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

IJSRD – International Journal for Scientific Research & Development| Vol. 3, Issue 10, 2015 | ISSN (online): 2321-0613


 

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

Author(s): Vinayaka V , AMC Engineering College; Santosh Kumar, AMC Engineering College; Byra Reddy, AMC Engineering College

Keywords: Static stress analysis, vertical tail, fatigue, AL 7075 T6, CATIA V5 R19, MSC PATRAN and MSC NASTRAN, CFD

Abstract: 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.


I. INTRODUCTION

Aircraft is a transportation vehicle which is designed to move people and cargo from one place to another. The shape and size of the aircraft depends on its task. The assembly of horizontal stabilizer and vertical stabilizer is known as empennage. Whose function is maintaining stability and control. In conventional tail configuration the vertical tail placed on top of the fuselage. The trailing end of vertical stabilizer consisting movable rudder, that allows pilot control yaw. The rudder is attached to vertical tail by hinges. When rudder deflects it vary amount of force generated by tail surface and that force is used to generate and control yawing motion of aircraft. The vertical tail contains spars and ribs as inner components,

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