Strength analysis of the horizontal stabilator torque box of time-worn aircraft in order to estimate the remaining life and its lifetime by the finite element method

Since the distribution of actual tensions in aircraft components is one of the most important inputs for carrying out aircraft design and survey research, the present study analyzes the strength of the horizontal stabilizer torque box structure of the aircraft. For this purpose, the exact geometric model of torque box construction components has been manufactured using the CATIA® software and has been transferred to the ABAQUS® software for static analysis. After modification of the geometric model and the aerodynamic load extraction, using the plane loading curves, a finite element model is constructed. Then appropriate boundary conditions and properties of the material of the components are allocated and finally, the stresses of the structural components and horizontal stabilizer are obtained. The structure of the torque box, with a large part of the forces involved on the tail of the aircraft, which has all a control level and is in different angles of change, can withstand a critical structure. After presenting the results of the static analysis, critical components of the torque box structure under aerodynamic forces have been investigated and evaluated for the remaining lifetime. Regarding the unequal nature of parts, the criterion of criticality based on the stress ratio on the piece is based on stress tolerance of the piece. Accordingly, given the lower supply tension in the second main rack, this piece was introduced as a critical piece.