Failure and Thermal Examination of Hybrid Materials for a Propeller shaft in Aerospace Applications
Shivanand1, Shravankumar B. Kerur2 

1Shivanand, Mechanical Engineering Department, Basaveshwara Engineering College, Bagalkot, Karnataka, India.
2Dr. Shravankumar B. Kerur, Mechanical Engineering Department, Basaveshwara, Engineering, College, Bagalkot, Karnataka, India

Manuscript received on 05 March 2019 | Revised Manuscript received on 09 March 2019 | Manuscript published on 30 July 2019 | PP: 6422-6428 | Volume-8 Issue-2, July 2019 | Retrieval Number: B2518078219/2019©BEIESP | DOI: 10.35940/ijrte.B2518.078219
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Abstract: Hybrid materials are an attractive option in case of aerospace and aviation applications since they are exceptionally strong. The current study presents the failure analysis of the hybrid material in ANSYS software. The main aim of this study is to check the suitability of the MATLAB results obtained from the previously selected composite material comprising of carbon steel + epoxy + S glass + T700 fibres using ANSYS software by creating a solid three-dimensional meshed model of the shaft. Layerwise shaft theory and finite element analysis have been employed for developing the model. The thermal analysis, delamination and buckling failure studies are conducted and found that increasing the thickness of the material will increase its load withstandability. The load failure point is found to be 8.4mm from the delamination studies. From analysis it was understood that the chosen composite material could be used for the propeller shaft of an aircraft.
Keywords: Composite Material, ANSYS, Delamination, Buckling, Layer-Wise Shaft Theory

Scope of the Article: Thermal Engineering