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Advances in Structural Integrity pp 15–26Cite as

Fracture Mechanics Analysis of Fuselage Structural Joints with Cracks

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Abstract

Fracture mechanics provides a methodology for prediction, prevention and control of fracture in materials, components, and structures. Fracture mechanics analysis is the backbone of damage tolerant design. Objectives of fracture mechanics analysis are: (1) stress analysis of cracks to derive crack tip stress field equations and define crack tip stress intensity factors , (2) determination of SIF solutions as function of crack length, orientation and applied loads for a given geometry, (3) prediction of mixed mode fracture under static, dynamic, and sustained loads, (4) prediction of residual strength as a function of crack length. The focus of this paper is on fracture mechanics analysis of longitudinal and circumferential joints of aircraft fuselage structure with cracks. The loading is by internal pressure. Commercial FEA software ANSYS and a special purpose post-processing subprogram called 3MBSIF are used to determine mixed mode membrane and bending SIF solutions. Residual strength prediction is based on the use of strain energy density theory of fracture. Significant results of this study are graphically presented and discussed in this paper.

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Abbreviations

t :

Thickness

E :

Modulus of elasticity

υ :

Poisson’s ratio

a 0 :

Initial half crack length

a cr :

Critical half crack length

K 1 :

Mode 1 stress intensity factor

K 2 :

Mode 2 stress intensity factor

K 3 :

Mode 3 stress intensity factor

∆K 1 :

Mode 1 stress intensity factor range

∆K 2 :

Mode 2 stress intensity factor range

N :

Number of cycles

References

  1. S. Pitt, R. Jones, Multiple-site and widespread fatigue damage in ageing aircraft. Eng. Fail. Anal. 4(4), 237–257 (1997) (Elsevier)

    Google Scholar 

  2. G. Samavedam, D. Hoadley, Fracture and fatigue strength evaluation of multiple site damaged aircraft fuselages—curved panel testing and analysis. Final Report, DOT/FAA/CT-94/10, DOT-VNTSC-FAA-93-8 (1994)

    Google Scholar 

  3. G. Samavedam, D. Hoadley, J. Davin, in Structural Integrity of Ageing Airplanes, Test Facility for Evaluation of Structural Integrity of Stiffened and Jointed Aircraft Curved Panels, (Springer, 1991), pp. 321–337

    Google Scholar 

  4. J. Bakuckas, Full-scale testing and analysis of fuselage structure containing multiple cracks. Report DOT/FAA/AR-01/46, (2002)

    Google Scholar 

  5. D.Y. Jeong, O. Orringer, G. C. Sih, Strain energy density approach to stable crack extension under net section yielding of aircraft fuselage. Theor. Appl. Fract. Mech. 127–137 (1995) (Elsevier)

    Google Scholar 

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Author information

Authors and Affiliations

  1. Department of Mechanical Engineering, Dayananda Sagar College of Engineering, Bangalore, 560078, India

    H. Ramesha & H. V. Lakshminarayana

  2. Department of Mechanical and Manufacturing Engineering, MSRUAS, Bangalore, 560058, India

    N. C. Mahendra Babu

Authors
  1. H. Ramesha
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  2. N. C. Mahendra Babu
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  3. H. V. Lakshminarayana
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Corresponding author

Correspondence to H. Ramesha .

Editor information

Editors and Affiliations

  1. Department of Mechanical Engineering, Indian Institute of Technology Madras, Chennai, Tamil Nadu, India

    Raghu Prakash

  2. Department of Materials Engineering, Indian Institute of Science, Bangalore, Karnataka, India

    Vikram Jayaram

  3. Department of Mechanical Engineering, University of Arkansas, Fayetteville, Arkansas, USA

    Ashok Saxena

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© 2018 Springer Nature Singapore Pte Ltd.

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Ramesha, H., Mahendra Babu, N.C., Lakshminarayana, H.V. (2018). Fracture Mechanics Analysis of Fuselage Structural Joints with Cracks. In: Prakash, R., Jayaram, V., Saxena, A. (eds) Advances in Structural Integrity. Springer, Singapore. https://doi.org/10.1007/978-981-10-7197-3_2

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  • DOI: https://doi.org/10.1007/978-981-10-7197-3_2

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  • Publisher Name: Springer, Singapore

  • Print ISBN: 978-981-10-7196-6

  • Online ISBN: 978-981-10-7197-3

  • eBook Packages: EngineeringEngineering (R0)

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