Computational Analysis of Hybrid Composite Material for Wing Frontal Spar
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Abstract
The fast growth of composite materials in the aerospace industry is due to its desired properties over conventional metals. In this paper, a detailed static structural analysis and vibrational analysis was carried out for the aircraft wing frontal spar using hybrid material and it was compared with different conventional materials used in aerospace industry like aluminium, CFRP (Carbon Fiber Reinforced Polymer). The carbon fiber and flax fiber were selected for composition in hybrid composite material since it shows an exceptional specific mechanical properties and good vibration damping properties. The frontal wing spar was designed using modelling software CATIA V5. Static structural analysis and modal analysis was performed using ANSYS software. Exploring the results of structural analysis, it was interpreted that the static structural efficiency of the hybrid composite material was exceptionally high compared to aluminium and it shows nearly equal specific mechanical properties compared to CFRP. This leads to reduction in cost of the structure. From the modal analysis the various natural frequencies for six modes are discussed. The analysis shows natural frequency of wing frontal spar using hybrid composite material exhibits similar deformation compared to CFRP. Hybrid composite material exhibits higher damping factor when compared to chosen materials. This behaviour of hybrid composite material shows that it could be effectively replaced in wing frontal spar instead of conventional materials like CFRP and aluminium.
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