|
Vol.23, No.2, 2023, pp. 167–172 |
|
NUMERICAL AND EXPERIMENTAL ANALYSIS OF THE INTEGRITY OF LIGHT AIRCRAFT WING STRUCTURE Aleksandar Grbović1*, Abdussalam Yousef Solob1, Simon Sedmak2, Aleksandar Sedmak1 1) University of Belgrade, Faculty of Mechanical Engineering, Belgrade, SERBIA *email: agrbovic@mas.bg.ac.rs 2) University of Belgrade, Innovation Centre of the Faculty of Mechanical Engineering, Belgrade, SERBIA
|
|
Abstract The wing spar is connected to the supporting elements of the aircraft fuselage through specially designed elements -aircraft fittings. All loads from the wing are transmitted to the main frame and through the wing-fuselage fitting. It is needless to point out the extreme importance of the accurate design of this fitting: its fatigue damage leads to an immediate separation of the wing from the fuselage and a consequent loss of aircraft. During flight, fatigue cracks appear on parts of the wing exposed to tensile stresses. These cracks are monitored, and certain measures are taken when they reach a critical length, but their appearance is not tolerated in the wing-fuselage fittings. This is also the reason why crack growth in these members has not been studied so far and why experimental tests of the remaining fatigue life of the damaged fitting were not required from the manufacturer. Determination of stress state is of great importance as it can be used to predict the locations of potential crack initiation. Experimental and numerical analysis of this problem is presented. Keywords: stress analysis, extended finite element method, wing spar, CS23 standard |
|
full article (874 kB)
|
