Modeling Of Fatigue Crack Growth in Composite Repair by Finite Element Method

Kulkarni, A S and M, Ramji (2011) Modeling Of Fatigue Crack Growth in Composite Repair by Finite Element Method. Masters thesis, Indian Institute of Technology Hyderabad.

ME09G002.pdf - Submitted Version

Download (2MB)


Fatigue failure is caused due to fluctuating loads and is one of the most common type of failure in mechanical structures. Fatigue damage starts with nucleation, crack formation and then propagation of the crack. Estimation of safe life of critical components becomes very essential in fail safe tolerant design for certification. Total life of a component generally consists of two stages viz. crack initiation and crack propagation. The proportion which each contributes will vary with the geometry, the loading and especially with the material. Crack growth behaviour is a major issue in scheduling of inspection and maintenance in variety of industries especially in aircraft industry. Here, failure leads to catastrophic consequences and loss of life. When aircraft reach the end of their service life, fatigue cracks are found to have developed along rivet holes and other highly stressed regions of the aircraft. In order to extend the life of these aircraft, repairs are made to arrest these cracks. This is because huge financial costs involved in manufacturing of aircrafts. Hence, extending the life of in-service aircrafts can provide huge saving

[error in script]
IITH Creators:
IITH CreatorsORCiD
Item Type: Thesis (Masters)
Uncontrolled Keywords: TD15
Subjects: Others > Electricity
Divisions: Department of Mechanical & Aerospace Engineering
Depositing User: Team Library
Date Deposited: 12 Nov 2014 04:38
Last Modified: 24 May 2019 06:30
Publisher URL:
Related URLs:

Actions (login required)

View Item View Item
Statistics for RAIITH ePrint 725 Statistics for this ePrint Item