• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.193-201
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• 2013

Propeller is an important component of Human Powered Aircraft (HPA) propulsion system. HPA uses large diameter low rotational speed propeller to get high propeller efficiency. The propeller was designed by HPA propeller designing program. The propeller pitch is adjustable by rotating the blade axis angle at ground. Performance of the propeller for various parameters are analysed by the same program used for design. Off-design condition performance was also checked including pilot power change and flight speed change. The propeller was manufactured in ultra-light structure using carbon composite material down to 950g. The propeller was ground tested on ironbird and installed on KARI HPA. Finally the HPA flew 291m with this propeller.

• Proceedings of the KSR Conference
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• 2008.06a
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• pp.603-609
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• 2008

Nowadays, double-system of TFM(Track-side Functional Modules) developed instead of single-system in use of high speed line to acquisition more availability. Safety Law for Railroad recommend to quality certification of development and general railway machines. It is important to select metrics which form the bases for testing software products. A number of package software development part do not open source cords, so testing external characteristic vectors having relationship with metrics. In this paper, review the process for the TFM Point Modules, Universal Modules and Switchers, think about the test methode of circuit boards output performance by using TFM tester and Simulators.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.277-284
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• 2017

This study is the results of the analytical research for a dual-model scramjet engine flowpath which is included inlet, isolator, combustor, and nozzle. To design a dual-mode scramjet engine and to investigate its performance, the performance analysis models and tools are required to develope for aerodynamic, thermodynamic characteristics, propulsion, and total system. Therefore, analysis models for air inlet, isolator, supersonic combustor, and nozzle of a dual-mode scramjet engine were accomplished, the performance characteristics of a dual-mode scramjet engine is investigated with using the developed analysis tools.

• Journal of Digital Convergence
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• v.16 no.2
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• pp.189-194
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• 2018

This study reflects the current trend of the blind hiring culture focused on job competency rather than education specification as government initiative. In order to overcome the limitation of the existing document-oriented online recruitment process, we proposed a system architecture design of video interview system. In addition, we have evaluated the effectiveness through the development of prototype and performance experiment based on it. The proposed online video interview system is designed to combine intelligent Web technology to enable customized job matching and distant job coaching. This system is designed to reduce recruitment cost and opportunity cost of job seekers. Based on results derived from this study, commercialization of the proposed video interview system can be expected to be an practical online recruitment solution for the job competency based employment.

• Proceedings of the KIEE Conference
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• 2007.07a
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• pp.729-730
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• 2007

선진국의 경우 송전용 애자의 내구성 향상을 위한 새로운 평가 기법을 적용하여 신뢰성을 향상시키는 등 연구가 활발하지만 국산 송전용 애자에 대한 열화요인 진단 및 대체기술은 거의 초기 연구 단계에 불과하다. 따라서, 국내 송전 선로 환경에 따른 송전용 애자의 구성 요소별 장기 열화요인 분석 기술의 부족을 극복할 필요가 있다. 모든 형태의 절연물은 사용 환경에 따라 열화에 따른 품질 저하는 피할 수 없다. 이에따라 초기 설계에서 최종적인 품질 확인 시험까지 적절한 불량 요인을 진단하여 개선 할 수 있는 제조공정과 경년품에 대한 정기적인 열화 시험 평가 등을 통해 송전용 자기애자의 신뢰성을 유지하는 것이 필요하다. 송전용 현수 애자의 수명과 신뢰성을 결정하는 요인은 복합적이며, 적정한 시료수와 통계적 접근 방법을 동원하여 분석하는 것이 최선이다 자기 애자의 수명에 영향을 주는 핵심 인자는 시멘트 및 자기부의 강도 저하로 알려져 있다. 기본적인 단품 성능시험을 실시한 결과, 냉열 및 급준파 특성에 대한 내구성이 문제점으로 도출되었다. 물론 특정 경년품(1989년도 제품)에서 집중적으로 불량이 발생한 것이지만, 이것은 일반적으로 문제가 있는 자기 애자에서 발생하는 전형적인 형태이다. 현재 가장 문제가 되는 것은 급준파 및 내아크 시험과 같이 열적, 기계적 충격에 대한 내구성을 확인하는 열화 평가방법이 요구된다. 본 연구에서는 경년품 및 신품에 대한 냉열 가속, 경년 가속 열화시험 및 급준파 열화시험과 현수 애자의 핵심 소재인 자기의 HRB 경도 특성 시험하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.4
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• pp.1-11
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• 1999

