Abstract
In this paper, whole work is done for hybrid laminated composite beam which is made of three composite materials boron-epoxy, aramid-epoxy, and s-glass-epoxy. A numerical study, using finite element method is carried out to analyse the free transverse vibration behaviour of composite beam. ANSYS APDL is used as a finite element solver to simulate the free transverse vibrations. A variety of parametric studies is performed to check the effects of various parameters associated with crack geometry and laminate property on the three least natural frequencies. Parameters for the investigation are included as fibre volume fraction, ply angle for (0°/Φ°/0°/Φ°/0°/90°/(90-Φ)°/0°/(90-Φ)°/0°) stacking sequence, location of crack geometry relative to the restricted end, depth of crack (a) and support conditions (C-C & C-F configuration) for hybrid laminated composite beam, trend of the least three transverse natural frequencies is also discussed in detail. It is noted that maximum value of natural frequency occur at Φ equals to 90° for both (CC) and (C-F) and for relative crack depth 0.5 to 0.6, there is sharp decrement in natural frequency for (C-F). Other factors of laminate and crack geometry are also discussed in present analysis, which shows a great scope of this hybrid composite with (0°/Φ°/0°/Φ°/0°/90°/(90-Φ)°/0°/(90-Φ)°/0°) stacking sequence in the field of aviation and prosthetics.
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