Design and Analysis of Aircraft Wing Rib with Different Configuration for A380 model

AUTHOR(S)

A J Sriganapathy, K Akash, M Susiendhar Baabu, S Arumugam, M Vishnu

DOI: https://doi.org/10.46647/ijetms.2023.v07i03.045

ABSTRACT
The wing rib of an aircraft is a very critical part. It provides airfoil contour to the wing. Its principal role in wing structure is that to transfer load from skin to stringers or other parts of wing. Cut-outs in aircraft structural components such as wing spars and ribs are commonly encountered in practice. Cut-outs are often necessary for lightening holes, passages for wire bundles, hydraulic and fuel pipes, control linkages, accessibility for final assembly and maintenance inspections. The shape of the cutout is a important parameter where depends on the cutout shape the structural parameters may get varied. The main objective in here is to study about the influence of cutout in rib section with different cutout shapes. The Airbus A380 model is considered and the rib section for the model is modeled using Solidworksmodeling package and the model is analyzed for different cutout shapes. The model has the cutout shapes such as circle, ellipse and rectangle, where the circular hole is a most practiced method in recent models. The numerical analysis is carried out in ANSYS static structural analysis to find the structural parameters such as stress, strain, deformation and weight.

Page No: 340 - 352

References:

[1]. Grigory I. Nesterenko, “Service life of airplane structures”, Central Aerohydrodynamic Institute (TsAGI), Russia, 2002.
[2]. A Rama Chandra Murthy, G S PalaniNagesh R Iyer, “Damage tolerant evaluation of cracked stiffened
panels under fatigue loading”, Sadhana Vol. 37, Part 1, February 2012, pp. 171–186.
[3]. AdarshAdeppa, Patil M S and Girish K E (2012), “Stress Analysis and Fatigue Life Prediction for Splice Joint in an Aircraft
Fuselage through an FEM Approach”, International Journal of Engineering and Innovative Technology (IJEIT), Vol. 1, No.
4, pp. 142-144.
[4]. J. C. Newman, Jr, “Advances in fatigue and fracture mechanics analyses for aircraft structures”, Mechanics and Durability
Branch, NASA Langley Research Center, Hampton, VA, USA.
[5]. A. Brot et al., “The damage-tolerance behaviour of integrally stiffened metallic structures”, Israel Annual Conference on
Aerospace Sciences, 2008
[6]. F.H.Darwish, G.M.Atmeh, Z. F. Hasan Design (2012) “Analysis and Modelling of a General Aviation Aircraft” Volume 6,
Number 2, ISSN 1995-6665 Pages183 – 191.
[7]. Michael Chung Yung Niu, “Airframe Structural Design”, Conmilit press Ltd, 1989, pp. 90-117
.MichaelBauccio (1993), ASM Metals Reference Book, 3rdEdition, ASM International, Materials Park, OH.
[8]. Fawaz, S. A. and BörjeAndersson. “Accurate Stress Intensity Factor Solutions for Unsymmetric Corner Cracks at a
Hole”. Proc. of the Fourth Joint NASA Conference on Aging Aircraft, vol 15 (2000),pp 135-139
[9]. C.S. Kusko, J.N. Dupont, A.R. Marder, “Influence of stress ratio on fatigue crack propagation behavior of stainless steel
welds”. Wlding Journal, vol19,(2004), pp 122-130
[10]. N. Ranganathan, H. Aldroe, F. Lacroix, F. Chalon, R. Leroy, A. Tougui.“Fatigue crack initiation at a notch”. InternationalJournal of Fatigue, vol 33, (2011), pp 492-499

How to Cite This Article:
A J Sriganapathy, K Akash, M Susiendhar Baabu, S Arumugam, M Vishnu .Design and Analysis of Aircraft Wing Rib with Different Configuration for A380 model . ijetms;7(3):340-352. DOI: 10.46647/ijetms.2023.v07i03.045