Investigation on buckling response of the aircraft’s wing using finite-element method

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ABSTRACT

The present investigation aims to provide the structural design and analysis of an aircraft wing which are the main lifting–load–carrying members in the aircraft structure. Almost 80% of the lift force is produced by the wing structure in an aircraft. Because of the loading, wing structure tends to buckle and buckling reduces the load-carrying capability and the components may fail below the design limit load. In the present investigation, a standard transport aircraft wing is considered and buckling analysis is carried out. The initial design was found to buckle. So several design modifications were made to make the design safe in buckling. Various materials were used for wing construction. Numerous results obtained using finite-element analysis ANSYS software, comparison studies, and parametric studies are presented.

KEYWORDS:

• Aircraft wing design
• buckling
• critical buckling load
• composite structure
• FEM (Finite Element Method)

Additional information

Notes on contributors

Ravi Kumar B.

Ravi Kumar is a trained Aerospace engineer with specialization in composite Materials and Aerospace Propulsion. He is presently working as Assistant Professor in Aerospace Department Under SoME, SASTRA University. His Research area includes Aerodynamics, Thermal Engineering, Nanomaterials, CNTs, Nonlocal Theory, Optimization, Smart Materials.