Dynamic analysis of cantilever beam used carbon fiber composite for aerospace applications

Abstract

The mixed carbon fibre composites and angle orientation of part is subjected to a dynamical study. Model analysis is used to identify the materials mode shapes and bending strength of composite structures. The higher outcomes of aircraft structural applications are supplied by natural frequency. The Ansys workbench module draws the cantilever beam with one end static and the other end free for analysing composite behaviours in the structural parts and linear structures. The research using finite elements showed eight different deformation shapes. The greatest values of natural frequency and comparable shapes are predicted by the mode shapes of 1 to 8. The strain rates is examined the basic frequency of 25.27 Hz determined in the cantilever beam structures. The dynamic vibration is formed 17.80 Hz of composite vibration is produced from these experiments.