Fatigue crack growth prediction under spectrum load using crack driving force DK 13;

Manjunatha, CM (2006) Fatigue crack growth prediction under spectrum load using crack driving force DK 13;. AIAA Journal, 44 (2). pp. 396-399. ISSN 0001-1452

Full text available as:
[img] PDF
Restricted to CSIR-NAL Registered users only

Download (1364Kb)
    Official URL: http://www.aiaa.org


    The damage tolerance concept is widely used in the aircraft industry to analyze the fatigue life of aircraft components. The total fatigue life of a component consists of life until a crack is initiated and life until this crack propagates to a critical size. Because of the existence of minor cracks at stress raisers in aging airframes, analysis of crack growth life assumes significant importance. Studies on fatigue crack growth behavior coupled with nondestructive test methods would help in determining inspection interval schedules for safe operation of the aircraft. In crack growth anallysis, the spectrum load blocks required for a fatigue crackt to grow from a given initial size to a critical size is evaluated based on well-established fracture mechanics principles.

    Item Type: Journal Article
    Additional Information: Copyright for this article belongs to AIAA
    Uncontrolled Keywords: Aircraft components;Fatigue cracks;Aircraft aging;Crack propagation;Airframes;Fatigue life;Aircraft safety;Load distribution (forces);Fracture mechanics;Flaw detection; Nondestructive tests;Damage tolerance
    Subjects: AERONAUTICS > Aircraft Propulsion and Power
    Division/Department: Structural Integrity Division
    Depositing User: Mrs Manoranjitha M D
    Date Deposited: 25 Feb 2010
    Last Modified: 24 May 2010 09:50
    URI: http://nal-ir.nal.res.in/id/eprint/2621

    Actions (login required)

    View Item