• Korean Chemical Engineering Research
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• v.52 no.3
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• pp.302-306
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• 2014

The present study was carried out to optimize fermentation parameters for the production of cellulolytic enzymes through solid substrate fermentation of Trichoderma reesei and Aspergillus niger grown on wheat straw. A sequential optimization based on one-factor-at-a-time method was applied to optimize fermentation parameters including temperature, pH, moisture content and particle size. The results of optimization indicated that $40^{\circ}C$, pH 7, moisture content 75% and particle size between 0.25~0.5 mm were found to be the optimum condition at 96 hr fermentation. Under the optimal condition, co-culture of T. reesei and A. niger produced cellulase activities of 10.3 IU, endoglucanase activity of 100.3 IU, ${\beta}$-glucosidase activity of 22.9 IU and xylanase activity of 2261.7 IU/g dry material were obtained. Cellulolytic enzyme production with optimization showed about 72.6, 48.8, 55.2 and 51.9% increase compared to those obtained from control experiment, respectively.

• The Bulletin of The Korean Astronomical Society
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• v.43 no.1
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• pp.71.2-71.2
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• 2018

태양계 질량의 대부분은 플라즈마, 기체, 또는 액체 상태로 존재하며, 극히 일부만이 고체 즉 암석과 광물로 존재한다. 하지만, 반응 특히 혼합(mixing)이 일어나는 속도가 매우 느린 고체의 특성상 태양계의 탄생과 진화 과정의 기록은 고체태양계 물질에 더 잘 보관되어 있다. 지구를 제외한 고체 태양계 물질을 확보하기 위해서는 지구로 낙하한 암석인 운석(meteorites)을 발견하거나, 우주로 나가 시료를 가져와야 한다. 아폴로 미션(Apollo mission)에 의한 월석(lunar rocks) 채취(Papike et al., 1998), 하야부사 미션(Hayabusa mission)에 의한 소행성(asteroid) 시료 채취(Nakamura et al., 2011), 스타더스트 미션(Stardust mission)에 의한 혜성 시료 채취(Zolensky et al., 2006) 등이 후자에 속한다. 능동적으로 가져온 시료는 아직까지는 그 종류와 양에서 운석에 비해 매우 부족하므로 현재까지 우리가 알고 있는 고체 태양계에 관한 대부분은 운석 연구를 통해 얻어졌다. 운석은 크게 미분화운석 즉 콘드라이트(chondrites)와 분화운석(differentiated meteorites)으로 구분한다. 분화운석 중 일부는 달운석(lunar meteorites) 또는 화성운석(martian meteorites)이며, 나머지 분화운석과 콘드라이트는 암석-지구화학적 특징과 성인적 연관성에 의해 다양한 그룹으로 세분되는데 각 그룹은 하나의, 또는 둘 이상의 매우 유사한, 소행성에서 유래한 것으로 해석된다(Krot et al., 2014; 최변각 2009). 다양한 종류의 운석과 구성 광물에 포함된 기록으로는 (1) 태양계 이전 존재한 항성의 대기에서 생성된 광물, 즉 선태양계 광물(presolar grains), (2) 태양계 성운 탄생과 각 진화 단계의 정확한 시기, (3) 태양계 성운의 화학조성-동위원소 조성, 온도-압력 조건 등을 포함한 물리-화학적 특징, (4) 가스-먼지로부터 미행성, 소행성, 행성으로의 진화 과정, (5) 행성 진화의 열원, (6) 소행성 핵의 생성 과정 등이 있다. 강연에서는 이들을 간략히 살펴보고자 한다. 운석연구 등을 통해 태양계 생성과 진화과정에 관한 다양한 정보가 축적되었지만, 앞으로 연구할 것들이 더 많다. 또한 태양계 물질 중에는 운석의 형태로 지구로 들어왔거나 앞으로 들어올 수 있는 것도 있지만 그렇지 않은 것도 있다. 가스나 기체의 경우가 그러할 것이며, 고체지만 결합이 약해 일부라도 원형을 유지한 채 대기권을 통과 할 수 없는 것도 있을 것이다. 또 공전궤도나 중력 등 물리적 이유로 지구권 진입이 불가능한 것도 있다. 이러한 태양계 구성원에는 우리가 아직까지 얻지 못한 정보들이 다량 보존되어 있을 것이다. 미래의 태양계탐사가 기대되는 이유 중 하나이다.

