• Proceedings of the Korean Society for Emotion and Sensibility Conference
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• 2001.11a
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• pp.112-116
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• 2001

본 연구는 자동차 시뮬레이터에서 필연적으로 발생하는 Sickness와 생리신호 간의 관련성에 대해 알아보고자 하였다. 이를 위해 Driving Simulator에서 중추신경계의 EEG 생리신호를 측정하고 이의 정량적 분석을 통하여 Simulator Sickness가 생리신호에 미치는 영향을 검토하였다. 중추신경계의 뇌파반응은 주행시간의 경과에 따른 특정 경향은 나타나지 않았으나 안정에 비해 delta파, theta파의 증가와 alpha파의 감소경향이 나타났다. 단, theta파는 초기 5분에 증가한 수치가 시간이 지남에 따라 그 비율이 일정하게 감소하는 것으로 나타났다. 또한 Sick그룹과 Non-Sick그룹 및 남녀그룹의 비교결과에 대한 유의한 차이가 인정되었다.

• Journal of Practical Agriculture & Fisheries Research
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• v.6 no.1
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• pp.41-49
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• 2004

This study was carried out to investigate the effects of temperature and photoperiod on the growth of Fagopyrum tataricum. It showed a tendency to promote the germination rate and plant height of tatary buckwheat under high temperature. Plant height and number of leaves were promoted in the order of 25>20>15>30℃ under the different temperature after 30 days of the planting. In the 10, 12, 14hr photoperiods at 20℃, plant height, number of leaves and dry weight were increased as much as photoperiod became long except by 16hr. Rutin contents was not regular both common and tatary buckwheat under the photoperiods. The rutin content in leaves was higher than stem. Compared to yield of tatary and common buckwheat, plant height, number of leaves, number of branch and stem diameter of tatary buckwheat increased more than common buckwheat. Especially, number of leaves was increased about 2.5 times more than common buckwheat. And there was a difference in about 2.1 times in grain weight and about 5.4 times in number of grains. Rutin content of plant parts was higher in the order of leaf>stem>grain in common buckwheat at the harvest. But it was higher with order of leaf>grain>stem in tatary buckwheat. Rutin content was 1469.8mg/100g in grain of tatary buckwheat. It was about 60 times higher than 22mg/100g in grain of common buckwheat.

• Journal of the Korea Concrete Institute
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• v.14 no.5
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• pp.708-717
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• 2002

Durability is a major concern in the design and construction of concrete structures which are located in the sea environments. In particular, the combined action of chlorides, sulfates, and carbonation nay influence greatly the deterioration behavior of concrete structures. The purpose of the present study is to explore the diffusion characteristics of chloride ions in concrete structures under combined deterioration conditions. The present test results indicate that the chloride penetration into concrete structures is more pronounced under combined attacks of chlorides, sulfates and carbonation. The diffusion coefficients and surface chloride contents were found to increase under combined multiple deterioration conditions. The present study provides quantitatively the penetration and diffusion characteristics of chloride ions in concrete structures under various deterioration conditions. The results of present study may be efficiently used for the realistic design of concrete structures under combined deterioration conditions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.892-897
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• 2011

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility(CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The fuel supply system modeling using AMESim was performed based on the results of the detailed design, and the fuel supply characteristics was analyzed in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.56-61
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• 2011

The deign and lay-out of a combustion chamber test facility(CTF), a turbopump real propellant test facility(TPTF), a rocket engine test facility for 3rd stage engine(SReTF), a rocket engine ground/high altitude test facility(ReTF, HAReTF) and a propulsion system test complex(PSTC) for KSLV-II is briefly described. The development/qualification tests of engine component, 3rd stage engine system and 75ton-class liquid rocket engine system will be performed in CTF, TPTF, SReTF, ReTF and HAReTF and the development test of 1st/2nd/3rd propulsion systems for KSLV-II will be performed in PSTC. These propulsion test facilities will be built in NARO space center considering construction schedule, cost, safety distance and utility factor of propulsion test facilities.

• Korean Journal of Plant Resources
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• v.18 no.2
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• pp.246-250
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• 2005

This study carried out to compared a rutin content in seed and plant of tartary buckwheat(Fagopyrum tataricum) to collect in the world. Rutin content in seed and plant parts of tartary buckwheat is higher than F. esculentum and F. cymosum. Rutin contents in plant parts of 3 species was higher with order of flower> leaf> seed> stem> root and that of tartary buckwheat was higher about 3.2 times in flower and about 3.1 times in stem and about 65 times in seed of F. esculentum. Compared to rutin contents for seed color and shape of tartary buckwheat 50 lines, seed color was higher with order of dark gray>black>brown and seed shape was higher with order of Slender> Notched> Round. Rutin content in plant parts of cultivated lines was higher than wild lines. Compared to rutin contents in plant parts of tartary buckwheat collected at the different region, Bhutan line had much higher than other lines. Rutin contents were lower than in the leaf and stem of Pakistan line and in the seed of India line.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.139-142
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• 2012

The deign and development status of a combustion chamber test facility(CTF), a turbopump real propellant test facility(TPTF), a rocket engine test facility for 3rd stage engine(SReTF), a rocket engine ground/high altitude test facility(ReTF, HAReTF) and a propulsion system test complex(PSTC) for KSLV-II is briefly described. The development/qualification tests of engine component, 3rd stage engine system and 75ton-class liquid rocket engine system will be performed in CTF, TPTF, SReTF, ReTF and HAReTF and the development test of $1^{st}/2^{nd}/3^{rd}$ propulsion systems for KSLV-II will be performed in PSTC. The CTF/TPTF are under construction such as ordering the long delivery items and the detailed design of ReTF/PSTC is being prepared.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.4
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• pp.87-92
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• 2012

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The fuel supply system modeling using AMESim was performed based on the results of the detailed design, and the fuel supply characteristics was analyzed in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.265-268
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• 2005

A series of ignition tests had been conducted for a thrust chamber propelled by Jet A-1 and liquid oxygen with a chamber pressure of 52.5 bara and a thrust of 30 tonf. The chamber ignited by a hypergolic fluid, TEAL, keeps its first constant pressure low at $63\%$ of the design value by $61\%$ of a liquid oxygen mass flow rate and $67\%$ of fuel for 0.25 sec. The operating O/F ratio of the chamber was kept at lower values than that of the design operating condition throughout the whole ignition procedure. Surge of the chamber pressure is below $6\%$ of the design value.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.88-93
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• 2017

For the control of pre-burner combustion pressure, the open angle of TTR(Throttle for Thrust Regulation) valve was varied from $143^{\circ}$ to $185^{\circ}$ while testing of cold flow, ignition, combustion. The major performance variables of rocket engine and hydraulic performance of TTR valve regarding the open angle was verified. However the controllability of pre-burner combustion pressure was not verified due to the limitations of test. The comprehensive research will be done after supplementing these problems.