• 유기물자원화
• /
• 제23권3호
• /
• pp.78-84
• /
• 2015

본 연구에서는 표면 메탄농도와 지구통계기법(거리역산가중기법)을 기초로 표면 메탄발산량을 평가하고자 하였다. 실험결과 표면 메탄농도는 표면 메탄발산량과 높은 상관성이 있는 것으로 나타나, 표면 메탄농도를 기초로 표면 메탄발산량을 산정하는 것이 가능한 것으로 나타났다. 또한 지구통계기법 적용 결과 측정 면적의 12.85%가 총 메탄발산량의 42.21%를 나타내어 챔버 방법으로 메탄발산량을 정확하게 평가하기 위해서는 지구통계기법을 반드시 적용해야 하는 것으로 사료된다.

• Carbon letters
• /
• 제2권3_4호
• /
• pp.192-201
• /
• 2001

The Carbon/Carbon composite was prepared from 3D carbon fiber preform and coal tar pitch as matrix precursor. In order to evaluate of ablative characteristics of the composite, liquid rocket system was employed Kerosene and liquid oxygen was used as propellants, operating at a nominal chamber pressure of 330 psi and a nominal mixture ratio (O/F) of 2.0. The results of an experimental evaluation were that high density composite exhibited high, while low density composites showed low erosion resistance. The erosion rate against heat flux was highly depended on the density of the materials. The morphology of eroded fiber showed differently according to collision angle with heat flux on the composite. The granular matrix which derived from carbonization pressure of 900 bar was more resistance to heat flux than well-developed flow type matrix.

• Journal of Astronomy and Space Sciences
• /
• 제16권2호
• /
• pp.177-190
• /
• 1999

An absorbed heat-flux method for ground simulation of on-orbit thermal environment of satellite is addressed in this paper. For satellite ground test, high vacuum and extremely low temperature of deep space are achieved by space simulation chamber, while spatial environmental heating is simulated by employing the absorbed heat-flux method. The methodology is explained in detail with test requirement and setup implemented on a satellite. Developed heat-load control system is presented with an adjusted PID-control logic and the system schematic realized is shown. A practical and successful application of the heat simulation method to KOMPSAT(Korea Multi-purpose Satellite)thermal environmental test is demonstrated, finally.

• 한국전기전자재료학회:학술대회논문집
• /
• 한국전기전자재료학회 2002년도 하계학술대회 논문집
• /
• pp.74-77
• /
• 2002

The channel of the superconducting Flux Flow Transistor has been fabricated with plasma etching method using ICP. The ICP conditions were 700 W of ICP power, 150 W of rf chuck power, 5 mTorr of the pressure in chamber and 1:1 of Ar : Cl$_2$, respectively. The channel etched by plasma gas showed superconducting characteristics of over 77 K and superior surface morphology. The critical current of SFFT was altered by varying the external applied current. As the external applied current increased from 0 to 12 mA, the critical current decreased from 28 to 22 mA. Then the obtained r$\sub$m/ values were smaller than 0.1Ω at a bias current of 40 mA. The current gain was about 0.5. Output resistance was below 0.2 Ω.

• 한국수소및신에너지학회논문집
• /
• 제12권2호
• /
• pp.147-155
• /
• 2001

To measure of thermal loading in the combustion chamber of hydrogen engine with dual injection, instantaneous wall-surface temperature and unsteady heat flux of the cylinder head are measured and analyzed. The maximum wall surface temperature is shown in direct injection region which has large heat supplied. Partial and spatial temperatures have slight deviation in transient region of injection, though injection method change suddenly. All of thermal characteristics such as instantaneous temperature, temperature swing and heat flux of hydrogen engine with dual injection are remarkably higher than those of gasoline engine. It means necessity of additional countermeasure of thermal loading.

• 한국추진공학회지
• /
• 제7권2호
• /
• pp.54-61
• /
• 2003

본 연구에서는 액체로켓에서 널리 사용되는 재생냉각시스템이 장치된 실험용 액체로켓 엔진을 설계하고 제작하여 연소실험을 수행한 내용을 다루었다. 설계 프로그램을 이용하여 엔진을 설계하였고 이를 바탕으로 엔진을 제작하였다. 연소실험을 통해 측정한 열유속이 계산에 의한 해석결과와 유사하므로 실제로켓엔진의 설계 및 제작에 설계 프로그램을 이용할 수 있음을 확인하였다. 또한 연소시 생성된 탄소층이 냉각성능에 미치는 영향을 간단히 고찰하였다.

• 한국전기전자재료학회논문지
• /
• 제16권5호
• /
• pp.424-428
• /
• 2003

The channel of a superconducting flux flow transistor has been fabricated with plasma etching method using a inductively coupled plasma etching. The ICP conditions then were ICP Power of 450 W, rf chuck power of 150 W, the pressure in chamber of 5 mTorr, and Ar : Cl$_2$=1:1. Especially, over the 5 mTorr, the superconducting thin films were not etched. The channel etched by plasma gas showed the critical temperature over 85 K. The critical current of the SFFT was altered by varying the external applied current. As the external applied current increased from 0 to 12 mA, the critical current decreased from 28 to 22 mA. Then the obtained trans-resistance value was smaller than 0.1 $\Omega$ at a bias current of 40 mA.

• International Journal of Korean Welding Society
• /
• 제1권1호
• /
• pp.71-77
• /
• 2001

The characteristics of the fume generation in a flux cored arc welding were investigated using the fume collection chamber developed. The Korean Standard concerning the method for the evaluation of the fume generation rate(FGR) was updated by the evaluation method obtained through this study. It was found that the effect of humidity in the test environment should be considered and the automatic welding method had to be employed for the purpose of the exact evaluation of the fume generation rate. The results showed that the fume generation rate was influenced by the welding parameters. The important factors were the welding current arc voltage, travel speed, and contact tip to work distance(CTWD) that affected the heat input as well as the torch angle and the shielding gas flow rate that influenced the shielding effect. The fume generation rate increased as the heat input increased and the shielding effect decreased. It was also observed that the effect of the welding current is much grater than the other welding parameters.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2003년도 제21회 추계학술대회 논문집
• /
• pp.78-82
• /
• 2003

우주발사체의 2단용 엔진으로 10톤급 케로신 재생 냉각 방식의 액체로켓엔진에 대한 보조 냉각 기구로서, 막냉각을 고려한 냉각특성에 대한 해석적 연구를 수행하였다. 연소기내에서 연소가스의 유동이 축방향으로 층류화되어 있다는 개념하에, 엔진 단면을 서로 독립적인 중심부와 외곽부로 나누며, 외곽부에는 여분의 연료를 분무시킴으로써 연소가스 온도를 낮추어 냉각채널로 전달되는 열유속량과 벽면 온도를 감소시킬 수 있었으며, 엔진의 열적 안정성을 향상시킬 수 있었다.

• 한국군사과학기술학회지
• /
• 제12권3호
• /
• pp.396-405
• /
• 2009

The experimental research was conducted to setup a performance prediction logic for the regenerative cooling system on a small scale liquid rocket engine using kerosene and LOX. Total heat flux of the combustion gas side was determined for the flow rate of the coolant, combustion pressure using the calorimeter thrust chamber. Based on the experimental investigation, a performance prediction scheme for the regenerative cooling system is setup in our own way. A performance prediction logic for the regenerative cooling system has been developed by the correction scheme of the combustion gas side. The key parameters determining the temperature limitation of the coolant are the mass flow rate of the coolant and the length of the combustion chamber and the nozzle. And the parameters to control the limitation of the usable wall temperature are the number of channels and wall thickness.