Mixed Mode Stress Intensity Factor Determination for Single and Multiple Cracks in an Aircraft Wing

Abstract:

Structural failure of aircraft wings due to nucleation and propagation of cracks is one of the main reasons for failure of aged aircrafts. Reported studies on aircraft failures indicate that the main cause of wing failure is due to fatigue cracks which nucleate from the wing root region. Thus, determination of residual life of the cracked wing structure using fracture mechanics approach becomes important. In the present work an attempt has been made to estimate the SIF of single and multiple cracks in an aircraft wing subjected to lift force. Crack depth ratios ranging between 0.1 and 0.4 and aspect ratios of 0.6 and 1.0 have been considered. Single and multiple cracks are introduced at the wing rib region and the lift force is applied at the bottom surface of the wing. Geometric correction factor (Y) is estimated with the additional consideration of mode II and mode III fracture. The effect of crack depth ratio and number of cracks on SIF is determined. Non symmetric SIF distribution is observed with increase of crack depth ratio. It is also noted that SIF values are always higher at the crack surface region compared to crack middle region irrespective of crack depth ratio.

• Periodical: Applied Mechanics and Materials (Volumes 592-594)
• Pages: 2528-2533
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.592-594.2528
• Online since: July 2014
• Authors: S. Suresh Kumar*, V. Veeraraghavan, M. Vimalesh, Sanjay B. Bharadwaj
• Keywords: Aircraft Wing, Geometric Correction Factor, Mixed Mode, Multiple Cracks, Stress Intensity Factor (SIF)

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