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Wanhill, R.J.H. (author)Over the last 30 years a number of corrosion and environment-assisted fatigue problems have occurred in aircraft operating in the Netherlands. This paper surveys these problems and discusses the major ones with emphasis on the measures taken to alleviate them. This paper has been prepared for the symposium on Environmentally Assisted Fatigue, to...report 1988
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Wanhill, R.J.H. (author), Schijve, J. (author)The current status of flight simulation fatigue crack growth concepts is reviewed. Crack growth models and methods of crack growth prediction are compared with respect to applicability and limitations. Research areas for improvement of crack growth prediction are specified.report 1988
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Wanhill, R.J.H. (author), Schra, L. (author)Constant amplitude low stress Intensity fatigue crack growth for 2024-T3 and 7475-T761 aluminium alloys In laboratory air, sump tank water and synthetic seawater was Investigated. Corrosion fatigue crack grouwt retardation and arrest occurred In both sump tank water and synthetic seawater, resulting In higher AKth values than In air. Crack...report 1987
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Wanhill, R.J.H. (author)Constant amplitude fatigue crack growth properties of five batches of aluminium alloy 2024 in the naturally aged T3 and T351 conditions are compared. Particular attention is paid to crack growth curve transitions in the near-threshold regime. These transitions correspond to monotonie or cyclic plane strain plastic zone dimensions becoming equal...report 1987
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Wanhill, R.J.H. (author)Over the last 20 years there have been many corrosion-related problems with aircraft operating in the Netherlands. This paper discusses the main problems so far encountered and the measures to alleviate them.report 1986
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Wanhill, R.J.H. (author)This paper has been prepared for presentation at the 15th ICAS Congress, London, September 1986report 1986
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't Hart, W.G.J. (author), Wanhill, R.J.H. (author)Environmental conditions in Europe are conducive to corrosion attack of aircraft structures. In military aircraft corrosion problems occur especially at countersunk fastener holes. The corrosion is generally removed by grinding. A limited amount of material removal is specified by the aircraft manufacturers, but it is sometimes necessary to...report 1986
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Wanhill, R.J.H. (author), de Luccia, J.J. (author)An overview is given of the AGARD-coordinated Fatigue in Aircraft Corrosion Testing (FACT) programme. This long-running programme can be traced back to the fall of 1976 and is due to finish in 1986. Milestones in the programme are discussed in some detail and the results are summarised. Conclusions are drawn both with respect to the setting up...report 1986
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Wanhill, R.J.H. (author)Stress corrosion cracking in high strength aluminium alloy aerospace components is discussed with particular reference to problems in older aircraft and the feasibility of continued service for components containing short cracks.report 1986
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't Hart, W.G.J. (author), Kolkman, H.J. (author), Schra, L. (author), Wanhill, R.J.H. (author)Engineering properties of the recently developed plate alloy 2324-T39 and the conventional alloy 2024-T351 are compared. Some results for the aluminium-lithium alloy DTD XXXA-T651 (Aluminium Association designation 8090) are also included. The strengths of 2324-T39 and DTD XXXA-T651 were comparable and significantly higher than that of 2024-T351...report 1985
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- Wanhill, R.J.H. (author) report 1985
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Wanhill, R.J.H. (author)The effects of cladding and anodising on flight simulation (gust spectrum) fatigue of notched specimens and riveted lap joints of 2024-T3 and 7475-T761 aluminium alloy sheet were investigated. Stress levels were chosen to provide long life data for bare alloy specimens. Cladding and anodising had very large effects on the fatigue lives. Cladding...report 1985
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Wanhill, R.J.H. (author), Schra, L. (author)Engineering properties of the PM alloy 7091-T7E69 and the IM alloys 7075-T73, 7175-T736, 7010-T736 and 7050-T736 were compared. The properties considered were strength, fracture toughness, fatigue strength, fatigue crack propagation resistance under constant amplitude and spectrum loading, stress corrosion crack initiation and propagation...report 1983
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Wanhill, R.J.H. (author)An overview of the fatigue and fracture toughness properties of technical aluminium alloys is given.report 1982
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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
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Schra, L. (author), Wanhill, R.J.H. (author)An extensive programme of notched fatigue testing of aluminium forging alloys has shown that the data result in two basic forms of S-N curve. Analytical approaches to constructing the S-N curves were less satisfactory than fitting the curves freehand. Since freehand curve fitting m\ist involve an element of subjectivity, guidelines for...report 1980
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Wanhill, R.J.H. (author)Flight simulation fatigue crack propagation tests on 202U-T3 and 7475-T761 aluminum alloy sheet were carried out using a gust spectrum representative of the load history of an under wing skin in a transport aircraft. The investigation included tests at several design stress levels and in environments of laboratory air and air plus water spray....report 1980
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Wanhill, R.J.H. (author), 't Hart, W.G.J. (author), Schra, L. (author)The fatigue crack propagation resistances of 7010-T7651, 7010-T73651 and 7075-T7351 thick plate were compared for flight simulation (gust spectrum) loading conditions. 7075-T7351 was slightly superior, and it was shown that this superiority was not essentially due to the higher fracture toughness of this alloy. The influence of specimen...report 1979
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- Wanhill, R.J.H. (author), de Graaf, E.A.B. (author), Delil, A.A.M. (author) report 1979