Static and Dynamic Analysis of Vibration in an Aircraft Using Finite Element


Mohammed Mousa Al-azzawi†, Hasanen Mohammed Hussain‡, Laith Jaafer Habeeb‡†


†Department of Refrigeration and Air Conditioning, Al-Rafidain University Collage, Baghdad, Iraq.

‡ Department Mechanical Engineering, University of Technology, Baghdad, Iraq.

‡†Training and Workshop Centre, University of Technology, Baghdad, Iraq.

Corresponding Author Email: Mohammed.azzawi55@gmail.com,hasanen.alsaady@yahoo.com,20021@uotechnology.edu.iq

This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Numerical simulation was performed to study an aircraft using Ansys software program. The three-dimensional geometry model was simulated through a series of analysis programs companied with Ansys. Fluent, Static structure, Modal, and Random vibration analysis models was used. Structural Steel was set as the material of the aircraft. The simulation was generated for different aircraft velocities (500, 640, 778 m/s). The result was obtained for the pressure and velocity around the aircraft as well as the stresses over the aircraft and the deformations. It was found that the velocity and the pressure of the space around the aircraft increase as the velocity of the aircraft increases, whereas the highest percentage of the air pressure and velocity were concentrated at the end of the aircraft. The stresses and the deformations over the aircraft increases as the velocity of the aircraft increases, whereas the most stresses and deformations occur at the wings and the tail of the aircraft.