International Research Journal of Engineering and Technology (IRJET)
e-ISSN: 2395 -0056
Volume: 04 Issue: 06 | June -2017
p-ISSN: 2395-0072
www.irjet.net
Stress analysis of splice joint in an aircraft fuselage with prediction of fatigue life to crack initiation Venkatesh Deshpande1, Pratik Phadnis2, S. P. Avadhani3 1Assistant
Professor, Department of Mechanical Engineering, KLS Gogte institute of Technology, Belagavi, Karnataka, India 2Assistant Professor, Department of Mechanical Engineering, KLS Gogte institute of Technology, Belagavi, Karnataka, India 3Assistant Professor, Department of Mechanical Engineering, KLS Gogte institute of Technology, Belagavi, Karnataka, India ---------------------------------------------------------------------***--------------------------------------------------------------------3. METHODOLOGY Abstract - stress analysis of a splice joint in a transport aircraft is studied in the current paper. Splice joint panel consists of skin plates, doubler plat.e Alloy of Aluminium 2024-T351 is considered for all the structural elements of the panel. We will be carrying out 2D Finite Element Analysis of splice joint. At the rivet locations Distribution of fasteners loads and local stress field. For a crack to initiate splice joint is one of the critical location. At maximum stress location prediction of fatigue life for crack initiation will be studied
In aerospace design, fatigue analysis is routinely used to minimize the fatigue accidents, as every component added important to aircraft. Therefore minimization of fatigue has played a significant role in aircraft industry.
4. DESIGN METHODOLOGY Linear Static Analysis:
Key Words: fuselage, splice joint, , crack propagation, finite element analysis.
CATIA V4 is used for the geometric modeling of the structure for the linear static analysis of the splice joint panel. Then abstraction of mid faces can be done. . For preprocessor the model is impoted , where MSC Patran V7 is used. Using MSC Patran a finite element model is created. For a model all the element properties, boundary conditions and loads are applied . For solving purpose MSC/.Nastran is used. After solving the model, it is again imported to MSC Patran for post processing. The results are obtained using MSC Patran and are plotted
1.INTRODUCTION A method of joining two members end to end is called Splice joint, If the material length is not sufficient then we opt for Splice joint. . As an alternate to Lap joint and Butt joint the Splice joint can be used. For shear flows span wise the splices are designed. In the majority of cases chord wise loads are small and can be ignored. Due to cabin pressurization the skin splices of longitudinal are designed for Hoops tension loading but It is required to consider local shear loads. Some times Skin and attachment both should be considered for analysis. Fastener hole-out efficiency is to be be maintained at 75 to 80 percent if a lower skin is designed to lower margin of safety.
1st phase: Stress analysis 2nd phase: fatigue analysis
5. Geometry:
2. OBJECTIVE: The dissertation works objective will be stress analysis of splice joint in aircraft fuselage along prediction of fatigue life to crack initiation. . For a study typical splice joint panel consisting of skin plates, doubler plate is considered. For structural analysis of a panel Aluminium alloy 2024-T351 material is considered. On a splice joint panel a twodimensional finite element-analysis will be carried out.
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Fig-1: Geometric model of fuselage segment contains butt joint
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