Nonlinear static/dynamic instability and vibration characteristics of composite shells = 복합적층 쉘의 비선형 정적/동적 불안정성 및 진동 특성 연구

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The finite element method based on the total Lagrangian description of the motion and the Heillinger-Reissner principle with independent strain is applied to investigate the nonlinear static and dynamic response including vibration characteristics for laminated composite shells. The nonlinear static problems are solved using arc-length method to trace the load-equilibrium path of snapping behaviors for thin shells. The nonlinear dynamic response is obtained by employing the implicit time integration method. Even with a small number of elements, the present finite element gives not only reliable solutions, but also good convergence independently of configurations and boundary conditions. In this study, three cases of numerical studies are carried out: (1) the vibration characteristics of twisted cantilevered conical shell, (2) the thermal post-buckling response of reinforced patched shell and (3) the dynamic instability (or buckling) of spherical shell. For a twisted cantilevered conical shell, the twisting angle affects greatly the twisting mode rather than the first bending mode. For a patched laminated cylindrical shell under thermal load, the patch on the panel can alleviate the snapping phenomena and give an improved performance of load-carrying capability, when the patch has the same order of the panel thickness. In addition, the lamination and location of the patch affect significantly the nonlinear thermal response. The dynamic (or transient) analysis with damping included can represent the true dynamic nature of the response of a structure for all equilibrium point and follows the evolution of the response as a function of time as seen in a large deformation (or collapse) of the spherical shell. For thin shells subjected to suddenly dynamic load, the critical load is lower than the expected static one. That is, the snapping can occur at the load below the static critical load. Also, the damping can give two possible load-equilibrium solutions with pr...
Advisors
Lee, Inresearcher이인researcher
Description
한국과학기술원 : 항공우주공학전공,
Publisher
한국과학기술원
Issue Date
2001
Identifier
169574/325007 / 000965300
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 항공우주공학전공, 2001.8, [ xv, 136 p ]

Keywords

dynamic instability (or buckling); thermal post-buckling behavior; nonlinear analysis; mixed finite element formulation; vibration of twisted conical shell; 원추형 쉘의 진동; 동적 불안정성(또는 좌굴); 열적 후좌굴 거동; 비선형 해석; 혼합유한요소법

URI
http://hdl.handle.net/10203/26277
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=169574&flag=dissertation
Appears in Collection
AE-Theses_Ph.D.(박사논문)
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