USE OF FIVE-PARAMETER OPTIMIZATION OF ATTACHMENT LUG GEOMETRY TO IMPROVE ITS FATIGUE LIFE

Vanja Stefanović Gobeljić, Aleksandar Grbović, Aleksandar Sedmak, Simon Sedmak, Gordana Djukanovic, Aleksandar Bogojević, Ivana Vučetić

DOI Number
10.22190/FUME240730043G
First page
Last page

Abstract


Pin-loaded attachment lugs are highly loaded and responsible aircraft component prone to fatigue failure. Thus, here the geometry of the wing-fuselage attach­ment lug was optimized using the fatigue life as the criterion. Separating Morphing and Adaptive Remeshing Technology (SMART) was used in the scope of Finite Element Method (FEM) to simulate fatigue crack growth by and to obtain fatigue life for different geometry parameters. Five-parameter optimization was applied, by varying two radii (rounding radius and radius of a pin hole), “hump” parameter, outer radius and thick­ness, using five different models. It was shown that fatigue life can be significantly improved with only modest increase of mass.


Keywords

Optimization, Attachment lug, SMART FEM, Fatigue crack growth

Full Text:

PDF

References


Grbović, A., Solob, A.Y., Sedmak, S., Sedmak, A., 2023, Numerical and experimental analysis of the integrity of light aircraft wing structure, Structural Integrity and Life, 23(2), pp. 167-172.

https://sassofia.com/blog/considerations-related-to-faa-supplemental-structural-inspection-programme-ssip/ (last access 26.06.2024)

Boeing's latest crisis is growing after an airline found cracks on two 737 planes that weren't due for inspection yet, https://www.businessinsider.com/boeing-737ng-pickle-fork-crack-lion-air-2019-11. (last access 26.06.2024)

https://www.theguardian.com/business/2019/nov/06/boeing-737-cracks-ryanair-grounds-three-planes-due-to-cracking-between-wing-and-fuselage. (last access 26.06.2024)

Braga, D.F.O., Tavares, S.M.O., da Silva, L.F.M., Moreira, P.M.G.P., de Castro, P. M.S.T., 2014, Advanced design for lightweight structures: Review and prospects, Progress in Aerospace Sciences, 69, pp. 29-39.

Solob, A.Y., 2021, Fatigue life analysis of damaged light aircraft wing fuselage fitting, Ph.D. Thesis, University of Belgrade, Faculty of Mechanical Engineering.

Barter, S., Sharp P.K., Clark, G., 1994, The failure of an F/A-18 trailing edge flap hinge, Engineering Failure Analysis, 1(4), pp. 255-266.

Witek, L., 2006, Failure analysis of the wing-fuselage connector of an agricultural aircraft, Engineering Failure Analysis, 13(4), pp. 572-581.

Azevedo, C.R.F., Hippert Jr, E., Spera, G., Gerardi, P., 2002, Aircraft landing gear failure: fracture of the outer cylinder lug, Engineering Failure Analysis, 9(1), pp. 1-15.

Huang, X., Moan, T., 2007, Improved modeling of the effect of R-ratio on crack growth rate, International Journal of fatigue, 29(4), pp. 591-602.

Lanciotti, F. Nigro, Polese, C., 2006, Fatigue crack propagation in the wing to fuselage connection of the new trainer aircraft M346, Fatigue Fract Eng Mater Struct., 29(12), pp. 1000-1009.

Wu, L.M., He, Y.T., Zhang, H.W., Cui, R.H., Du, J.Q., Ding, H., 2011, Study on fatigue crack growth model of attachment lug subjected to oblique pin-load, Advanced Materials Research, 291-294, pp. 1043-1050.

Sumanth, T.A.M.H., 2018, Comparative analysis of aircraft wing fuselage lug attachment bracket, International Journal for Technological Research in Engineering, 5(11), pp. 4422-4429.

Shridhar, K., Suresh, B.S., Kumar, M.M., 2019, Fatigue Analysis of Wing-Fuselage Lug section of a Transport Aircraft, Procedia Structural Integrity 14, pp. 375-383.

