Abstrakt

Stress Analysis of the Vertical Tail Root Fitting Bracket and Calculation of Fatigue Damage Due To Fluctuating Side Loads

Chinmayee M J , Dr. Thammaiah Gowda

Vertical tail (VT) is one of the important components in the airframe structure connected to the fuselage structure. VT experiences side loads due to rudder deflection. VT is attached to the fuselage through attachment brackets. The joint locations between the major components of the aircraft are considered to be critical locations. The current project includes the stress analysis of the vertical tail root fitting bracket and modifying the design if necessary. Bracket connects the fuselage and VT. Loads received by the VT will get transferred to fuselage at the root. It is almost like a cantilever action, which induces maximum bending moment at the root. Attachment bracket with surrounding structural elements will be considered in the stress analysis. Finite element method is adopted in the stress analysis of the structure. Stress analysis will be carried out at the high tensile stress location to capture the stress concentration and gradient stress field near the fasteners. Since the VT experiences fluctuating side loads, fatigue crack will initiate at the maximum tensile stress location. Fatigue damage calculation will be carried out using linear damage theory. S-N curve for aluminum alloy material obtained from the literature will be used.