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[論文] 有限要素法을 利用한 코오드-고무 複合板의 動的特性에 關한 硏究
김두만(Doo Man Kim),김항욱(Hang Wook Kim) 한국자동차공학회 1986 오토저널 Vol.8 No.2
There has been considerable interest over the last twenty years in the subject of the elastic properties of the cord-rubber laminates. This has been due to the rather intensive study of the composites materials characteristics brought about by the increased use of rigid composites in many structural applications.<br/> The object of this study is to obtain the natural frequencies and modes of the simply supported cord-rubber laminate plates prior to the study on the analysis of the dynamic properties of the pneumatic tire.<br/> To obtain these natural frequencies and modes, the 12 degrees of freedom orthotropic rectangular plate finite elements are developed. By using the c1assicallamination theory, the<br/> stress-strain relations are represented.<br/> The governing equation for the finite element is derived by energy method.<br/> To find the natural frequencies and modes, the eigenvalues and corresponding eigenvectors are computed by the well known Jacobi power method.<br/> In order to verify the capability of this present finite element, the results of the specially orthotropic plate and the angle-ply laminate plate are compared with the analytical solution. The analytical and numberical results are in good agreement.<br/> The following problems of the simply supported plate are analyzed by the present finite element.<br/> a) The natural frequencies and mode shapes of the cord-rubber laminate plate for various aspect ratio.<br/> b) The natural frequencies and mode shapes of the orthotropic plate with the rectangular hole in its center.
金恒旭 한국항공대학교 1975 論文集 Vol.8 No.-
航空機體의 主部分인 胴體를 圓筒形과 圓錐臺形構造의 結合體로 模型化 했음을 前題로 하고 圓錐臺形 SHELL 構造의 振動問題를 FINITE ELEMENT 方法으로 다루었으며 計算된 結果를 旣存結果와 比較圖示하였음.
문관호,김항욱 한국항공대학교 1986 論文集 Vol.24 No.-
A Finite Element Model based on the super-parametric shell element is studied for the dynamic analysis of rotating structure of arbitrary shape and thickness. The linearized equations of motion derived for the rotating structure, including the effect of the centrifugal mass, centrifugal force vector and the pseudo static equilibribrium position, have good accuracy and save the cumputational time, instead of complexity of the non-linear one previously studied. The power of the method is illustrated by applying it to a pretwisted rectangular plate and tapered cylinderical type blade.
航空機胴體에서 窓門切開로 因한 應力集中現象과 그 解消策의 有限要素法에 依한 硏究
金恒旭,이성철 한국항공대학교 1982 論文集 Vol.20 No.-
The stress concentration phenomena of aircraft fuselage, due to the window cut-out, is investigated by finite element method. In order to satisfy the boundary conditions and inter-element compatibility conditions up to the stress level, a new finite element is developed by compensating the handicap that the conventional membrane finite element revelas in applying it for this research problem. Equivalent nodal load assumption is done by the well known method that equated the virtual work due to the nodal load and the other due to the actual distributed load. The boundary conditions are not only those vanishing ones, but also some conditions given by the linear relations of the type:??, and the applying technique for this kind of boundary condition is worked out. fuselage is idealized to a cylindrical shell and loading is considered to be the only torsion which is the semi-monccoue aircraft skin has to take care of. The stress concentration factor is numerically calculated and the result is plotted to show the influence of the cut-out.