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Structural Analysis OF Different Skin Stringer Panels

  • Unique Paper ID: 180080
  • Volume: 12
  • Issue: 1
  • PageNo: 95-98
  • 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.
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  • ISSN: 2349-6002
  • Volume: 12
  • Issue: 1
  • PageNo: 95-98

Structural Analysis OF Different Skin Stringer Panels

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