• Proceedings of the Korean Powder Metallurgy Institute Conference
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• 2000.04a
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• pp.36-36
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• 2000

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.8
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• pp.692-698
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• 2015

This paper represents a trajectory design and analysis technique which uses invariant manifolds of the circular restricted three body problem. Instead of the classical patched conic method based on 2-body problem, the equation of motion and dynamical behavior of spacecraft in the circular restricted 3-body problem are introduced, and the characteristics of Lyapunov orbits near libration points and their invariant manifolds are covered in this paper. The trajectories from/to Lyapunov orbits are numerically generated with invariant manifolds in the Earth-moon system. The trajectories in the Sun-Jupiter system are also analyzed with various initial conditions in the boundary surface. These methods can be effectively applied to interplanetary trajectory designs.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.5
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• pp.98-103
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• 2015

A flow passage opening device utilizing an acceleration follow-up technique allows fuel to flow continuously through a pressurized fuel tank system. It is very difficult to test the device in a real flight situation because of severe test condition and a cost problem. In this paper, therefore, the results of a basic negative g test conducted by low-speed airplane are compared with RecurDyn simulation. Dynamic behavior of the device in total flight profile of a high-speed vehicle is also analyzed by using RecurDyn to predict its performance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.1
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• pp.49-57
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• 2003

The flight trajectory of a boomerang is predicted with the momentum theory (actuating disk theory) and the blade element method generally used as tools to analyze in the rotary-wing aerodynamics. Boomerangs made by students are actually compared with the computational results, utilized to get the physical intuition. The transition from helicopter mode to autogyro mode with the gyroscopic precession is observed in numerical analysis and experiment like a 'flying rotor' after the boomerang taking off. The whole system is shown to be highly nonlinear and very sensitive to the initial conditions. Various flight loci may be obtained if we change the parameters.

• Korean Journal of Crystallography
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• v.17 no.2
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• pp.60-65
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• 2006

표면 및 계면층의 결정구조, 결함구조, 불순물 편석, 표면의 전자 구조, 원자 진동 등과 같은 산화물의 표면물성은 촉매, 센서, 소결, 마찰, 부식 등과 같은 분야에서 그 특성을 좌우한다. 고체 표면의 결정구조 해석 수단으로 저에너지 이온산란 분광법이 유용한 도구로 알려져 있는데, 이 방법의 뛰어난 표면민감성은 표면에서의 효과적인 이온 중성화 과정에 기인한다. $He^+$, $Ne^+$, $Ar^+$ 등과 같은 이온은 Auger 중성화 과정에 의하여 쉽게 중성원자화 되고, 중성화 확율의 타겟에 대한 의존성이 낮기 때문에 이온빔으로서 종종 사용된다. 산란각도를 180$^{\circ}$로 고정하여 산란이온 검출기를 설치한 직충돌 이온산란 분광법의 경우는 산란된 이온의 궤적이 입사궤도와 거의 동일하기 때문에 산란궤적의 계산이 간단해지고, 수 층 깊이의 원자구조의 해석이 가능해진다. 본 고에서는 고체 표면의 원자구조를 실공간에서 해석할 수 있는 직충돌 이온산란 분광법에 대하여 측정의 기본원리, 측정장치, 간단한 분석 예 등에 관하여 기술하고자 하며, 다음 편에서는 복잡한 표면구조를 가지는 반도체 표면에서 직충돌 이온산란분광법의 이용하여 해석한 예를 중심으로 기술하고자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.97-100
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• 2008

A hybrid sounding rocket carrying about 10kg payload reaching up to 15km altitude has been designed. The commercial seamless aluminium tube and liquid ${N_2}O$ without pressurization devices were chosen as rocket motor case and oxidizer supply system respectively. A hybrid rocket engine performing required propulsion impulse is designed with time dependent internal ballistic scheme. Engine performance, aerodynamic characteristics, and trajectory were predicted by a integral technique of internal ballistics and external ballistics. The design results were evaluated by comparison with previous experimental data, technical reports, and literatures.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.7
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• pp.544-551
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• 2014

A program of launch vehicle performance analysis is composed for the education of the conceptual design of launch vehicles and the requirement analysis for the propulsion system design. The program is applied for the mission analysis of space launch vehicles based on KSLV-II with liquid rocket boosters. The 75-ton class liquid rocket engine is assumed for the boosters by referring the mass ratio of KSLV-II second stage. The launch performance analysis is carried out for KSLV-II with 2, 3 and 4 boosters by targeting the circular orbit of 700 km altitude. The trajectory is assumed as two-dimension considering the variation of the flight environment. Payload of advanced KSLV-II could be increased to maximum 3 tons, though it is limited by the thrust performance of the upper stage.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.4 no.5
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• pp.931-936
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• 2000

A novel CPFDTD algorithm for modeling the smooth curved surfaces is presented. This scheme subdivides electric fields on the distorted grid into the extended contour field, the non-distorted field, and the quasi-available field to avoid the collinear borrowing approximation. Several preceding methods are applied to the I-plane sectoral horn antenna to get far-field patterns. The accuracy of the presented method is demonstrated by comparison with measured values.

• Proceedings of the KIEE Conference
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• 2007.07a
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• pp.317-318
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• 2007

휴머노이드 로봇이 인간에게 필요한 다양한 서비스를 제공하기 위해서는 정해진 동작이 아닌 상황에 따른 다양한 동작이 요구된다. 특히 보행에 있어서는 회전각도 보폭 등이 상황에 따라 변경이 가능해야 한다. 이에 따라 로봇에게 필요한 다양한 보행 궤적을 생성하기 위해서는 보행궤적의 생성과 안정성 판별을 위한 ZMP(Zero Moment Point), COG(Center Of Gravity)등의 생성을 위한 시뮬레이터가 필요하게 된다. 본 논문에서는 성행 연구를 통해 개발된 시뮬레이터 프로그램의 단점을 분석하고 보완하여, 보폭 및 회전 각도가 자유로운 회전 보행의 생성이 가능한 시뮬레이터 프로그램을 구현하였다. 그리고 구현된 시뮬레이터 프로그램을 사용하여 생성된 궤적 파일을 동역학 해석 프로그램인 NASTRAN을 이용 시뮬레이터를 검증한다.

• Korean Chemical Engineering Research
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• v.44 no.3
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• pp.294-299
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• 2006

Computational simulation was performed to analyze flow velocities and particle trajectories onto the surface of bag-shaped filters with a different permeability. When the permeability of a filter is lower than that of a low-efficient fabric bag-filter widely used, the distributions of flow velocities and particle trajectories on the filter surface were not different with decreasing the filter permeability. The distributions of streamlines and radial directional gas velocities were uniform on the filter surface except for the neighbors of the bottom edge and outlet of the filter. The particle trajectories onto filter surface were more densely distributed around the bottom edge of the filter, so that the particle number on the filter surface was maximized near the bottom edge and decreased in the direction of the filter outlet.