Exploration of hybrid materials for a propeller shaft in aerospace applications

Abstract

This paper is a comprehensive analysis of the different composite materials that can withstand the maximum load to be used in shaft instead of the conventional steel which is currently in use. The research focuses on developing a laminated composite propeller shaft for a two-seater aircraft that can withstand maximum load with least deflection. The mathematical model for the shaft of the two-seater aircraft is developed using classical laminate theory. The in-plane forces concerning the applied torque, the strain and stress relations are evaluated for the laminated shaft which is exposed to the in-plane forces. The code is developed in Matlab for the analysis. The results obtained from the Matlab are analysed and the analysis determines that the hybrid material consisting of low carbon steel, epoxy, S glass and T700 fibres is the best suitable for the propeller shaft to withstand maximum load with the least deflection. The orientation angle is considered to be 45 degrees.