Data.xlsx

As it is known that civilian air vehicle is used for transportation of passengers to various places due to its complex geometry. These air vehicles fly to and fro continuously. While at the take-off, as the vehicle is lifted to maximum level it induces a high bending moment on the propeller, winglet, wings, and slats. The respective parts are fixed to the air vehicle fuselage through wing-fuselage attachment brackets. Complete internal moment vector and shear stress from the propeller, winglet, wings, and slats are distributed to the air vehicle fuselage at the joint where attachment exists. This paper deals with the analysis of bending load transfer at the joints and fatigue life of the wing attached to the fuselage bracket of the air vehicle. Stress values have been analyzed to find the geometry of the air vehicle wing attached to the fuselage bracket.