International Journal of Vehicle Structures and Systems

H. Ramesha ¹, N. C. Mahendra Babu ², H. V. Lakshminarayana ¹

Affiliations
1 Dept. of Mech. Engg., Dayananda Sagar College of Engineering, Bengaluru, IN
2 Dept. of Mech. Engg., B.N.M. Institute of Technology, Bengaluru, IN

Abstract

Ring frames, stringers and skin panels are the main parts of aircraft fuselage structure. Circumferential joint is formed by joining skin panels in circumferential direction using doubler plates and adhesive bonding. In this paper finite element (FE) modeling of circumferential butt joint of fuselage structure using commercial FEA software (ANSYS) is presented. The FE model is validated using a benchmark and then fracture mechanics results are graphically presented and discussed.

Keywords

Circumferential Joint, Crack, Finite Element Modelling, Aircraft Fuselage Structure, Structural Integrity.

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