Abstract
Nowadays, polymer composites have wide applications from the soft electronic devices like actuator, sensors, medical equipment to the parts of helicopters, automobile, space vehicles etc. In this study, we are considering Chicken Feather Fibre (CFF) with Epoxy-Resin (CY-230) matrix as a beam structure. From literature, the sample is prepared from hand layup techniques and consist of 5% CFF by weight in Epoxy Resin (CY-230) matrix, which is considered to be the best sample. The computational structural analysis is carried out to understand the deformation and stress distribution over the beam structure while subjected to tensile and compressive load of 25 kN with one end fixed condition. And then, modal analysis is carried out to determine the natural frequency of vibration of beam under both end fixed boundary condition. The maximum stress and deformation are generated when the beam is subjected to tensile load, which is 493 MPa and 18.569 mm respectively. It is found that natural frequency of beam structure varies from 1769.7 Hz to 7216.5 Hz. These results will be helpful to determine the safe working condition while working with this material.
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