A finite element analysis for the free vibration behaviour of doubly curved shells is presented in which eight-noded curved quadrilateral isoparametric finite elements are used. The first order shear deformation theory for thin and shallow shells is used in the formulation. Results are obtained for
FINITE ELEMENT TRANSIENT DYNAMIC ANALYSIS OF LAMINATED STIFFENED SHELLS
โ Scribed by B.GANGADHARA PRUSTY; S.K. SATSANGI
- Publisher
- Elsevier Science
- Year
- 2001
- Tongue
- English
- Weight
- 400 KB
- Volume
- 248
- Category
- Article
- ISSN
- 0022-460X
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โฆ Synopsis
The present work describes the transient dynamic response of unsti!ened/sti!ened composite plates/shells using "nite element method. Composite panels "nd wide applications in aerospace, marine and other engineering because of its high strength to weight ratios. These structures are often subjected to air-blast loading, underwater shock etc., which requires a thorough dynamic response analysis under such loading. A modi"ed approach of shell and sti!ener modelling is adopted here using an eight-noded isoparametric quadratic element for the shell and a three-noded curved sti!ener element for the sti!eners on the concept of equal displacements at the shell}sti!ener interface. The present formulation obviates the need for imposing the mesh line along the sti!eners; rather it accommodates the sti!eners elegantly anywhere placed arbitrarily inside the element with computational e$ciency. Newmarks method for direct time integration has been adopted for the solution of the governing equation for undamped motion. The transient dynamic response of sti!ened and unsti!ened structures subjected to various kinds of time variant loading has been studied and the results are compared with the published ones.
2001 Academic Press C , (2) *z * ! *z * *y * # *z * *x * ! *x * *z * # *x * *y * ! *y * *x * and C " *y * *z * ! *z * *y * # *z * *x * ! *x * *z * # *x * *y * ! *y * *x * . (3) *z * ! *z * *y * # *z * *x * ! *x * *z * # *x * *y * ! *y * *x * . (17)
๐ SIMILAR VOLUMES
A finite element analysis for the free vibration behaviour of point supported laminated composite cylindrical shells is presented. Eight-noded curved quadrilateral isoparametric elements are used. The formulation is based on the assumptions of the first order shear deformation theory for thin, shall
The results of the finite element analysis of 3-ply laminated conical shells with light core for linear panel flutter are presented and certain advantages of such shells discussed.