Structural analysis of Aircraft fuselage splice joint

International Conference on Advances in Materials and Manufacturing Applications 2016

Udaya Prakash, R.^1 ; Raj Kumar, G.^1 ; Vijayanandh, R.^1 ; Senthil Kumar, M.^1 ; Ramganesh, T.^1

Department of Aeronautical Engineering, Kumaraguru College of Technology, Coimbatore, Tamil Nadu

641049, India^1

关键词: Aviation sector;    Composite skins;    Design flexibility;    ITS applications;    Numerical solution method;    Riveted joints;    Three-dimensional model;    VonMises stress;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/149/1/012127/pdf
DOI  :  10.1088/1757-899X/149/1/012127

来源: IOP

【 摘 要 】

In Aviation sector, composite materials and its application to each component are one of the prime factors of consideration due to the high strength to weight ratio, design flexibility and non-corrosive so that the composite materials are widely used in the low weight constructions and also it can be treated as a suitable alternative to metals. The objective of this paper is to estimate and compare the suitability of a composite skin joint in an aircraft fuselage with different joints by simulating the displacement, normal stress, vonmises stress and shear stress with the help of numerical solution methods. The reference Z-stringer component of this paper is modeled by CATIA and numerical simulation is carried out by ANSYS has been used for splice joint presents in the aircraft fuselage with three combinations of joints such as riveted joint, bonded joint and hybrid joint. Nowadays the stringers are using to avoid buckling of fuselage skin, it has joined together by rivets and they are connected end to end by splice joint. Design and static analysis of three-dimensional models of joints such as bonded, riveted and hybrid are carried out and results are compared.