Cycle sequence sensitivity of near threshold fatigue under programmed loading – A fractographic study
Source abstract
Abstract
Abstract Statistically representative programmed block renditions of a transport aircraft wing load spectrum were used to study cycle sequence effects on near-threshold fatigue crack growth rate. Less frequent higher load cycles served as markers that permitted unambiguous estimation of crack growth rate under individual load levels in the load spectrum. Small cycle crack growth rates down to threshold levels are extremely sensitive to the peak-valley sequence of preceding large load cycle, suggesting the need to model the effect of near-tip residual stress on threshold stress intensity in handling load spectra with a large statistical content of smaller load cycles.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Fatigue and fracture mechanics · Probabilistic and Robust Engineering Design · Material Properties and Failure Mechanisms
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (32)
Show source-provided references
1. Strength experiments under cyclic loading in aircraft structures
2. Die Lebensdauer von Kugellagern
3. Cumulative damage in fatigue10.1115/1.4009458 ↗
4. C.M. Hudson, H.F. Hardrath, Effect of changing stress amplitude on the rate of fatigue-crack propagation in two aluminium alloys. NASA TN D-960 (September 1961).
5. Schijve J. Observations on the prediction of fatigue crack propagation under variable-amplitude loading. Fatigue Crack Growth under Spectrum Loads, ASTM STP 595; 1976:3–23.10.1520/STP33360S ↗
6. Newman JC. A crack-closure model for predicting fatigue crack growth under aircraft spectrum loading. In: Chang JB, Hudson CM, editors. Methods and Models for Predicting Fatigue Crack Growth under Random Loading. ASTM STP 748; 1981. p. 53–84.10.1520/STP28334S ↗
7. Wheeler · J Basic Eng, Trans ASME · 1972 · 18110.1115/1.3425362 ↗
8. Willenborg JD, Engle RM, Wood HA. A Crack Growth Retardation Model Using an Effective Stress Concept, AFFDL-TM-FBR-71-1. Air Force Flight Dynamics Laboratory; 1971.10.21236/ADA956517 ↗
9. Nishida · 1991
10. van der Linden HH. Modifications of flight-by-flight load sequences to provide for good fracture surface readability. In: Fatigue crack topography. AGARD conference proceedings, vol. 376; 1984.
11. Dainty RV. The use of ‘marker-loads’ as an aid in quantitative fractography in full-scale aircraft fatigue testing – a case study. Technical Report LTR-ST-1374. National Research Council, Canada; May 1982.
12. Barter SA, Molent L, Wanhill RJH., Marker loads for quantitatve fractography of fatigue cracks in aerospace alloys. In: Proc. 25th ICAF Symposium, Rotterdam, 27–29 May 2009.10.1007/978-90-481-2746-7_2 ↗
13. Binary coded event registration on fatigue fracture surfaces
14. Observations of crack path changes caused by periodic underloads in AA7050-T745110.1016/j.ijfatigue.2007.08.021 ↗
15. Fatigue crack growth under an equivalent FALSTAFF spectrum10.1111/j.1460-2695.1995.tb01419.x ↗
16. Laird · 1978 · 149
17. Crack extension by alternating shear10.1016/0013-7944(70)90008-1 ↗
18. Fatigue crack growth as a consequence of environment-enhanced brittle-micro fracture10.1111/j.1460-2695.2005.00857.x ↗
19. Fatigue voids and their significance10.1046/j.1460-2695.2002.00565.x ↗
20. van Dijk GM, de Jonge JB. Introduction to a Fighter Aircraft Loading Standard for Fatigue Evaluation “FALSTAFF”. National Aerospace Laboratories Report NLR MP 75017U, Amsterdam; 1975.
21. de Jonge JB, Schutz D, Lowak H, Schijve J. A standardized load sequence for flight simulation tests on transport aircraft wing structures, LBF Report LBF-BERICHT FB-106, NLR Report NLR TR 73029 U, Darmstadt – Amsterdam; 1973.
22. Mom AJA, Evans WJ, ten Have AA. TURBISTAN, A Standard Load Sequence for Aircraft Engine Discs, National Aerospace Laboratory Report NLR MP 85033U, Amsterdam; 1985.
23. Edwards PR, Darts J. Standardised Fatigue Loading Sequences for Helicopter Rotors HELIX and FELIX, National Aerospace Laboratory Report NLR TR 84043U Parts 1&2, Amsterdam; 1984.
24. ten Have AA. WISPER and WISPERX, Final Definition of Two Standardised Fatigue Loading Sequences for Wind Turbine Blades, National Aerospace Laboratory Report NLR TP 91476U, Amsterdam; 1991.
25. Sunder R. Contribution of individual load cycles to fatigue crack growth under aircraft spectrum loading, Eds. MR Mitchell and RW Landgraf, ASTM STP 1122; 1992:176–190.10.1520/STP24159S ↗
26. de Jonge JB, Vink WJ. Gust load conditions for fatigue tests based on a continuous gust concept, NRL TP 97015, National Aerospace Laboratory NLR; 1997.10.2514/6.1997-1279 ↗
27. On the hysteretic nature of variable-amplitude fatigue crack growth10.1016/j.ijfatigue.2005.06.030 ↗
28. Unraveling the science of variable amplitude fatigue10.1520/JAI103940 ↗
29. Characterization of threshold stress intensity as a function of near-tip residual stress: theory, experiment, and applications10.1520/MPC20140037 ↗
30. Synergy of crack closure, near-tip residual stress and crack-tip blunting in crack growth under periodic overloads – a fractographic study10.1016/j.ijfatigue.2016.08.004 ↗
31. A Fractographic study of load-sequence-induced mixed-mode fatigue crack growth in an Al-Cu alloy
32. Toward improved modeling of variable-amplitude fatigue crack growth—theory and fractographic validation