Advertisement

Journal of Failure Analysis and Prevention

, Volume 17, Issue 4, pp 780–787 | Cite as

Mixed-Mode Stress Intensity Factor Determination of Riveted Lap Joints Used in Aircraft Fuselage Structures

  • S. Suresh Kumar
  • H. Ashwin Clement
  • R. Karthik
Technical Article---Peer-Reviewed
  • 131 Downloads

Abstract

In the present work, mixed-mode stress intensity factor (SIF) of multiple cracks in a riveted lap joint has been determined, with and without the presence of stringer under two different (uniaxial and biaxial) loading conditions. Geometry correction factor (Y) has been determined with consideration of mode II and mode III fractures, and the effect of stringer on SIF of intermediate as well as edge cracks was investigated. Diametrically opposite surface cracks with various crack depth ratios (a/t) were considered for a typical longitudinal splice joint. At the crack middle region [(S/S 0) = 0], SIF of cracks estimated under uniaxial loading condition reduces gradually with crack depth ratio due to frictional contact, whereas in the case of biaxial loading, higher SIF was observed at lower crack depths [(a/t) = 2]. The presence of stringer reduces the SIF of multiple cracks as it decreases the secondary bending moment caused by the eccentric loading. Compression of crack surfaces is observed at regions closer to crack middle [(S/S 0) = −0.33] due to the presence of stringer, and mode I fracture was observed to be dominant at the crack surface region [(S/S 0) = ± 1]. Influence of mode II fracture is higher at the crack middle region due to crack interaction in unstiffened plates, whereas the effect reduces with the presence of stringer. A three-parameter relationship has been developed to estimate the SIF of multiple cracks in a riveted lap joint. The residual life of the riveted joints can be determined from the calculated mixed-mode SIF.

Keywords

Stress Intensity factor Mixed-mode fracture Biaxial loading Crack depth ratio Stringer 

List of symbols

a

Crack length (mm)

t

Thickness of the sheet (mm)

S0

Points along the crack front

(a/t)

Crack depth ratio

Y

Geometric correction factor

S/S0

Location ratio

σh

Hoop stress (MPa)

σe

Longitudinal tension (MPa)

P

Internal pressure (MPa)

R

Radius of the fuselage (mm)

σ

Far field loading (MPa)

KI

Mode I stress intensity factor (MPa√m)

KII

Mode II stress intensity factor (MPa√m)

KIII

Mode III stress intensity factor (MPa√m)

Kmix

Effective stress intensity factor (MPa√m)

f

Friction coefficient

Notes

Acknowledgments

This work was financially supported by the management of SSN College of Engineering, Chennai, India.

References

  1. 1.
    H. Terada, A proposal on damage tolerant testing for structural integrity of aging aircraft-learning from JAL accident in 1985. Fract. Mech. 25, STP 1220 (1995)Google Scholar
  2. 2.
    M. Skorupa, T. Machniewicz, A. Korbel, Fatigue crack location and fatigue life for riveted lap joints in aircraft fuselage. Int. J. Fatigue 58, 209–217 (2014)CrossRefGoogle Scholar
  3. 3.
    M. Skorupa, A. Skorupa, T. Machniewicz, A. Korbel, Effect of production variables on the fatigue behaviour of riveted lap joints. Int. J. Fatigue 32(7), 996–1003 (2010)CrossRefGoogle Scholar
  4. 4.
    In Erdogan, F. (ed.) Fracture Mechanics. ASTM STP 1220, 25 (ASTM, Philadelphia, 1995), pp. 557–574Google Scholar
  5. 5.
    L.F.M. da Silva, J.P.M. Goncalves, F.M.F. Oliveira, P.M.S.T. de Castro, Multiple-site damage in riveted lap-joints: experimental simulation and finite element prediction. Int. J. Fatigue 22(4), 319–338 (2000)CrossRefGoogle Scholar
  6. 6.
    H. Hertel, Fatigue Strength of Structures (Springer-Verlag, Berlin, 1969)Google Scholar
  7. 7.
    H. Vlieger, Results of uniaxial and biaxial tests on riveted fuselage lap joint specimens, in Proceedings of FAA/NASA International Symposium of Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, Hampton, VA, 4–6 May 1994. NASA CP 3274, pp. 911–930Google Scholar
  8. 8.
    M.P. Szolwinski, G. Harish, P.A. McVeigh, T.N. Farris, The role of fretting crack nucleation in the onset of widespread fatigue damage: analysis and experiments, in Proceedings of the FAA–NASA Symposium on the Continued Airworthiness of Aircraft Structures, Atlanta, Georgia, 1997, ed. by C.A. Bigelow, W.J. Hughes, pp. 585–596Google Scholar
  9. 9.
    J. Schijve, Multiple site damage of riveted joints, in International Workshop on Structural Integrity of Ageing Airplanes, Durability of Metal Aircraft Structures (Atlanta, 1992), pp. 2–27Google Scholar
  10. 10.
    J. Schijve, Multiple-site damage in aircraft fuselage structures. Fatigue Fract. Eng. Mater. 18, 329–344 (1995)CrossRefGoogle Scholar
  11. 11.
    R.P.G. Muller, An Experimental and Analytical Investigation on the Fatigue Behavior of Fuselage Riveted Lap Joints. The Significance of the Rivet Squeeze Force and a Comparison of 2024-T3 and Glare 3, Ph.D. thesis (Tu Delft, Delft, 1995)Google Scholar
  12. 12.
    T.P. Soetikno, Residual Strength of the Fatigued 3 Row Riveted Glare3 Longitudinal Joint, Master Thesis (Aerospace Engineering, Delft University of Technology, 1992) Google Scholar
  13. 13.
    M.C.Y. Niu, Airframe Structural Design: Practical Design Information and Data on Aircraft Structures, 2nd edn. (Hong Kong Conmilit Press limited, 1999)Google Scholar

Copyright information

© ASM International 2017

Authors and Affiliations

  • S. Suresh Kumar
    • 1
  • H. Ashwin Clement
    • 1
  • R. Karthik
    • 1
  1. 1.Department of Mechanical EngineeringSSN College of EngineeringChennaiIndia

Personalised recommendations