Thermal behavior of spacecraft propulsion system utilizing monopropellant hydrazine ($N_2$$H_4$) is addressed in this paper. Thermal control performance to prevent propellant freezing in spacecraft-operational orbit was test-verified under simulated on-orbit environment. The on-orbit environment was thermally achieved in space-simulation chamber and by the absorbed-heat flux method that implements an artificial heating through to the spacecraft bus panels enclosing the propulsion system. Test results obtained in terms of temperature history of propulsion components are presented and reduced into duty cycles of the avionics heaters which are dedicated to thermal control of those components. The duty cycles are subsequently converted into the electrical power required in the operational orbit. Additionally, cyclic temperature of each component, which was made under thermal-balanced condition of spacecraft, is compared to the acceptable design range and justified from the viewpoint of system verification.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.35 no.4
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• pp.417-424
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• 2011

A fuel assembly consists of five major components, i.e., a top end piece (TEP), a bottom end piece (BEP), spacer grids (SGs), guide tubes (GTs) and an instrumentation tube (IT); in addition, it also includes fuel rods (FRs). The TEP/BEP should satisfy stress intensity limits according to the conditions A and B of ASME, Section III, Division 1-Subsection NB. In a dual-cooled fuel assembly, the array and position of fuel rods are different from those in a conventional PWR fuel assembly; these changes are necessary for achieving power uprating. The flow plates of the TEP and BEP have to be modified accordingly. The pattern and shape of the flow holes were newly designed. To verify the strength compatibility, the Tresca stress limit according to the ASME code was investigated in the case of an axial load of 22.241 kN. In this paper, the stress linearization procedure for strength evaluation of a newly designed TEP is presented.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.41 no.10
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• pp.1005-1009
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• 2017

In this study, the shock resistance of a gas turbine package subjected to a shock load caused by non-contact underwater explosion was investigated using numerical analysis. To perform shock analysis, the time-history shock load was calculated according to BV-043 (German Navy Regulation). The direct transient response analysis in the time domain for the simplified Whole Engine Model (WEM) was performed using the calculated shock load. In addition, the structural integrity of a detailed model was evaluated by considering the shock load transferred to each component. As a result, it was confirmed that the safety factor was at least 1.0 as compared with the reference stress. Finally, the structural and functional integrity of the Engine Management System (EMS) of the gas turbine package was verified through an actual shock test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.5
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• pp.439-446
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• 2016

The characteristics of bearingless main rotor of helicopter are investigated through non-rotating tests and rotating tests. The stiffness and natural frequencies of rotor blades, flexbeam, and torque tube which are core components of baearingless rotor are measured to obtain input material properties for rotor analysis. The functional test on ground for assembly of one hub with damper, snubber, and no blade is carried out to check interfaces between components, kinematics of components, and pitch motion ranges under applied loads including centrifugal load. The 4-bladed bearingless rotor with 5.82m of rotor radius is tested on the whirl tower with rotation plane of 9.65m height. The thrust and power are measured to obtain hover performance and the frequencies and dampings of the rotor are obtained by excitation of cyclic pitch by hydraulic actuators.

• Journal of the Korean Institute of Intelligent Systems
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• v.18 no.2
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• pp.230-235
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• 2008

Recently, LG chemical corporation developed new material called HYPERIER, which has an excellent barrier characteristic. It has many layers which are made of nano-composite within LDPE(Low-Density Poly Ethylene). In order to guarantee the quality of the final product from the production line, a certain test equipment is required to investigate the existence of layers inside the HYPERIER. In this work, ultrasonic sensor based test equipment for investigating the existence of inner layers is proposed. However, it is a tedious job for human operators to check the existence by just looking at the resounding waveform from ultrasonic sensor. Therefore, to enhance the performance of the ultrasonic test equipment, Fast Fourier Transform(FFT) and Principle Components Analysis(PCA) and Back-Propagation Neural Network(BPNN) are utilized which is used for classification of Quality. To verily the feasibility of the proposed scheme, some experiments are executed.