Design and Finite Element Analysis of Aircraft Wing using Ribs and Spars
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Abstract
In this paper, project detailed design of trainer aircraft wing structure
made by using CATIA. Then stress analysis of the wing structure is carried out to
compute the stresses at wing structure. The stresses are estimated by using the
finite element approach with the help of ANSYS to find out the safety factor of the
structure. In a structure like airframe, a fatigue crack may appear at the location of
high tensile stress. Life prediction requires a model for fatigue damage
accumulation, constant amplitude S-N (stress life) data for various stress ratios
and local stress history at the stress concentration. The response of the wing
structure will be evaluated.In this thesis, the trainer aircraft wing structure with
skin, spars and ribs is considered for the detailed analysis. The wing structure
consists of 15 ribs and two spars with skin. Front spar having „I‟ section and rear
spar having „C‟ section. Stress and fatigue analysis of the whole wing section is
carried out to compute the stresses and life at spars and ribs due to the applied
pressure load.In this project, the mentor aircraft wing with winglets with at
different angles (450 and 250) is thinking about for the itemized investigation.
Static and fatigue analysis of the entire wing area is done to figure the burdens and
life at various winglet points (250 and 450) because of the applying weight load.
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