Typical fatigue-initiating discontinuities in metallic aircraft structures
Source abstract
Abstract
Abstract A fatigue lifing framework using a lead crack concept, based on years of detailed inspection and analysis of fatigue cracks in many specimens and airframe components, has been developed by the DSTO for metallic primary airframe components. This framework is an important additional tool for determining aircraft component fatigue lives in the Royal Australian Air Force fleet. Like the original Damage Tolerance concept, developed by the United States Air Force, this framework assumes that fatigue cracking begins as soon as an aircraft enters service. However, there are major and fundamental differences. Instead of assuming initial crack sizes and deriving early crack growth behaviour from back-extrapolation of growth data for long cracks, the framework uses data for real cracks growing from small discontinuities inherent to the material and the production of the component. To this end, this paper examines the types of discontinuities that initiate fatigue cracks in typical metallic airframe structures. These discontinuities and the fatigue cracks that have grown from them are taken from coupon, component and full-scale tests, and also from service aircraft, including commercial transport aircraft and high performance military aircraft.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Fatigue and fracture mechanics · Mechanical Failure Analysis and Simulation · Probabilistic and Robust Engineering Design
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (46)
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1. Molent L, Barter SA, Wanhill RJH. The lead crack fatigue lifing framework, DSTO-RR-0353, Defence Science and Technology Organisation, Melbourne, Australia; 2010.
2. Athiniotis N, Barter SA, Clark G. Summary of fatigue cracking in RAAF Macchi MB326H wings, DSTO Technical Report DSTO-TR-0757, Defence Science and Technology Organisation, Melbourne, Australia; 1999.
3. Wanhill RJH, Platenkamp DJ, Hattenberg T, Bosch AF, De Haan PH. GLARE teardowns from the MegaLiner Barrel (MLB) fatigue test, NLR Technical Publication NLR-TP-2009-068, National Aerospace Laboratory NLR, Amsterdam, the Netherlands, 2009. In: Bos MJ, editors. ICAF 2009: Bridging the Gap between Theory and Operational Practice, Springer Netherlands, Dordrecht, the Netherlands, 2009, p. 145–67.
4. Burgess PJ. Extending the life of the RAAF Macchi jet trainer – selection of the Durability and Damage Tolerance philosophy, Australian Aviation Symposium, Canberra, Australia; 1987.
5. Goldsmith NT, Clark G. Analysis of wing main spar cracking. In: Esakul KA, editors. Handbook of Case Histories in Failure Analysis, ASM International, Metals Park, Ohio, USA, 1, 1992. p. 9–11.10.31399/asm.fach.v01.c9001021 ↗
6. Huynh J, Molent L, Barter SA. Predictions for 7050 aluminium alloy with different stress concentration factors, DSTO Research Report DSTO-RR-0330, Defence Science and Technology Organisation, Melbourne, Australia; 2007.
7. Hartley D. Australian P-3C empennage fatigue test summary of teardown activities and findings, DSTO Technical Report DSTO-TR-1618, Defence Science and Technology Organisation, Melbourne, Australia; 2004.
8. Huynh J, Barter SA. Fatigue crack growth in 7050-T7451 aluminium alloy notched coupons, DSTO Technical Report DSTO-TR-1966, Defence Science and Technology Organisation, Melbourne, Australia; 2007.
9. Molent L, Dixon B, Barter S, White P, Mills T, Maxfield K, et al., Enhanced teardown of ex-service F/A-18A/B/C/D centre fuselages. In: Bos MJ, editors. ICAF 2009: Bridging the Gap between Theory and Operational Practice, Springer, Netherlands, Dordrecht, the Netherlands; 2009. p. 123–42.10.1007/978-90-481-2746-7_8 ↗
10. Barter SA. Investigation of a JAL 747 wing main landing gear trunnion failure, DSTO Contract Report DSTO-CR-2005-0104, Defence Science and Technology Organisation, Melbourne, Australia; 2005.
11. Goldsmith NT, Everard P, Capraro B, Byrnes R. Fractographic examinations of F-111 wing A15-5, DSTO Defence Publication DSTO-DP-00986, Defence Science and Technology Organisation, Melbourne, Australia; 2004.
12. Barter SA. Fatigue crack growth in 7050T7451 aluminium alloy thick section plate with a glass bead peened surface simulating some regions of the F/A-18 structure, DSTO Technical Report DSTO-TR-1477, Defence Science and Technology Organisation, Melbourne, Australia; 2003.
13. Analysis and prediction of microstructural effects on long-term fatigue performance of an aluminium aerospace alloy10.1016/S0142-1123(97)00044-3 ↗
14. Barter SA. Fatigue crack growth in several 7050T7451 aluminium alloy thick section plates with aircraft manufacturer’s and laboratory surface finishes representing some regions of the F/A-18 structure, DSTO Technical Report DSTO-TR-1539, Defence Science and Technology Organisation, Melbourne, Australia; 2003.
15. Krieser R, Molent L, editors. A record of the Australian Mirage wing fatigue test, DSTO Technical Report DSTO-TR-1561, Defence Science and Technology Organisation, Melbourne, Australia; 2004.
16. Bathias C. Designing components against gigacycle fatigue. In: Stanzl-Tschegg SE, Mayer HM, editors. Proc of the Int Conference on Fatigue in the Very High Cycle Regime, Institute of Meteorology and Physics, University of Agricultural Sciences, Vienna, Austria, 2001. p. 97–109.
