• Proceedings of the KAIS Fall Conference
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• 2009.05a
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• pp.143-146
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• 2009

소형엔진은 매우 열악한 환경에서 작동하게 되는데, 이러한 엔진으로 흡입되는 공기를 정화하는 흡기시스템은 매우 중요한 설계인자이다. 본 연구는 이러한 소형엔진에 적용하기 위한 흡기시스템을 개발하고, 효율적인 개발 업무를 진행할 수 있도록 하는데 그 목적을 두었다. 기초 자료를 확보하기 위하여 3가지의 기본 모델을 제작하였다. 이를 바탕으로 유동 해석 및 엔진 특성 분석을 통해 기존 사양 대비, 우수한 성능을 보이는 모델을 제시하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.4
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• pp.67-74
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• 2001

Based on the national space development project, the necessity of developing liquid propellant rocket engine is revealed to secure the basic technology for the development of individual artificial-satellite launcher. Consequently, KARI (Korea Aerospace Research Institute) is developing a liquid propellant rocket engine for the KSR-III. Currently, a prototype engine using kerosene/LOx which produces 13-ton thrust is designed, fabricated and tested. In this paper, test procedure and technique for liquid propellant rocket engine are introduced with the analysis of static and dynamic test data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.5-5
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• 2000

이 연구의 목적은 한국항공우주연구소가 개발 중인 액체추진제 로켓엔진의 축소형 엔진에 대하여 인젝터 배열의 변화가 성능 및 연소특성에 미치는 영향을 분석하는데 있다. 인젝터의 배열방식에 따라 방사형(radial) 및 직교형(H-type) 인젝터를 연구대상으로 하였으며 충돌각의 변화에 2차원 및 3차원 해석을 수행하였다. 로켓엔진에는 스월러 인젝터를 고려하지 않았기 때문에 인젝터의 배열 및 충돌 각은 엔진성능뿐만 아니라 연소특성에도 중요하게 영향을 미치는 인자가 된다.(중략)

• Proceedings of the Korea Information Processing Society Conference
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• 2011.11a
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• pp.992-995
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• 2011

ALADDIN(Advanced Layer-free DDoS Defense INfrastructure) 시스템은 양방향 10Gbps 트래픽을 처리할 수 있는 안티 DDoS 전용 시스템이다. 로드 밸런서 엔진, 안티 DDoS 분석 엔진, PCI-Express 엔진으로 구성된 세 개의 FPGA 기반 하드웨어 엔진과 소프트웨어 엔진으로 이루어진 시스템은 인라인 모드로 동작하면서 Wire-speed 로 패킷을 처리한다. 시스템은 네트워크 레벨의 DDoS 공격뿐만 아니라 어플리케이션 레벨의 DDoS 공격도 실시간으로 탐지하고 대응한다. 본 논문에서는 ALADDIN 시스템의 설계 및 구현, 테스트 결과에 대해 기술한다.

• 한국HCI학회:학술대회논문집
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• 2008.02b
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• pp.304-309
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• 2008

The development in information technology allowed most of the information around us into digital information, in other words, a database. The innovation increased the accessibility and helped this society change into an informational age. However, there is a shortcoming of this open source as the users have difficulty in assorting the information that s/he needs and realizing if the information provided is important. Therefore, the need for search engine has risen in such a way to increase the accessibility and facilitation of information provided to the users through searching the necessary information in the database by an easy and accurate way. This study aims to increase the utilization of search engine through relationship analysis between purpose of user and interface design factors of search engine. Also, it intends to propose design guidelines for search engine interface design in order to increase user satisfaction and usability. This study categorized and correlated the relationships of the purpose in using the search engine and types of search engine interfaces. This study explicates the critical properties in designing each search engine interface according to the purpose of the users in using them. Also, this study proposes recommendations for appropriate design guidelines for search engine interface and effective advertisement use through properties of interface and their importance. The search engine interface suggested from the result provides interface that allows efficient search for desired information and embrace a variety in users, eventually increasing the usability in search engine.

