Commenced in January 2007
Frequency: Monthly
Edition: International
Paper Count: 32731
Structural Analysis of Aircraft Wing Using Finite Element Analysis

Authors: Manish Kumar, Pradeep Rout Aditya Kumar Jha, Pankaj Gupta


Wings are structural components of an aeroplane that are used to produce lift while the aircraft is in flight. The initial assault angle of the wing is definite. Due to the pressure difference at the top and bottom surfaces of the wing, lift force is produced when the flow passes over it. This paper explains the fundamental concept of the structural behaviour of a wing threatened by flowing loads during the voyage. The study comprises the use of concepts and analysis with the help of finite element analysis. Wing assembly is the first stage of wing model and design, which are determined by fascinating factual features. The basic gathering wing consists of a thin membrane, two poles, and several ribs. It has two spars, the major spar and the secondary spar. Here, NACA 23015 is selected as the standard model for all types of aerofoil structures since it is more akin to the custom aerofoil utilized in large aircraft, specifically the Airbus A320. Two rods mostly endure the twisting moment and trim strength, which is finished with titanium contamination to ensure enough inflexibility. The covering and wing spars are made of aluminium amalgam to lessen the structural heaviness. Following that, a static underlying examination is performed, and the general contortion, equivalent flexible strain, and comparing Von-Mises pressure are obtained to aid in investigations of the mechanical behaviour of the wing. Moreover, the modular examination is being upheld to decide the normal pace of repetition as well as the modular state of the three orders, which are obtained through the pre-stress modular investigation. The findings of the modular investigation assist engineers in reducing their excitement about regular events and turning away the wing from the whirlwind. Based on the findings of the study, planners can prioritise union and examination of the pressure mindfulness range and tremendous twisting region. All in all, the entertainment outcomes demonstrate that the game plan is feasible and further develop the data grade of the lifting surface.

Keywords: FEM, Airbus, NACA, modulus of elasticity, aircraft wing.

Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 428


[1] A. Aabid, M.A.M.B.M. Zakuan, S.A. Khan, Y.E.J.A.S. Ibrahim, Structural analysis of three-dimensional wings using finite element method, 5 (2022) 47-63.
[2] Y. Abbas, T. Elsonni, A.A. Abdulmajid, A. Khalafallh, M.J.I.B. Alnazir, Structural analysis of a transport aircraft wing, 13 (2021) 3-9.
[3] N. Akshayraj, J.A. Dhanraj, J.M. Solomon, S. Salyan, M. Subramaniam, M. Mohan, R.K. Chetty, R.C.J.M.T.P. Paul, Design and analysis of a tail sitter (VTOL) UAV composite wing, (2022).
[4] J.S.M. Ali, S.S.B.J.C.L. Haron, Stress Analysis of Composite Aircraft Wing using Coupled Fluid-Structural Analysis, 13 (2021) 78-86.
[5] S. Elangovan, C. Sureshkumar, P. Divyabarathi, Design and Analysis of Aircraft Wing Spar with Different Materials Using Ansys.
[6] P. Gupta, B.J.A.S.C. Singh, Local mean decomposition and artificial neural network approach to mitigate tool chatter and improve material removal rate in turning operation, (2020) 106714.
[7] P. Gupta, B.J.J.o.V. Singh, Control, Ensembled local mean decomposition and genetic algorithm approach to investigate tool chatter features at higher metal removal rate, 28 (2022) 30-44.
[8] P. Gupta, B.J.S.C. Singh, Investigation of tool chatter using local mean decomposition and artificial neural network during turning of Al 6061, (2021) 1-24.
[9] K. Jha, I. Yeswanth, D. Manish, Y. Tyagi, Structural and Modal Analysis of PEEK-CF Composite for Aircraft Wing, Recent Trends in Engineering Design, Springer, 2021, pp. 101-112.
[10] M. Kumar, A.K. Jha, Y. Bhagoria, P. Gupta, A review to explore different meshless methods in various Structural problems, IOP Conference Series: Materials Science and Engineering, IOP Publishing, 2021, pp. 012119.
[11] M. Kumar, J. Rajiyan, P.J.M.T.P. Gupta, A computational approach for solving elasto-statics problems, 46 (2021) 6876-6879.
[12] Y.-s. Meng, L. Yan, W. Huang, T.-t. Zhang, Z.-b.J.J.o.Z.U.-S.A. Du, Structural design and analysis of a composite wing with high aspect ratio, 20 (2019) 781-793.
[13] S.S.J.T.J.o.C. Raj, M. Education, Numerical Analysis of an Aircraft Wing, 12 (2021) 3760-3766.
[14] P. Sondankar, R. Arakerimath, Stress and Failure Analysis of Aircraft Wing Using Glare Composite and Aluminum 7075, International Conference on Reliability, Risk Maintenance and Engineering Management, Springer, 2019, pp. 33-39.