• CDE review
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• v.1 no.1
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• pp.38-46
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• 1995

STEP(Standard for the Exchange of Product Model Data)은 이기종 자동화 시스템 간에 제품정보를 교환하는데 사용되는 국제표준이다. 이 표준안은 ISO TC184/SC4에서 제정되고 있는데, 이 회의가 매년 3-4회씩 열리고 있다. 95년 3월에는 호주 시드니, 95년 6월에는 미국 워싱톤, 지난 10월에는 프랑스의 그레노블에서 개최되었다. 이 글에서는 그레노블 회의에 참석한 보고를 드리고자 한다. 말미에 수집자료 목록을 첨부하였으므로 관심있는 분들은 연락을 바란다.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.103-109
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• 2008

A study has been conducted on the bulging process of regenerative cooling nozzle which is essential for the manufacturing of liquid rocket thrust chamber. Tension tests have been performed for the material to be used for the development of the bulging process and mechanical properties are obtained by the test. Two or three bulging tools were required to complete the bulging process. The necking of the material was a major failure encountered in the bulging process and a research has revealed that grain size of the material has considerable effect on its occurrence. The presently developed bulging process with a controlled grain size material has been successfully applied to the manufacturing of subscale and 30-tonf full scale regeneratively cooled nozzle while demonstrating the applicability and usefulness of the presently developed bulging process.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.1416-1417
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• 2011

킹크효과를 억제할 수 있는 새로운 f-모양 트리플게이트 구조를 가지는 다결정실리콘 박막트랜지스터는 추가적인 공정과정 없이 제안 및 제작되었다. 이러한 다결정실리콘 박막트랜지스터의 채널에는 순차적인 횡방향 고체화(Sequential Lateral Solidification, SLS)나 CW 레이져 횡방향 결정화(CW laser Lateral Crystallization, CLC) 등과 같은 방법으로 제작된 횡방향으로 성장시킨 그레인이 있다. 이 소자의 전체적인 전류흐름은 횡방향으로 성장시킨 그레인 경계에 강력하게 영향을 받는다. f-모양 트리플게이트에는 횡방향으로 성장시킨 그레인과 평행한 방향으로 위치한 채널, 그리고 수직인 방향으로 위치한 채널이 있다. 이 소자는 f-모양 게이트 구조에서의 비대칭 이동도를 이용하여 다결정실리콘 박막트랜지스터의 킹크효과를 효과적으로 억제시킬 수 있다는 사실을 실험과 시뮬레이션을 통해 검증되었다. 우리의 실험 결과는 이 논문에서 제안된 f-모양 트리플게이트 박막트랜지스터가 기존의 박막트랜지스터와 비교할 때 더 효과적으로 킹크 효과를 감소시킬 수 있다는 것을 보여주었다. 또한 고온 캐리어 스트레스 조건에서의 신뢰성도 개선할 수 있음이 확인되었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.3
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• pp.271-278
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• 2008

A study has been conducted on the bulging process of liquid rocket engine nozzle which is essential to the manufacturing regenerative cooling combustion chamber. Mechanical properties of the material used for the bulging were experimentally obtained by tension tests. Deformation of the bulged nozzle was confirmed by a structural analysis. The developed bulging process and the deformation analysis result were confirmed by manufacturing of the bulged nozzle specimens and the bulging test. There has been a bulging failure among 7 bulged specimens due to the necking of the material. The cause of necking was investigated by comparing microstructure of the material. The investigation has revealed grain size of the material has considerable effect on the occurrence of the necking.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.233-236
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• 2007

In this paper, thermal sensitivity of the solid fuel grain in the hybrid rocket motor was investigated. When the heat from the non-reacting hot flow passing the grain ports is transferred to the solid fuel grain, the temperature fields in the solid fuel was numerically analyzed. These numerical analyzes were performed under the different nine port radii, and the critical distance between the ports in which the temperature in the solid fuel is sensibly responding was determined. Thus, the critical distance between the ports would be the important consideration for the design of the fuel grain because the high temperature in the fuel can bring the structural problems.

• The Transactions of the Korea Information Processing Society
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• v.7 no.1
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• pp.126-134
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• 2000

Version control is an application to maintain consistency between different instances of the same document allowing operations such as navigation, differencing, and merging. Most version control systems, however, lack the support of functionality for cooperative writing environment, such as to represent and store the history of the actions of different individuals, to effectively differentiate and merge the individual actions including the text object, and to manage different access privileges for different granularity and individuals. With the help of Activity IDentification (AID) tag and its unique addressing scheme proposed in this paper, differencing and merging become simple and effective. Access and role control is improved by associating the access right table and role assignment in AID scheme also eliminates the requirements for large storage capacity for version information maintenance.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.3
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• pp.22-31
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• 2022

Existing Finocyl grain designs assume configurations and repeat the process of configuration modification and confirmation of the requirements through burn-back analysis. Such a design increases the design fatigue of workers and has a problem of different design completeness depending on capabilities. Therefore, this study devised an optimal design method that applied genetic algorithms to the Burn-back automation analysis program to solve the problem of existing design. For stable search, variable-offset and non-drawable configuration control techniques were developed. The program performance was verified through the searching neutral and double thrust grains.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.30 no.4
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• pp.184-190
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• 2022

In an attempt to apply hybrid rocket to the RATO (Rocket-Assisted Take Off) system, combustion characteristics of the non-circular grain were figured out in this study. Having larger combustion area, it was reconfirmed that the non-circular grain has advantages over regression rate, characteristic velocity and chamber pressure in which all gave higher values. Experiments were performed to understand the effect of the non-circular grain geometry over time where local regression rates depending on grain location were analyzed. It was found that the regression rate of five distinct locations were different. Partial conclusion driven was that these differences are due to the heat transfer caused by dissimilar distances from the flame layer. Besides, as combustion duration increased, the fuel port became circular, and the regression rate converged to a single value over the whole grain.

• The Journal of the Acoustical Society of Korea
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• v.39 no.4
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• pp.371-377
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• 2020

Combustion instability occurred in the combustion test of solid rocket motor with large aspect ration Length/Diameter (L/D) and cylinder-slot grain. As a result of spectral analysis of the pressure perturbation, it was confirmed that the central axis longitudinal frequency was dominant, so that the length of the cylinder part was increased to eliminate the coincidence with acoustic node. In addition, acoustic modal analysis and flow analysis were performed to analyze the cause of instability by unsteady flow structure in solid rocket motors. It was confirmed that the combustion instability is reduced by quantitative comparison of the amplitude and frequencies of the pressure inside the combustion chamber using the grain shape before and after the design change. Finally, a combustion test was performed to verify that the combustion instability was resolved as in the flow analysis.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.957-967
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• 2017

Firing test of the fuel grain for solid fuel ramjet with additives and ignition support material was conducted. Fuel grain consist of HTPB mixed with AP particle 15 wt.%, Boron particle 5 wt.%. To cause the short ignition delay, ignition support consist of $NC/BKNO_3$ and composite propellant was coated to the fuel grain. An oxidant gas having a controlled temperature, pressure and oxygen composition close to the air condition in the ramjet combustor was supplied using the Ethanol blended $H_2O_2$ gas generator. Gas was set to flow at a mass flow rate of 150 g/s and mass flux of $200kg/m^2s$ in the grain port. Through the test, ignition support operated well and ignition delay of 0.5. During the test, stable chamber pressure with 8 bar and high combustion efficiency of 0.86 was confirmed.