Abstract:
During the service life of aerospace structures, fatigue loads application may cause catastrophic failure due to fracture of structure at critical locations. Study of crack initiation and propagation plays a major role in the aerospace industry, not only in the design of new structures and components but also ongoing maintenance. Damage Tolerance Analysis (DTA) is a procedure that defines whether a crack can be sustained safely during the projected service life of the structure. Using this methodology, service life of an aerospace structure can be determined and may be extended. In this paper crack growth behavior of notched specimen is discussed in details. The fatigue loadings applicable to the specimen are four points bending in rotation of 1000 rpm. Life assessment of any other engineering component under rotational fatigue loadings can be made using the similar technique. Effect of damage increment on the convergence of the residual strength is investigated for a notched component made of Aluminum 2024-T6. The stress distribution with notch growth is discussed in detail. Simulations using Linear Elastic Fracture Mechanics (LEFM) laws are performed, that results the damage scenarios to be assessed in the real structural geometry and loading environment using Stress concentration Factors. Fatigue behavior of the component is investigated experimentally using four points bending rotation. The fatigue experiments were performed under constant stress amplitude. It has been observed that the computed fatigue curves fit well with the experimental results.
Page(s):
106-113
DOI:
DOI not available
Published:
Journal: Proceedings 6th International Bhurban Conference on Applied Sciences and Technology , Volume: 1, Issue: 0, Year: 2009