Damage tolerant evaluation of cracked stiffened panels under fatigue loading

Author:

MURTHY A RAMA CHANDRA,PALANI G S,IYER NAGESH R

Publisher

Springer Science and Business Media LLC

Subject

Multidisciplinary

Reference21 articles.

1. Brussat T R, Kathiresan K and Rudd J L (1986) Damage tolerance assessment of aircraft attachment lugs, Eng. Fracture Mech. 23: 1067–1084

2. Cali C and Citarella R (2004) Residual strength assessment for a butt-joint in MSD condition, Adv. Eng. Software 35: 373–382

3. David Broek (1989) The practical use fracture mechanics (Netherlands: Kluwer Academic Publishers)

4. Dawicke D S C (1997) Overload and underload effects on the fatigue crack growth behaviour of the 2024-T3 Aluminum Alloy, NASA Contractors Report 201668

5. Irwin G R (1957) Analysis of stress and strain near the end of a crack traversing a plate, J. Appl. Mech. 24

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1. Design and Analysis of Aircraft Wing Rib with Different Configuration for A380 model;international journal of engineering technology and management sciences;2023

2. Structural Response and Remaining Life of Damaged Composites;Applied Mechanics and Materials;2015-11

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