Fiber-reinforced composites are being widely used in the aircraft and aerospace industry, as well as in other field such as automobile, electronics, etc. In this work, a method based on the superposition and state-space techniques is developed to study the free vibration of cross-ply laminated composite shell panels with general boundary conditions. An example problem of a shell panel with two adjacent edges clamped and the others simply supported is investigated. Convergence tests have been carried out to demonstrate the veracity of the approach. Accurate fundamental frequencies of the shell are presented for various shell parameters.

Issue Section:
Research Papers
Topics:
Dynamic response, Shells, Aerospace industry, Aircraft, Automobiles, Boundary-value problems, Composite materials, Electronics, Fiber reinforced composites, Free vibrations
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