Searched for: subject:"Aluminum%5C+alloy"
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document
Biglari, M.H. (author), Brakman, C.M. (author), Mittemeijer, E.J. (author), Van der Zwaag, S. (author)
conference paper 1993
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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
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Schra, L. (author), Huisman, H.N. (author)
An experimental investigation was carried out into the applicability of various corrosive environments for stress corrosion crack initiation testing of high strength aluminium alloys using constant strain loaded tuning fork type specimens. The effect of surface preparation was also involved. The most important findings were that salt-chromate...
report 1981
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't Hart, W.G.J. (author), Schra, L. (author)
The Al-Zn-Mg-Cu alloy 7050 produced by Alcoa is a typical plate and forging alloy because of its low quench sensitivity. In order to compare this alloy with the earlier tested plate alloy 7010 an experimental programme was performed involving tensile, fracture toughness, and fatigue testing. In addition stress corrosion crack initiation and...
report 1980
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't Hart, W.G.J. (author), Nederveen, A. (author)
Constant amplitude and flight simulation fatigue tests have been carried out on sulphuric acid, chromic acid and phosphoric acid anodized specimens. A comparison was made with the fatigue behaviour of bare sheet material. Before fatigue testing the fracture strain of the anodic layers was determined.
report 1980
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Lameris, J. (author)
Fracture toughness measurements were carried out to test the ageing behaviour of three adhesives in different environments. It was possible to compare and evaluate adhesives and surface pretreatments. It is doubtful whether the derived R-curves could be used for residual strength calculations in certain environments. Phosphoric acid anodizing...
report 1978
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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
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Schijve, J. (author), Jacobs, F.A. (author), Tromp, P.J. (author)
Flight-simulation tests based on a standardized gust load spectrum were carried out in normal air, very dry air and salt water. Specimen thicknesses were t = 2 mm and t = 10 mm, mean stress in flight was 70 or 55 MN/m². In all cases a significant effect of the environment was found. Fatigue lives for t = 10 ram were much shorter than for t = 2...
report 1976
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Wanhill, R.J.H. (author), Schra, L. (author)
The effects of flat to slant fracture transitions on flight simulation fatigue crack propagation in specimens of 7O5O aluminium alloy forgings are discussed. For specimens containing flat, shearlipped, or full slant fractures at similar crack lengths the crack resistance (R curve) approach appears to provide an explanation for differences in the...
report 1976
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't Hart, W.G.J. (author)
Residual strength tests have heen performed, on 300 mm wide centrecracked panels of various thicknesses, at room temperature and at -50 C. During the tests, stable crack growth was filmed and recorded with the electric potential method. Fracture toughness was determined using the method of Feddersen.
report 1976
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Hartman, A. (author)
SEN specimens of 70T5 alloy loaded in bending have been used to determine time to failure and the crack propagation rate as a function of K, the stress intensity factor, and of the electrical potential in 3 wt % aqueous solutions of NaCl, NaBr and Nal with p values of 3 and 7. The SC tests were supplemented by potentio-kinetic polarization tests...
report 1976
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Vlieger, H. (author), Sanderse, A. (author)
This report gives a detailed description of the computer program ARREST and of the execution of it in determining the residual strength diagram of cracked stiffened panels. The essentials of the computer program are dealt with in chapters 1 through 5, whereas the derivation of the equations together with the program flow charts ajid the program...
report 1975
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't Hart, W.G.J. (author), Nederveen, A. (author), Nassette, J.H. (author), van Wijk, A. (author)
The influence of previous corrosion on fatigue crack initiation has been determined. Cylindrical specimens and flat specimens with a central hole of the aluminium alloy T075-T6 were corroded in a 3.5 % NaC1 solution. The cylindrical specimens were tested under constant amplitude loading while for the specimens with a central hole a block...
report 1975
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