• Journal of the Korean Society of Radiology
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• v.10 no.8
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• pp.577-582
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• 2016

This study is aimed to prove that a solid sialogogue can improve the defects of the liquid one and substitute it with no differences in the signal intensity. From January to August 2016, 60 patients with no salivary gland diseases were enrolled. The patients were divided into two groups as follows; a group with a liquid sialogogue and the other group with a solid sialogogue. MR images were acquired and signal intensities of the parotid glands were compared. As a result, the signal intensities of liquid and solid sialogogues showed no statistically significant differences($59.42{\pm}15.74$ and $61.80{\pm}13.99$, respectively) In conclusion, a solid sialogogue was verified to have no signal intensity differences from the liquid one while it could improve the defects of the liquid sialogogue.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.9
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• pp.802-808
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• 2014

MEMS based solid propellant thruster researched for the purpose of an academic research will be verified at space environment through CubeSat program. For this, the temperature of the MEMS thruster should be within allowable operating temperature range by proper thermal control to prevent the ignition failure caused by ignition time delay and to guarantee the structural safety of the MEMS thruster in the low temperature. In this study, we proposed an effective thermal control strategy, that is to use micro-igniter as a heater and temperature sensor for active thermal control instead of using additional heater. The effectiveness of the strategy has been verified through on-orbit thermal analysis of CubeSats with MEMS thruster.

• Polymer(Korea)
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• v.36 no.4
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• pp.500-506
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• 2012

In this study, we developed and optimized hydrophilic polymer based solid dispersion formulations (SDs) for enhancing the aqueous solubility of eprosartan, one of poorly soluble drugs, that has been broadly used for the treatment of high blood pressure. Poly(ethylene glycol) (PEG) and poly(vinyl pyrrolidone) (PVP) based SDs were prepared by hot melting and solvent evaporation methods and the drug/polymer composition varied in the range of 1:1~1:5 with or without poloxamer 407 (P407) as a polymeric surfactant. The SDs prepared by solvent evaporation showed more reduced crystallinity than ones by hot melting, and PVP based SDs showed more enhanced solubility and lower crystallinity than PEG based SDs. Furthermore, it was observed from DSC and PXRD analysis that the SDs with P407 (drug:polymer: P407 = 1:5:1) demonstrated no crystallinity and the most enhanced solubility (more than 3~4 times).

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.6
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• pp.581-586
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• 2008

The MEMS solid propellant thrusters have very low thrust level for applying to the propulsion system of micro/nano satellites or the side jet thruster of smart bombs. In this research, the fabrication possibility of planar type MEMS solid propellant thrusters that have enlarged burning surface area was examined and the safety of the structure of thruster during the firing test was confirmed. The performance of a micro igniter which is the key component of the MEMS solid propellant thruster was estimated by the ANSYS Icepak and evaluated by the experiment. Finally, the thrust was measured by the micro force sensor. The levels of thrust were 300, 600 mN in the case of K=15, 20.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.207-210
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• 2008

We developed an integrated design system for a solid rocket motors. We can do a conceptual design of a solid rocket motor easily and quickly with this system. It consists of four modules, or, size design, structure design, grain design and performance analysis module. Size design module determines the lengths and diameters of some major parts, which results in fixing the whole size of a motor. Structure design module has many master models, which enables a designer can do a conceptual design of almost parts of motor structures. Grain design module can design a solid fuel according to the result of structure design. Finally performance analysis module verifies the proposed design with the output from grain design module.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.5
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• pp.12-18
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• 2014

A study of gas generator Fuel-Rich propellant for air-breathing propulsion system was performed in this paper. General solid propellant comprises a mean of 60% or more oxidizing agents. but, to develop the fuel-rich solid propellant increased the content of the metal fuel and reduced the content of the oxidizing agents by approximately 30%. Very high amount of heat per volume of fuel into the metal having the Boron was used. Amorphous Boron Powder was applied to propellant as beads type and it allowed to design more amount of metal fuel in the fuel-rich propellant. And the Combustion characteristics and properties of fuel-rich solid propellant according to the Boron-bead sizes were confirmed.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.2
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• pp.57-62
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• 2013

A crack in a solid propellant increases the area of burning surface, which leads to excessive burning that causes motor failure. Therefore, it is necessary to evaluate fracture toughness of solid propellants. However, it is very difficult to measure fracture toughness of solid propellants because of the nonlinear mechanical behavior. In this study, evaluation of fracture toughness on a solid propellant was carried out under the assumption that the solid propellant is a linear viscoelastic material. Actual displacements from fracture toughness tests using CCT specimens were converted into pseudo-elastic displacements by using stress relaxation characteristics and fracture toughness was evaluated using ASTM E399 standard. Also, effects of test temperature and speed on the fracture toughness were considered.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.1
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• pp.8-16
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• 2017

Structural integrity of solid rocket depends on the residual reactions between constituents of its composition(post cure, migration etc.), the oxygen(or anti-oxydent) in the free volume and humidity (desiccant) under the perfect sealed condition. Mechanical Properties of composite solid propellant arising from those factors are very complex. Moreover the propulsion are faced with thermal loads from diurnal & seasonal cycle till firing. In this study, the fast evaluation method of long term mechanical properties is suggested based on Thermo-Rheological Simplicity from curing oven to cool-down stage in view point of thermal stabilization. For this subject, endurance tester having temperature control capability are devised. From the results from incremental load and strain, non-linear characteristics are discussed.