-tonf engine system including combustion chamber, turbopump, gas generator, propellant supply system are presented. During the 75tonf engine test campaign, the development of startup sequence of LOx-Kerosene engine system, engine startup using pyrostarter, ignition of gas generator, steady operation and engine shutdown is successfully performed. As a passenger test during engine hot firing tests, Thrust Vector Control system (TVC) of the engine are also evaluated during engine hot firing test. The results of hot firing test of 75-tonf thrust engine system will be used for the design confirmation and performance evaluation of 75 tonf engine system for KSLV-II first Stage.