Design Parameters Influencing the Fatigue Behaviour of Riveted Lap Joints

  • Andrzej Skorupa
  • Małgorzata Skorupa
Part of the Solid Mechanics and Its Applications book series (SMIA, volume 189)


Geometric variables related to the design of a riveted lap joint are the number and spacing of rivet rows, the rivet pitch in a row, the distance of the rivet from the sheet edge, the sheet thickness, the joint size, and the rivet pattern, Fig. 4.1. Because each of these parameters can exert influence on stress concentration at the rivet hole or modify the secondary bending, they also affect joint fatigue behaviour. The corresponding experimental observations reported in the literature are reviewed in the present chapter.


Fatigue Life Fatigue Strength Sheet Thickness Fatigue Test Result Longe Fatigue Life 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.


  1. ESDU data sheet No. 79031. Endurance of riveted lap joints (aluminium alloy sheets and rivets). Engineering Science Data Unit, London (1979)Google Scholar
  2. Fung, C.-P., Smart, J.: Riveted lap joints. Part 1: A numerical parametric study. Proc. Inst. Mech. Eng. Part G 211, 13–27 (1997)CrossRefGoogle Scholar
  3. Hartman, A.: A comparative investigation on the investigation on the influence of sheet thickness, type of rivet and number of rivet rows on the fatigue strength at fluctuating tension of riveted single lap joints of 24 ST Alclad sheet and 17 S rivets. Report NLR M.1943. NLR, Amsterdam (1954)Google Scholar
  4. Hartman, A., Duyn, G.C.: A comparative investigation on the fatigue strength at fluctuating tension of several types of riveted lap joints, a series of bolted and some series of glued lap joints of 24 ST Alclad. Report NLR M.1857. NLR, Amsterdam (1952)Google Scholar
  5. Hartman, A., Klaassen, W.: The fatigue strength at fluctuating tension of simple lap joints of clad 24 ST and 75 ST aluminium alloy with 2 rows of 17 S rivets. Report NLR M.2011. NLR, Amsterdam (1956)Google Scholar
  6. Hartman, A., Schijve, J.: The effect of secondary bending on the fatigue strength of 2024-T3 Alclad riveted joints. Report NLR TR 69116U. NLR, Amsterdam (1969)Google Scholar
  7. Hartman, A., Jacobs, F.A., de Rijck, P.: Tests on the effect of the size of the specimen on the fatigue strength of 2024-T3 Alclad double row riveted single lap joints. Report NLR M.2104. NLR, Amsterdam (1962)Google Scholar
  8. Hertel, H.: Ermüdungsfestigkeit der Konstruktionen. Springer, Berlin/Heidelberg/New York (1969)Google Scholar
  9. Müller, R.P.G., Hart-Smith, L.J.: Making fuselage riveted lap splices with 200-year crack-free-lives. In: Cook, R., Poole, P. (eds.) Proceedings of 19th ICAF Symposium, Fatigue in New and Aging Aircraft, Edinburgh, Scotland, 18–20 June 1997, pp. 499–522. EMAS, Warley (1997)Google Scholar
  10. Niu, M.C.Y.: Airframe Structural Design. Practical Information and Data on Airframe Structures. Conmilit Press Ltd., Hong Kong (1988)Google Scholar
  11. Oldersma, A.: Fatigue of riveted joints. A literature survey and statistical analysis of existing test data. Report NLR CR 92401 L. NLR, Amsterdam (1992)Google Scholar
  12. Schijve J.: The fatigue strength of riveted joints and lugs. Technical Memorandum 1935. National Advisory Committee for Aeronautics, Washington, D.C (1956)Google Scholar
  13. Skorupa, M., Skorupa, A., Machniewicz, T., Korbel, A.: Improving the fatigue performance of riveted joints in airframes. Final report on EUREKA project IMPERJA, No. E!3496. University of Science and Technology AGH, Kraków (2011) (in Polish, unpublished results)Google Scholar
  14. Smith, C.R.: Fatigue resistance. Design considerations. Aircr. Eng. 1960, 142–144 (1960)CrossRefGoogle Scholar
  15. Smith, C.R., Lindenau, G.D.: Riveted joints fatigue strength. Reprint from Fatigue of Aircraft Structures. ASTM STP 203, pp. 10–25. ASTM, Philadelphia (1957)Google Scholar
  16. Vlieger, H.: Results of uniaxial and biaxial tests on riveted fuselage lap joint specimens. In: Harris, Ch.E (1994) 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. 911–930 (1994)Google Scholar

Copyright information

© Springer Science+Business Media Dordrecht 2012

Authors and Affiliations

  • Andrzej Skorupa
    • 1
  • Małgorzata Skorupa
    • 1
  1. 1.Faculty of Mechanical Engineering and RoboticsAGH University of Science and TechnologyKrakówPoland

Personalised recommendations