Rigby, R., Aliabadi, M. H., 1997, Stress intensity factors for cracks at attachment lugs, Engineering Failure Analysis, 4(2), pp. 133-146.

Kim, J.-H., Lee, S.-B., Hong, S.-G., 2003, Fatigue crack growth behavior of Al7050-T7451 attachment lugs under flight spectrum variation, Theoretical and applied fracture mechanics, 40(2), pp. 135-144.

Maksimović, M., Vasović, I., Maksimović, K., Trišović, N., Maksimović, S., 2018, Residual life estimation of cracked aircraft structural components, FME Transactions, 46(1), pp. 124-128.

Boljanovic, S., Maksimovic, S., 2014, Fatigue crack growth modeling of attachment lugs, International Journal of Fatigue, 58, pp. 66-74.

Boljanović, S., Maksimović, S., 2017, Fatigue damage analysis of wing-fuselage attachment lug, Procedia Structural Integrity, 5, pp. 801-808.

Antoni, N., Gaisne, F., 2011, Analytical modelling for static stress analysis of pin-loaded lugs with bush fitting, Applied Mathematical Modelling 35(1), pp. 1-21.

Mookaiya, K., Balaji, S., Balakrishan, S.R., 2013, Crack Growth Analysis in Aircraft Wing Lug Section and Fatigue Life Estimation, International Journal of Engineering Research and Technology, 2(6), pp. 2018-2023.

Naderi, M., Iyyer, N., 2015, Fatigue life prediction of cracked attachment lugs using XFEM, International Journal of Fatigue, 77, pp. 186-193.

Solob, A., Grbović, A., Božić, Ž., Sedmak, S.A., 2020, XFEM based analysis of fatigue crack growth in damaged wing-fuselage attachment lug, Engineering Failure Analysis, 112, 104516.

Grbović, A., Solob, A.Y., Sedmak, S., Sedmak, A., 2023, Optimization of wing-fuselage attachment lug, Structural Integrity and Life, 23(2), pp. 161-165.

Grbovic, A., Solob, A., Bozic, Z., Sedmak, S., Sedmak, A., 2024, Fatigue life of damaged wing-fuselage fitting, Procedia Structural Integrity 58, pp. 42-47.

Sedmak A. 2024, Fatigue crack growth simulation by extended finite element method: A review of case studies, Fatigue Fract Eng Mater Struct., e14277.

Li, H., Li, J., Yuan, H., 2018, A review of the extended finite element method on macrocrack and microcrack growth simulations, Theoretical and Applied Fracture Mechanics, 97, pp. 236-249.

Martínez, E.R., Chakraborty, S., Tesfamariam, S., 2021, Machine learning assisted stochastic-XFEM for stochastic crack propagation and reliability analysis, Theoretical and Applied Fracture Mechanics, 112, 102882.

SMART Fracture Whitepaper, available at: https://www.ansys.com/resource-library /white-paper/smart-fracture. (last access 27.06.2024)

Grbović, A., Sedmak, A., Lazić-Vulićević, Lj., Zaidi, R., Kirin, S., 2023, Extended finite element method simulation of fatigue crack growth in Charpy specimen, Structural Integrity and Life, 23(3), pp. 237-242.

Busari, Y.O., Manurung, Y.H.P., 2020, Welded high strength low alloy steel influence on fatigue crack propagation using LEFM, a practical and thematic review, Structural Integrity and Life, 20(3), pp. 263-279.

Grbović, A. Solob, A., Sedmak, S. Sedmak, A. Božić, Ž., 2024, Three-parameter optimization of an attachment lug, Structural Integrity and Life, 24(1), pp. 124-127.

ASTM E647-23a, Standard Test Method for Measurement of Fatigue Crack Growth Rates, 2023.


Refbacks

  • There are currently no refbacks.


ISSN: 0354-2025 (Print)

ISSN: 2335-0164 (Online)

COBISS.SR-ID 98732551

ZDB-ID: 2766459-4