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Oldersma, A. (author), Wanhill, R.J.H. (author)
Discussions between D-BAA and the NLR have shown that significant variability in fatigue crack growth properties is possible for the industry standard damage tolerant aluminium alloy, 2024-T3 sheet. This is important for two reasons: (1) design assumptions and (2) comparisons of different candidate materials, such as 6013-T6, with 2024-T3....
report 1996
document
Schra, L. (author), 't Hart, W.G.J. (author), Boogers, J.A.M. (author)
Outdoor corrosion and stress corrosion tests were conducted on Al-Li plate and sheet materials for 3 and almost 5 years respectively. The results can be summarized as follows: Corrosion: Peak aged XXXA-T651 (8090-T651) exhibited greater exfoliation corrosion resistance than 2024-T351 and 2324-T39 plate. 2091-T3 and 2024-T3 sheet were found to be...
report 1990
document
de Koning, A.U. (author)
As an introduction the practical significance of fatigue crack growth life prediction is related to the service life, the inspection period and the fracture control requirements. Then different aspects of fatigue crack growth in metallic materials are discussed in more detail. Important effects such as chemical environment, short cracks, crack...
report 1987
document
de Koning, A.U. (author), Liefting, G. (author)
The crack opening behaviour of a fatigue crack in a centrally cracked panel was studied using a discretised version of the Dugdale and Barenblatt model. The effect of crack growth was also included. Results obtain ed for constant amplitude loading were in agreement with data reported in the open literature. The effect of application of single...
report 1986
document
't Hart, W.G.J. (author)
In this report the results of an impact damage and fatigue investigation are discussed. Comparative impact tests have been carried out on a solid (± 45₂,O ₄)s carbon/epoxy base laminate and the same type of laminate covered with outer layers of glass, aramid or carbon fabric. In addition an Aramid Reinforced Aluminium Laminate (ARALL) was...
report 1985
document
de Koning, A.U. (author)
This study deals with fracture mechanics aspects of mode 1 crack growth under montonically increasing (quasi-static) loads. Using the finite element method stable crack growth and the plastic deformation fields associated with this process are analyzed. A two parameter approach is proposed for a description of initiation and subsequent stable...
report 1985
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Kolkman, H.J. (author)
Differences in the fatigue crack propagation rates of 2024-T351 and 2324-T39 are explicable from differences in microstructures. The slope changes (transitions) in the crack propagation curves are probably associated with the plastic zone sizes being equal to certain microstructural dimensions. As a consequence of different chemical compostion...
report 1985
document
van der Linden, H.H. (author)
The GARTEUR Group of Responsables for Structures and Materials identified the need for an evaluation of fatigue crack propagation models. This resulted in a collaborative GARTEUR activity in which 13 variations of the F-27 transport spectrum were evaluated by 7 institutes and companies using in total 13 crack propagation prediction methods and...
report 1983
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van der Hoeven, W. (author)
The effects of strain rate and temperature on the fracture behaviour of three structural adhesives (Redux 775, Metlbond 328 and EC 2216) were investigated using Double Cantilever Beam specimens. The test results were presented as critical elastic energy release rate data (G) to investigate whether this parameter could be used to characterize me...
report 1983
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Wanhill, R.J.H. (author)
Flight simulation fatigue crack propagation tests with gust spectrum loading were carried out on laminates of (i) aluminium alloy 2024-T3/carbon-epoxy, (ii) aluminium alloy 7475-T761/carbon-epoxy and (iii) titanium alloy Ti-6Al-4V/carbon-epoxy with nominal weight savings of 30% and 40% as compared to equivalent 2024-T3 Alclad and 7475-T761...
report 1982
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Wanhill, R.J.H. (author), Jongebreur, A.A. (author), Morgan, E. (author), Moolhuijsen, E.J. (author)
Flight simulation fatigue crack propagation tests on single and double element lugs made from 2024-T351 and TOT5-TT351 aluminium alloys and Ti-6AJ.-UV titanium alloy were carried out. Initial damage was a throughthickness notch at one side of each hole in one element. Results showed that crack propagation lives for double element lugs were much...
report 1981
document
de Koning, A.U. (author), van der Linden, H.H. (author)
A model for the prediction of growth rates of fatigue cracks in aluminium alloys subjected to service loading conditions is presented. The model is based on an approximate description of the crack opening behaviour and was applied successfully in an analysis of effects of crack growth acceleration and retardation observed experimentally under...
report 1981
document
Schijve, J. (author)
Paper presented at the 16th ICAP Conference, Brussels, 14 and 15 May 1979.
report 1979
document
de Jonge, J.B. (author), Nederveen, A. (author), Tromp, P.J. (author)
Riveted specimens that are considered representative for F-27 type wing structure were subjected to comparative flight simululation test in which the gust load severity and Ground-Air-Ground cycle were systematically varied. The effect of these variations on crack propagation behaviour was studied by means of crack growth tests on 2 mm sheet...
report 1978
document
de Jonge, J.B. (author), Nederveen, A. (author), Tromp, P.J. (author)
Fatigue tests under flight simulation loading were done on simple notched 2024-T3 Alclad sheet specimens. Reduction of the gust load amplitudes resulted in an increase of crack initiation life but hardly influenced crack propagation. Reduction of the overall stress level increased both initiation and crack propagation life. The observed...
report 1978
document
Wanhill, R.J.H. (author)
2024-T3, 2048-T851, 7075-T6 and 7475-T761 aluminium alloy sheets were compared for fatigue crack propagation resistance under manoeuvre spectrum and constant amplitude loading. For manoeuvre spectrum loading 7475-T761 was superior overall, and this superiority is most probably due to superior toughness of this alloy. In more detail, 2024-T3 was...
report 1978
document
Wanhill, R.J.H. (author)
report 1978
document
Wanhill, R.J.H. (author), Döker, H. (author)
report 1977
document
Schra, L. (author), van Leeuwen, H.P. (author)
The influence of previous corrosion on the fatigue life was investigated. It was foimd that a slight corrosive attack could drastically reduce the fatigue life. The damaging effect of corrosion was greater for the alloy AA 7050 than for AZ 74.61. It could be established that fatigue cracks initiated from various corrosion pits. A second series...
report 1977
document
de Rijk, P. (author), Schijve, J. (author)
A second series of exploratory acoustic fatigue tests using a shaker. A second series of exploratory acoustic fatigue tests was carried out, again employing simple specimens mounted on a shaker. Strain measurements were compared with calculations. Crack growth initiated by a central notch was observed. A comparison was made between three types...
report 1977
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