EXPERIMENTAL DYNAMIC ANALYSIS OF AIRCRAFT WING

The objective of this project is to analyze the dynamic structural
response of an aircraft wing and to simulate it for various stability conditions.
This report briefly explains aircraft wing vibration, deformation, stresses, strains,
frequencies, and its application using ANSYS. The analysis is carried out in
ANSYS workbench. The loading conditions are the self-weight of the wing and
pressure is about 0.5PSI, Maneuver loads, Surface loads, Vibrational loads, FSI. The
output extracted is the mode shapes, Vibrations, Maneuver Loadings, Surface
Loadings, Total Deformation, Frequencies at nodes, and Von-Misses Stress of
the wing at different frequencies and FSI of lift and drag over wing. The dynamic response data will be acquired by
Fabricating the Aluminium wing with the help of sensors used to calculate the
vibration along the wing. The design of the prototype is done in CATIA V5
software and model is generated. At the end, the report made would provide us
with a better perspective for the scope of optimization in the required fields.