Computer aided modelling and simulation of carbon fibre utilization for light aircraft wing application

Light aircrafts play a significant role in climatic and disaster management operations such as in aerial surveillance, mapping, monitoring, response etc. This study aims to contribute to enhanced performance and sustainability of light aircraft operations through effective design of its wing. Using commercial software code, computer aided modelling and simulation of carbon fibre material-based application was carried out, to determine suitability for the development of a light aircraft wing. The effect of different lengths of the wing (3500 mm, 5000 mm, 6500 mm, 7000 mm) on the performance of the aircraft was investigated with respect to the resulting stress and strain induced, plastic strains and displacement. The results obtained indicated that the maximum induced stress could reach 25.515 MPa, which is significantly lower than the yield strength of the material (3.20 GPa). Furthermore, wing length of 5000 mm showed less strain induced and thus more stability compared to others. Furthermore, the equivalent plastic strain and resultant displacement for the various lengths of the aircraft wings at the root chord (central axis) were found to be negligible. The outcome of this study can assist light aircraft developers to optimally harness the potentials of carbon fibre for aircraft wing development.