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@article{180080,
        author = {Dhanwin Mehta and Kaustubh Avharkar and Pranjal Chandekar and Amar Kulkarni},
        title = {Structural Analysis OF Different Skin Stringer Panels},
        journal = {International Journal of Innovative Research in Technology},
        year = {2025},
        volume = {12},
        number = {1},
        pages = {95-98},
        issn = {2349-6002},
        url = {https://ijirt.org/article?manuscript=180080},
        abstract = {This project report presents a comprehensive 
study on the structural analysis of skin-stringer panel. 
Stringers are critical longitudinal components that 
contribute significantly to the strength and rigidity of 
the aircraft’s fuselage by distributing aerodynamic 
loads and reducing skin buckling. The study explores 
structural analysis of three various skin-stringer 
panels-Omega, L-shaped, and Z-shaped stringers that 
are most often utilized in aerospace applications to 
provide strength and stiffness to aircraft fuselages. The 
research aims to assess their performance under 
compressive and bending loads to identify the most 
effective design for weight savings and structural 
integrity. The design process of project was carried out 
on CATIA V5, with each type of stringer modelled and 
combined with a skin panel and Z-section frame. Finite 
Element Analysis (FEA) is done on ANSYS Workbench 
to simulate the distribution of stresses, deformation, 
and buckling response under 1000 N/m² applied to skin 
and 4900 N/m² loads applied to the stringer joints. The 
material chosen for analysis was 2024-T3 aluminum 
alloy, commonly used in aerospace due to its high 
strength-to-weight ratio.},
        keywords = {ANSYS, CATIA, Finite Element Analysis,  Skin – Stringer Pannels},
        month = {May},
        }