• Transactions of the Korean Society of Mechanical Engineers
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• v.18 no.11
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• pp.2986-2998
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• 1994

• Proceeding of EDISON Challenge
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• 2016.11a
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• pp.78-80
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• 2016

우주발사체와 항공 분야에서 초음속과 극초음속 영역에서 비행체의 항력을 최소화하기 위한 최적 형상설계 연구가 활발히 진행되고 있다. 본 논문에서는 마하수 2의 초음속 영역에서 대표적인 비행체 선두부 형상 3가지에 대한 수치해석을 eMEGA 프로그램을 활용해 격자를 생성하고 eDAVA 프로그램을 활용해 유동 해석을 수행하였다. 그 결과 자유유동 마하수 2의 초음속 영역에서는 선두부 형상이 뾰족한 Cone 형상이 3가지 형상 중 작용하는 항력이 가장 적게 나타났고, 선두부가 무딘 형상이 극초음속 영역에서 가장 적합한 현상과 다르게 나타났다.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.12 no.2
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• pp.278-284
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• 2001

In this paper, the slanted metallic boundaries is analyzed for the triangular cell grid method and compared with staircase approximation. Specially, this paper is derived an error range to the angle of inclination between the metal and the dielectric from the triangular cell grid method. That result, when the angle of inclination is from 30˚ to 60˚, the triangular cell grid method improves the accuracy, the computer memory and time requirement in comparison with the staircase approximation. But, out of this range, we do not expect the accuracy because a side of cell size lengthen.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2000.06a
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• pp.1261-1267
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• 2000

외부에서 자극이 가해질 때 상전이(phase transformations)하는 방식으로 대응하는 재료들이 최근 다양하게 연구되고 있다. 예를 들어 형상기억합금은 주변 온도의 변화에 대응하여 그 형상을 변화시키는데 이 과정은 미시적으로는 격자의 형태가 - 예를 들면 정방형 격자에서 입방형격자로 혹은 그 반대로 - 변화하는 과정이다. 강유전체 역시 외부에서 인가되는 전계의 변화에 대응하여 그 격자구조가 변하는데 그와 함께 기계적 변형이 동반하게 된다. 본 논문에서는 상전이를 하는 재료에 적용될 수 있는 1차원 구성방정식을 강유전체의 예를 들어 제시하고 간단한 계산결과를 보이기로 한다. 본 모델을 확장하여 강유전체에서의 분극역전(polarization reversals)에 대한 3차원 유한요소 모델을 개발하고 응용하려는 시도가 이루어지고 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.12
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• pp.1097-1106
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• 2011

Unsteady numerical analysis was performed to simulate air-launched missiles from a complete helicopter in hover by using an unstructured overset mesh flow solver coupled with a module of six degree-of-freedom motion of equations. The unsteady computations have been performed to obtain flow fields around the complete helicopter including main rotor, tail rotor, and fuselage equipped with multiple missiles, and six-DOF simulation has been performed to predict the behavior of the air-launched missile. The effects of the launching position and the missile thrust on the trajectory of the missile were investigated as well as the aerodynamic interference of the air-launched missile under the unsteady downwash produced by main rotor.

• Journal of KSNVE
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• v.6 no.6
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• pp.827-834
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• 1996

The effect of pipe breaks in the secondary side is investigated as a part of the fuel assembly qualification program. Using the detailed dynamic analysis of a reactor core, peak responses for the motions induced from pipe breaks are obtained for a detailed core model. The secondary side pipe breaks such as main steam line and economizer feedwater line braksare considered because leak-before-break methodology has provided a technical basis for the elimination of double ended guillotine breaks of all high energy piping systems with a diameter of 10 inches or over in the primary side from the design basis. The dynamic responses such as fuel assembly shear force, bending moment, axial force and displacement, and spacer grid impact loads are carefully investigated. Also, the stress analysis is performed and the effect of the secondary side pipe breaks on the fuel assembly structural integrity under the faulted condition is addressed.

• Journal of the Korean Applied Science and Technology
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• v.14 no.2
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• pp.87-91
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• 1997

서로 다른 씨클로펜타디엔 유도체가 ${\pi}$-결합된 최초의 비스무스 화합물인 ${\eta}^5-C_5(CH_3)_5Bi({\eta}^5-C_5H_5)_2$이 디펜타메틸씨클로펜타디에닐 비스무스디메틸아미드 $Cp{\ast}_2BiNMe_2[Cp{\ast}=C_5(CH_3)_5]$와 씨클로펜타디에닐 모노머와의 반응으로 합성되었다. 반응조건은 에테르 용매하에 -78$^{\circ}C$ 반응온도 조건하에서 얻어졌다. 합성된 반응물을 노르말 헥산 용매에서 재결정시킨 결과, 검은색 결정이 60% 수율로 얻어졌다. 그리고 재결정시킨 반응물을 190K에서 X-선 단결정 구조 분석 방법에 의해 그 구조를 밝혔다. 그 결과 결정계의 격자계는 I2/a, a=1756.00 picometer, b=906.00 picometer, c=2211.00 picometer, ${\beta}$=104.04, Z=8로 확인되었다. 여기서 a, b, c는 결정�Ю� 상수이고, ${\beta}$는 결정격자 상수인 b와 c간의 각도이며, Z는 단위 결정 격자당 분자의 갯수이다.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.11 no.8
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• pp.1363-1375
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• 2000

The electromagnetic scattering characteristics by a periodic strip grating on a grounded dielectric slab for TM polarization case are examined from the viewpoints of both the reflection grating and the leaky wave antenna problems. Numerical results far two kinds of Bragg blazing (resonance type and non-resonance type) phenomena are given and some discussions on the properties(complex propagation constants, scattering characteristics, and distributions of strip current density) are presented. The comparison of the Bragg blazing phenomena between TM and TE polarization cases are also given in detail.

• Journal of the Korea Concrete Institute
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• v.15 no.3
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• pp.377-385
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• 2003

Flexural characteristics of the R.C beams strengthened with newly-developed grid-type carbon fiber plastics(CFRP-GRIDS) were investigated. The tests were conducted under the four-points load to the failure to investigate the strengthening effects of CFRP-GRIDS on the beams. Results showed that initial cracks appeared in the boundary layers of fibers embedded in the newly-placed mortar concrete slowly progressed to the direction of supports and showed fracture of fiber plastics and brittle failure of concrete in compression in sequence after the yielding of steel reinforcement. Accordingly, the appropriate area of Grid-type carbon-fiber plastics in the strengthening design of deteriorated RC structures should be limited and given based on the ultimate strength design method to avoid the brittle failure of concrete structures.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.2
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• pp.17-25
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• 2006

In the present study, a 2-D chimera technique for overlapped bodies in relative motion is developed using unstructured triangular meshes. The solid boundary nodes located next to the intersecting point between bodies are merged to the intersecting point to assure accurate representation of the intersecting region. In order to assign proper value of flow variables at the nodes located out of the computational field, interpolation is conducted for non-active nodes. For validation, the motions of a NACA64A006 airfoil and a NACA0012 airfoil with a plane flap are computed and the results are compared with other simulations. The motion of a launching missile ejected from a NACA0012 airfoil is also simulated.