The Prediction of Crack Growth Rates From Total Endurances in High Strain Fatigue

Skelton, R. P.

doi:10.1111/j.1460-2695.1979.tb01089.x

Cited by 17 publications

(9 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…2 it can be seen that in 1Cr-Mo-V creep damage will cause failure well before fatigue, and, in fact, the calculated life in terms of fatigue only is nearly twenty times greater than the observed endurance. Thus a "creep dominated" failure results under these conditions, and consequently, the use of a fatigue-based predictive expression such as that of Skelton [19], which is in error by an order of magnitude, is not feasible. The situation for Type 316, however, is completely different (Fig.…”

Section: Experimentally Observed Conditions For Fatigue and Creep Dommentioning

confidence: 99%

The Importance of Failure Mode in Fatigue–creep Interactions

Plumbridge

Dean²,

Miller³

1982

Fatigue Fract Eng Mat Struct

View full text Add to dashboard Cite

The present work emphasizes the need to understand the processes involved in fatiguexreep interactions before reliable life predictions may be sensibly made. In particular, the simultaneous interaction involving a strain controlled cycle with a dwell period at maximum tensile strain is analysed and the accumulation of fatigue-creep damage computed in terms of strain range, extent of dwell and microstructure. Dominant failure modes are thus identified and the findings are used to explain the apparently different failure mechanisms previously reported for a 1Cr-Mo-V alloy steel and a Type 316 stainless steel. Due to lack of data overall mapping of regimes of dominance is not possible, but in cases where a single mechanism prevails throughout the duration of dwell accurate lifetime prediction may be achieved.

show abstract

Section: Experimentally Observed Conditions For Fatigue and Creep Dommentioning

confidence: 99%

The Importance of Failure Mode in Fatigue–creep Interactions

Plumbridge

Dean²,

Miller³

1982

Fatigue Fract Eng Mat Struct

View full text Add to dashboard Cite

show abstract

“…Two important articles in the area were published in 1979 by Skelton [110] and Wanhill [111]. Skelton [107] proposed a method to be used for fatigue crack growth subjected to high strain and Wanhill [108] published a study of fatigue crack propagation tested on a flight simulation. [116] introduced the approximation of time-dependent crack size using a Markov process.…”

Section: Fracture and Fatiguementioning

confidence: 99%

Probabilistic Analysis of a Thin-Walled Beam with a Crack

Kunaporn¹,

Singh²,

Patil³

et al. 2010

51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

0
0
0
0

View full text Add to dashboard Cite

Probabilistic Analysis of a Thin-walled Beam with a CrackChalitphan Kunaporn (ABSTRACT) It is reasonable to assume that an aircraft might experience some in-flight discrete source damage caused by various incidents. It is, thus, necessary to evaluate the impact of such damage on the performance of the aircraft. This study is focused on evaluating the effect of a simple discrete damage in an aircraft wing on its static and dynamic response.The damaged wing is modeled by a thin-walled beam with a longitudinal crack the response of which can be obtained analytically. As uncertainties are present in the location and size of the crack as well as in the applied loads, their effects are incorporated into the framework consisting of structural response, crack propagation and aeroelasticity.The first objective of this study is to examine the effect of damage represented by a crack on the wing flexibility that influences its deformation and aero-elastic divergence characteristics. To study this, the thin-walled beam is modeled by Benscoter thin-walled beam theory combined with Gunnlaugsson and Pedersen compatibility conditions to accurately account for the discontinuity at the interface of the cracked and uncracked beam segments. Instead of conducting a detailed finite element analysis, the solution is obtained in an exact sense for general distributed loads representing the wind pressure effects. This analytical approach is shown to provide very accurate values for the global beam response compared with the detailed finite element shell analysis. This analytical solution is, then, used to study the beam response probabilistically. The crack location and size are assumed to be uncertain and are, thus, characterized by random variable. For a specified limit state, the probability of failure can be conveniently calculated by the first order second moment analysis using the safety index approach. The same analytical solution is also used to study the aero-elastic divergence characteristics of a wing, the inner structure of which is represented by a thin-walled beam with a crack of uncertain size and position along the beam.iii The second objective of this study is to examine the time growth of a crack under dynamic gust type of loading to which a wing is likely to be exposed during flight.Damage propagating during operation further deteriorates the safety of the aircraft and it is necessary to study its time growth so that its impact on the performance can be evaluated before it reaches its unstable state. The proposed framework for the crack growth analysis is based on classical fracture mechanics where the remaining flight time is obtained by Monte Carlo simulation in which various uncertainties are taken into account. To obtain equivalent cyclic loading required for crack growth analysis, random vibration analysis of the thin-walled beam is conducted for stochastic wind load defined by a gust load spectral density function. The probability of failure represented by the crack size approaching the critical crack size wit...

show abstract

“…Skelton [65] developed a FCG approach dubbed the plastic strain range-based growth law, which effectively modifies the Coffin-Manson Law. Wareing [66] modified the Paris Law for FCG through a cavitated material, as induced by creep.…”

Section: Nonlinear Fracture Mechanicsmentioning
confidence: 99%

Stress Intensity Solutions of Thermally Induced Cracks in Combustor Liner Hot Spots Using Finite Element Analysis (FEA)
Rhymer¹
2005
0
0
0
0
View full text Add to dashboard Cite

The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS.

show abstract

The Prediction of Crack Growth Rates From Total Endurances in High Strain Fatigue

Cited by 17 publications

References 28 publications

The Importance of Failure Mode in Fatigue–creep Interactions

The Importance of Failure Mode in Fatigue–creep Interactions

Probabilistic Analysis of a Thin-Walled Beam with a Crack

Stress Intensity Solutions of Thermally Induced Cracks in Combustor Liner Hot Spots Using Finite Element Analysis (FEA)

Contact Info

Product

Resources

About