17. Einfluß von Kugelstrahlen und Bohrungsaufweitung auf das Ermüdungsverhalten von AlZnMgCu-Proben
18. Hunter MS, Fricke WG, Jr. Metallographic aspects of fatigue behavior of aluminum. In: Proc, ASTM, 54, 1954. p. 717–32.
19. Grosskreutz JC, Shaw GG. Mechanisms of fatigue in 1100-0 and 2024-T4 aluminum, Air Force Materials Laboratory Technical Report AFML-TR-65-127, Wright-Patterson Air Force Base, Dayton, Ohio, USA; 1965.
20. Grosskreutz JC, Shaw GG, Benson DK. The effect of inclusion size and distribution on fatigue of 2024-T4 aluminum, Air Force Materials Laboratory Technical Report AFML-TR-69-121, Wright-Patterson Air Force Base, Dayton, Ohio, USA; 1969.
21. Critical mechanisms in the development of fatigue cracks in 2024-T4 aluminum
22. Finney JM. The relationship between aged structure and the fatigue behaviour of aluminium alloys. Part II: experimental results of aluminium–copper–magnesium alloys, Aeronautical Research Laboratories Structures and Materials Report 325, Melbourne, Australia; 1969.
23. Forsyth PJE. The metallurgical aspects of fatigue and fracture toughness, Metallurgical Aspects of Fatigue and Fracture Toughness, AGARD Report No. 610, Advisory Group for Aerospace Research and Development, Neuilly-sur-Seine, France; 1973. p. 1-1–1-22.
24. Lütjering G, Döker H, Munz D. Microstructure and fatigue behavior of Al-alloys. In: Proc of the Third Int Conference on the Strength of Metals and Alloys, Inst of Metals, London, UK; 1973. p. 427–31.
25. Fatigue-crack initiation and microcrack growth in 2024-T4 and 2124-T4 aluminum alloys10.1007/BF02658324 ↗
26. Metallography of fatigue crack initiation in an overaged high-strength aluminium alloy10.1007/BF02644299 ↗
27. Newman Jr. JC, Edwards PR. Short-crack growth behaviour in an aluminum alloy – an AGARD cooperative test programme, AGARD Report No. 732, Advisory Group for Aerospace Research and Development, Neuilly-sur-Seine, France; 1988.
28. Wanhill RJH. Damage tolerance engineering property evaluations of aerospace aluminium alloys with emphasis on fatigue crack growth, NLR Technical Publication TP 94177, National Aerospace Laboratory NLR, Amsterdam, the Netherlands; 1995.
29. Initiation and early growth of fatigue cracks in an aerospace aluminium alloy10.1046/j.1460-2695.2002.00482.x ↗
30. A study of nucleation and fatigue behaviour of an aerospace aluminum alloy 2024-T310.1016/j.ijfatigue.2004.06.010 ↗
31. Observations of fatigue crack initiation in 7075-T65110.1016/j.ijfatigue.2009.06.003 ↗
32. Staley JT. Microstructure and toughness of high-strength aluminum alloys, Properties Related to Fracture Toughness, ASTM STP 605, American Society for Testing and Materials, Philadelphia, Pennsylvania, USA; 1976, p. 71–103.10.1520/STP27801S ↗
33. Kaufman JG. Design of aluminum alloys for high toughness and high fatigue strength, Specialists Meeting on Alloy Design for Fatigue and Fracture Toughness, AGARD Conference Proc. No. 185, Advisory Group for Aerospace Research and Development, Neuilly-sur-Seine, France; 1976. p. 2-1–2-26.
34. George RW, Forsyth PJE. The influence of nickel and manganese on the fatigue properties and microstructures of three Al–Mg–Zn alloys, Royal Aircraft Establishment Technical Note No. Met. Phys. 352, Farnborough, UK; 1962.
35. Böhmer M. Die Beeinflussung des Ermüdungsverhaltens einer Aluminiumlegierung durch den Druck der Luft und ihrer Bestandteile zwischen 760 und 10-7 Torr, Deutsche Luft- und Raumfahrt Forschungsbericht 74-19, Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt Institut für Werkstoff-Forschung, Porz-Wahn, Germany; 1974.
36. The effect of environment on fatigue crack growth in aluminium and some aluminium alloys
37. Effect of vacuum on the fatigue life of aluminum10.1016/0001-6160(66)90093-9 ↗
38. Fatigue behavior of aluminum in vacuum10.1016/0001-6160(66)90234-3 ↗
39. Beitel GA. An ultrasonic device for the study of fatigue crack initiation in anodized aluminum alloys. In: Devereux OF, McEvily AJ, Staehle RW, editors. Corrosion Fatigue: Chemistry, Mechanics and Microstructure, National Association of Corrosion Engineers, Houston, Texas, USA; 1972. p. 512–7.
40. Fatigue behavior and crack propagation in 2024-T3 aluminum alloy in ultrahigh vacuum and air
41. Atmospheric action as a factor in fatigue of metals
42. The effect of atmospheric corrosion on metal fatigue10.1080/14786435808237045 ↗
43. Broom T, Nicholson A. Atmospheric corrosion-fatigue of age-hardened aluminium alloys. J Inst Metals 1960–61;89:183–90.
44. The nature of fatigue-crack propagation in air and vacuum for 2024 aluminum
45. The influence of gaseous environment and fatigue frequency on the growth of fatigue cracks in some aluminum alloys10.1007/BF00190956 ↗
46. Fractography of fatigue crack propagation in 2024-T3 and 7075-T6 aluminum alloys in air and vacuum10.1007/BF02641972 ↗