WEIGHT OPTIMIZATION OF FTAC SECONDARY STRUCTURE OF AN AIRCRAFT

Abstract

The Fuel Tank Access Covers (FTAC) primary function is to provide the aerodynamic surface on the lower wing at the Fuel Tank Access Manholes. These manholes are used in maintenance to access the inside of the wing box. The FTACs also provide sealing of the fuel bays. Fuel Tank Access Cover area include wings, control surfaces, aero engine nacelles, fan casings, etc. These are all safety critical components which may be subjected to high velocity impacts due to bird strike or foreign object damage (FOD). Typically on wing leading edges, nacelles, or on fan blades causing fan blade debris to impact fan casings and wing or fuselage structures. Analysis tools, such as finite element (FE) codes for predicting structural stiffness and strength of the structures under quasistatic loading with relevant materials data. The aim of the present work is to optimize the Fuel tank Access Cover. As the weight optimization of each component in the Aircraft plays as a significant role in the performance of the aircraft. The 3D modeling of fuel tank access plate is designing using PRO-E and FEA analysis especially structural analysis was done using ANSYS. The structural strength of the Inner Cover, Outer Cover, and Fasteners are validated. Objectives  To study about the FTAC design.  To study various conditions which can be replicated to get the most approximate results?  To demonstrate a CAD model of FTAC by using predominant software PRO (E).  To develop a Finite Element Model of Fuel Tank Access Cover accurately to the dimensions with the limited information available as any company does not release all the designs data. To determine the structural behavior of Fuel Tank Access Cover with different boundary conditions by using ANSYS software.