FREE VIBRATION ANALYSIS OF LAMINATED COMPOSITE OPEN CYLINDRICAL SHELLS WITH ARBITRARY BOUNDARY CONDITIONS

摘要

Laminated composite open cylindrical shells are often encountered in aircrafts, missiles, rockets and other engineering practices. These applications have attracted a great many of researchers to develop mathematical models to predict their vibration behaviours with sufficient accuracy. The history of the vibration analysis of laminated composite open cylindrical shells can be traced back to about half a century ago and the vibration characteristics of these shells with classical boundary conditions, such as free edges (F), simply-supported supports (S) and clamped restraints(C) can be predicted precisely. Research papers and articles oriented to such contributions may be found in Quta [1], Quta and Leissa [2], Zhao et al. [3, 4], Selmane and Lakis [5], Bardell et al. [6], Zhang et al. [7], Messina and Soldatos [8-10], Lim et al. [11], Bercin [12] and so on. However the shell with more complicated boundary conditions such as elastic restraints, mix boundaries, partial supports and their combinations is still a challenge. Moreover, the existing solution procedures are often only customized for a specific set of different boundary conditions. The vibration of laminated composite open cylindrical shells with general boundary conditions is rarely studied in literature. Therefore, a general method which can be used to determine the vibration behaviours of these shells accurately and efficiently is necessary and of great significance. In this paper, a Chebyshev-Ritz method is presented for the free vibration analysis of laminated composite open cylindrical shells with general elastic boundary conditions. The displacements of the shell are generally expanded, regardless of boundary boundaries, as Chebyshev polynomial series. Several examples are given to demonstrate the accuracy and effectiveness of the current solution. The proposed solution can be readily extended to shells with nonuniform boundary supports.