Structural analysis of Aircraft fuselage splice joint

• Published in: IOP conference series. Materials Science and Engineering Vol. 149; no. 1; pp. 12127 - 12134
• Main Authors: Udaya Prakash, R, Raj Kumar, G, Vijayanandh, R, Senthil Kumar, M, Ramganesh, T
• Format: Journal Article
• Language: English
• Published: Bristol IOP Publishing 01.09.2016
• Subjects: Aircraft; Airframes; Bonded joints; CAD; Composite materials; Computer aided design; Fuselages; Mathematical models; Numerical methods; Riveted joints; Rivets; Shear stress; Strength to weight ratio; Stringers; Structural analysis; Three dimensional analysis; Three dimensional models
• ISSN: 1757-8981; 1757-899X
• DOI: 10.1088/1757-899X/149/1/012127

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.