DYNAMIC BUCKLING OF LAMINATED COMPOSITE CYLINDRICAL SHELLS SUBJECTED TO RADIAL IMPACT

Ananalysis was given to the dynamic pulse buckling of a finite-length laminated composite cylindrical shell subjected to uniform radial impact. The buckling equations including transverse shear deformation and rotatory inertia were derived from Lagrange equation. According to numerical results generated by the fourth-order Runge-Kutt a method, the number of the most amplified mode and critical velocity were obtained. Finally, the effects of transverse shear, geometric parameter and lamination angle on the behavior of dynamic buckling of laminated cylindrical shells were discussed.