Design and Finite Element Analysis of Wing Root Attachment for Two Seater Passenger Aircraft

Aircraft is a highly complex flying structure. Generally passenger aircraft undergoes nominal maneuring flights. During the flight, when the maximum lift is generated, wings of the aircraft will undergo stress at the location of the attachment brackets. The attachment is used to carry all type of wing load to this frame. So, the wing root attachments should be high strength enough to carry the load transferred from wing. In the present research work, an attempt has been made for designing the wing root attachment frame for two seated passenger aircraft using four stringers. First we need ensure the static load carrying capability of the wing root attachment bracket. Later, the wing root fittings were designed with different iterations by adding number of stringers with varied calculations. Finally fatigue analysis was conducted to find out the stress acting on the attachment with the life expectancy calculations.By adding the stringers, the fatigue/stress will be less for wing roots and the life expectancy of wing root attachment will also increase (more than 2 folds).The methodology of Finite Element Method (FEM) has been implemented and analyzed in the present work for stress and fatigue. An attempt has been made to estimate life expectancy of the wing root attachment under fatigue analysis.The design was carried out using Catia V5 tool. The analyzing part of this research work is done using the NASTRAN-PATRAN package and the results were reported.