Optimization of Design Parameters of Aircraft Wing Structure with Large Cut Outs using Damage Tolerant Design and Finite Element analysis Approach
Thammaiah Gowda1, Jagadeesha T2, V. Dhinakaran3

1Thammaiah Gowda, Principal, Yagachi Engineering College, Hassan (Karnataka), India.
2Dr. Jagadeesha, Assistant Professor, Department of Mechanical Engineering, National Institute of Technology, Calicut (Kerala), India.
3V. Dhinakaran, Department of Mechanical Engineering, Chennai Institute of Technology, Chennai (Tamil Nadu), India.
Manuscript received on 20 May 2019 | Revised Manuscript received on 06 June 2019 | Manuscript Published on 15 June 2019 | PP: 128-132 | Volume-8 Issue-1S2 May 2019 | Retrieval Number: A00260581S219/2019©BEIESP
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)

Abstract: Wings are the lift generating components in the airframe structure. Wings are also used as fuel tanks in the transport aircraft. Cutouts are provided in the bottom skin of the wing to permit entry into the airplane fuel tanks for inspection or component repair. Finite element method is adopted for stress analysis of the structural components. MSC NASTRAN and MSC PATRAN FEM packages are used to carry out the analysis. The damage tolerance capabilities of a wing box with a fuel access cutout to ensure the structural integrity while achieving the maximum possible safety margin and a reasonable lifetime of the aircraft structure is investigated. First finite Element Modeling of the Wing box in standard FE package (Global model) is carried out followed by structural analysis of the wing box to identify the critical location for fatigue crack initiation. Once critical location is found out, then Finite Element Modeling of the Panel with critical location for more detailed analysis (Local model) is carried out. Simulation of cracks of various lengths in the Local FE model and Stress intensity factor (SIF) calculations for each crack length using Modified Virtual Crack Closure Integral (MVCCI) method. Qualitative comparison of SIF with Fracture toughness for every crack length is carried.
Keywords: Stress Concentration, Stress Intensity Factor, MVCCI, Finite Element, Damage Tolerance.
Scope of the Article: Machine Design