Airplane wing will experience vibration from various sources due to airflow during flight and mechanical equipment. Vibration is the major consideration to the safety of airplanes since it can lead to resonance, structure failures and system breakdown. Resonance will increase vibration deformation which can cause structure failure. One of the vibration sources is the abnormal vibration resulting from imbalance of fuel weight. Therefore, this project investigates the vibration deformation of a plane wing (Airfoil NACA 2415) under a harmonic load caused by fuel weight. Finite element methods like modal analysis and harmonic response analysis are used. From the results, the first six order natural frequencies of the wing are from 4.5168 Hz to 119.63 Hz, which are much smaller than the harmonic response frequency (around 150 Hz). So resonance will not happen. The maximum deformation of the fourth order of the plane wing is the largest (1.5329 mm) compared to other orders. The fuel weight during a flight is treated as a harmonic load, which is applied to the middle of the wing. The maximum harmonic response is 4.7929e−3 mm. H-convergence study are conducted to verify the numerical results are accurate. Theoretical results from Euler–Bernoulli Beam Theory are in comparison with the numerical results from modal analysis and errors between two results are very small (2.608%), indicating that the results from modal analysis are precise.
Vibration Analysis of Airplane Wing Under Fuel Weight
Lect.Notes Mechanical Engineering
International conference on Advancement in Materials, Manufacturing, and Energy Engineering ; 2022 ; Xi'an, China September 23, 2022 - September 25, 2022
Recent Advances in Applied Mechanics and Mechanical Engineering ; Kapitel : 45 ; 459-468
09.08.2023
10 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch