Finite element analysis of Euler’s Bernoulli cantilever composite beam under uniformly distributed load at elevated temperature

Abstract

Recently, the requirement of composites becomes very high due to their unique mechanical properties and their application, whether it is in the field of aerospace or medical equipment, sensors, actuators, automobiles, and many more. In this research Chicken Feather Fibre (CFF) with Epoxy-Resin is considered as a beam structure, to check the structural integrity of the composite beam under the uniformly distributed load of 500 N and at an elevated temperature of 500 °C. The study depicts that, under UDL, the structure will be subjected to 51.53 MPa and produces a displacement of 0.1127 mm. To evaluate the vibrational frequency for the composite beam at an elevated temperature of 500°Celsius for both the cantilever beam type condition and both end fixed type condition, modal analysis has been considered for the first eight modes. Results indicates that, for cantilever beam type boundary condition frequencies varies from 205.91 Hz (mode1) to 2939.4 Hz (mode8), whereas for both end fixed type condition, frequency is very high as compared to the cantilever type condition, it varies from 1174.4 Hz (mode1) to 4890.3 Hz (mode8). This study helps us to ensure a safe working environment while working with these composite beams.