• 한국공간구조학회:학술대회논문집
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• 한국공간구조학회 2006년도 춘계 학술발표회 논문집 제3권1호(통권3호)
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• pp.256-264
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• 2006

This paper describes the formulation of rectangular flat shell element that is modeled with the six degree of freedoms including a rotational degree of freedom. The rectangular finite element matrix with a rotational degree of freedom is developed using a beam stiffness matrix and compared with other methods. The outputs of the quantity of vertical deflection of cantilever beam show us the improving evidence of the Frame-Shell finite element matrix in a calculation of vertical deflections of cantilever beam.

• 한국공간구조학회논문집
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• 제4권4호
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• pp.85-89
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• 2004

A frame element embedded normal to a shear wall or slab (shell element) is common in the structural systems. In that case there is a need for a membrane or shell element to have a normal rotation degree of freedom at each node in order to have a good result of stresses. Even if Many other people studied this area, All man, Cook and Sabir are representative investigators in this area. In this research paper, Sabir's methods of vertex rotation stiffness matrix in a membrane element are studied. New stiffness of vertex rotation are proposed by taking advantage of beam stiffness theory. Rectangular elements stiffness with rotational degree of freedom are compared in accuracy ratio each other.

• 한국공간구조학회논문집
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• 제8권4호
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• pp.81-90
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• 2008

이 논문에서는 적분형 르장드르 다항식을 사용한 3차원 계층적 고체요소의 유한요소 정식화를 보여준다. 제안하는 육면체 고체요소는 절점, 변, 면, 그리고 내부모우드를 포함한은 4개의 서로 다른 모우드로 구성되어 있다. 영에너지 모우드와 일정변형률 조건을 확인하기 위해 고유치 시험과 조각시험이 수행되었다. 여기에 추가되어, 적응적 p-유한요소해석을 위해 유한요소해석으로부터 구한 후처리 응력값의 평활화에 기초를 둔 사후오차평가 기법이 연구된다. 자유도가 증가함에 따라 수렴속도측면에서 균등 p-분배와 불균등 p-분배에 의한 유한요소해의 차이점이 비교된다. 제안된 요소의 성능을 보이기 위해 간단한 캔틸레버보가 테스트되었다.

• 한국정보통신학회:학술대회논문집
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• 한국해양정보통신학회 2007년도 추계종합학술대회
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• pp.325-327
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• 2007

3차원 형상의 물체에 대한 표면 면적을 6축 센서를 사용하여 측정하였다. 3차원 형상의 표면적은 여러 개의 작은 삼각형으로 나타낼 수 있다. 이 여러 개의 삼각형의 합을 구함으로써 표면 면적을 구할 수 있고, 삼각형의 크기가 작으면 작을수록 실제 면적의 크기에 접근 하였다. 실험 결과 평균 7.78%의 오차율을 보였다.

• 한국항공우주학회지
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• 제30권8호
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• pp.37-45
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• 2002

본 연구에서는 이차원에서 비정상 비점성 유동해석을 위한 비정렬 동적 편자 기법을 개발하였다. 유동해석 기법은 시간에 대해 2차의 정확도를 갖는 내재적인 시간적분법을 사용하였으며, 격자중심의 유한 체적법과 Roe의 풍상차분법을 이용하여 공간에 대한 차분화를 하였다. 시간과 공간에 대한 정확도를 증가시키기 위해서는 해에 따라 원하는 위치에 격자점들을 임의로 추가할 수 있는 비정상 동적 적응격자 기법을 사용하였다. 이를 이용하여 이차원의 2자유도를 갖는 스프링 에어포일 시스템의 와류와의 간섭현상에 따른 공탄성적 변위를 예측하였다.

• Steel and Composite Structures
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• 제26권6호
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• pp.771-791
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• 2018

This paper deals with the low velocity impact response and dynamic stresses of composite sandwich truncated conical shells (STCS) with compressible or incompressible core. Impacts are assumed to occur normally over the top face-sheet and the interaction between the impactor and the structure is simulated using a new equivalent three-degree-of-freedom (TDOF) spring-mass-damper (SMD) model. The displacement fields of core and face sheets are considered by higher order and first order shear deformation theory (FSDT), respectively. Considering continuity boundary conditions between the layers, the motion equations are derived based on Hamilton's principal incorporating the curvature, in-plane stress of the core and the structural damping effects based on Kelvin-Voigt model. In order to obtain the contact force, the displacement histories and the dynamic stresses, the differential quadrature method (DQM) is used. The effects of different parameters such as number of the layers of the face sheets, boundary conditions, semi vertex angle of the cone, impact velocity of impactor, trapezoidal shape and in-plane stresses of the core are examined on the low velocity impact response of STCS. Comparison of the present results with those reported by other researchers, confirms the accuracy of the present method. Numerical results show that increasing the impact velocity of the impactor yields to increases in the maximum contact force and deflection, while the contact duration is decreased. In addition, the normal stresses induced in top layer are higher than bottom layer since the top layer is subjected to impact load. Furthermore, with considering structural damping, the contact force and dynamic deflection decrees.

• 한국전산유체공학회지
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• 제19권2호
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• pp.86-92
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• 2014

In this paper, prediction of separation trajectory for Two-stage-To-Orbit space launch vehicle has been numerically simulated by using an aerodynamic database based on steady state analysis. Aerodynamic database were obtained for matrix of longitudinal and vertical positions. The steady flow simulations around the launch vehicle have been made by using a 3-D RANS flow solver based on unstructured meshes. For this purpose, a vertex-centered finite-volume method was adopted to discretize inviscid and viscous fluxes. Roe's finite difference splitting was utilized to discretize the inviscid fluxes, and the viscous fluxes were computed based on central differencing. To validate this flow solver, calculations were made for the wind-tunnel experiment model of the LGBB TSTO vehicle configuration on steady state conditions. Aerodynamic database was constructed by using flow simulations based on test matrix from the wind-tunnel experiment. ANN(Artificial Neural Network) was applied to construct interpolation function among aerodynamic variables. Separation trajectory for TSTO launch vehicle was predicted from 6-DOF equation of motion based on the interpolated function. The result of present separation trajectory calculation was compared with the trajectory using experimental database. The predicted results for the separation trajectory shows fair agreement with reference[4] solution.