Design and Linear Static Analysis of Transport Aircraft Vertical Tail for Different Rudder Deflection (Rotation)

The design of vertical tail structure varies according to nature of aircraft and its function. The experimental test of vertical tail structure is difficult and more expensive process. In this present work detailed design of transport aircraft vertical tail with rudder structure modelling done by using CATIA V5 R19 software. The static stress analysis is carried out to find the stresses at of the vertical tail with rudder structure for different deflection of rudder. The stresses are estimated to find the safety factor of the structure using finite element approach with the help of MSC/PATRAN and MSC/NASTRAN software. The material used in the vertical tail structure is aluminium 7075-T6, which has high fatigue strength. From the analysis it is found that maximum principal stress of vertical tail structure is less than yield strength of aluminium 7075-T6 alloy. The maximum principal stress value form analysis is used to find fatigue damage calculations for vertical tail structure. The obtained analytical result shows that safe no of fatigue life hours of vertical tail structure. The result is verified with reserve factor approach.