• Proceedings of the Korea Multimedia Society Conference
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• 2002.11b
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• pp.5-8
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• 2002

전자상거래의 보편화와 더불어 인터넷 쇼핑몰이 급격히 늘어나면서 선택의 폭이 커짐과 동시에 고객에게는 선택의 불편이 있고, 판매자에게는 경쟁이 가중될 것이므로 더욱 치밀하고 편리한 마케팅 기법이 요구되어지고 있다. 따라서 인터넷 쇼핑몰에서의 개별고객의 니즈를 파악하기 위한 다양한 분석적 접근이 이루어지고 있다. 웹 데이터마이닝은 웹사이트에 접근한 사용자들의 개인별 접근패턴을 파악하고 예측하기 위해 로그파일을 분석한다. 본 연구에서는 eCRM의 핵심요소인 로그분석을 위한 데이터마이닝 엔진을 설계하고 구현한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.3
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• pp.17-26
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• 2004

In this paper, power transmission systems converts the shaft power of a Turbo-shaft Engine with Free Power Turbine into the generator power and be composed of a method being supplied in the thrust motor driving a propellers. Being used this, Gas turbine engine works to flat rating about 110 kw (147 shp) that the thrust motor be extremely supplied from the engine of 317shp. In this test equipment, the engine is installed with the flywheel being able to the damping function when happen to the varying load between gas turbine engine output-shaft and generator. Then if the flywheel of inertial moment be not considered, the generator and motor not get the required power from the engine for raising the load. Also it is certified that the engine works the abnormal operation. Hence the flywheel of inertial moment is determined the required range to do the performance analysis with the dynamic transient from the given and tested engine data. This system is able to get the required power after a mounting test with the redesigned flywheel.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.95-101
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• 2004

Stability rating of KSR-III rocket engine is conducted based on stability rating tests in the course of development of KSR-III rocket engine. Rocket engine is approved to have combustion stabilization ability when it can suppress the external perturbation or pressure oscillation with finite amplitude and recover the original stable combustion. Rocket engine in flight may be perturbed by unexpectedly large-amplitude pressure oscillation and thus a designer should not only assure combustion stabilization ability of the engine but also quantify the stabilization capacity. For this, principal quantitative parameters and their evaluation are introduced. To verify dynamic stability of KSR-III rocket engine, six stability rating tests have been conducted. Based on these test results, such parameters are quantified and thereby, the stabilization capacity of KSR-III rocket engine is evaluated.

• Journal of Korea Game Society
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• v.3 no.2
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• pp.56-63
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• 2003

This research is a result of the study of 3D online game engine supported by korea science foundation in third year. The 3D engine and server engine have been upgraded from those in second year. A demonstration game has been made using our engines. Source codes of our engines have been distributed to several research centers for analysis and evaluations. The methodology of game development using our engines is described as well as the efficiency of our engines. In this paper, features and performance of the proposed engines are described as well as the methodology of utilizing the engines.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.144-152
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• 2011

In order to investigate the operation performance behaviors of the UAV's propulsion system to be operated long time in high altitude, the engine performance tests, which are simulated in the altitude engine test facility should be needed. If the test is performed in a existing altitude engine test facility, additional test apparatuses are required. Among them a proper design of the inlet and exhaust ducts that may directly affect the engine performance is very important. If the design is not adequate, the engine performance loss due to the flow behavior change and the pressure loss may be not similar to the real engine performance. In this work, firstly the engine inlet and exhaust ducts to be mounted to the existing altitude facility are modelled in 3D and its flow behaviors and pressure losses are analyzed using a commercial CFD tool, ANSYS's CFX, and the engine performance with the duct losses is calculated using the performance analysis program developed by C. Kong et al. Finally, the optimized inlet and exhaust ducts' configurations are proposed through the repeated analyses of various duct configurations.