The main objective of the research work is to eliminate divergence of swept wing by using proper fibre angle orientation of composite material with better mechanical properties. It is mainly done by aeroelastic tailoring using composite material. Basically, the wing behaviour of an aircraft is characterized by the interaction between the material and shape of the wing. The forward swept wings prove to have high aerodynamic efficiency, if the divergence problem is eliminated. These forward swept wing aircraft is one of the most superior aircraft in terms of both aerodynamics and structural configurations. This design has been consistently frustrated by the divergence problem. Generally, in the forward swept wing, when the aircraft turns, it applies high G-loads on the wing, this load causes the wing tip to bend upward which in turn leads the twist of the leading edges in the upwards direction. This bending is known as divergence, which increases the angle of attack leading to failure of wing. More over the divergence in the wing can be reduced by increasing the wing bending stiffness which in turn associates with the increase in the weight of the wing that leads to increase in overall weight of the aircraft. This weight penalty is known to be very severe for conventional metal wings, but with the unique lightweight property of advanced composites the designer will be able to overcome the difficulty in designing. Fibre angle orientation means the individual arrangement of the fibre in the development of material. As it greatly influences the property of the material, we chose this as a prominent key to avoid divergence. The materials involved in this research works are Glass fibre, Glass epoxy and Kevlar epoxy. The simulation and mathematical calculations of these materials are conducted by using MSC NASTRAN and MATLAB. Finally, comparison of mathematical and simulation works provides a better results for elimination of the divergence problem.
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