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Schra, L. (author), Wanhill, R.J.H. (author)In 1991 a simple automated stress corrosion testing method called the ASCOR (Automated Stress corrosion Ring) test was developed to test aluminium alloys according to ASTM specification G49. The present investigation concentrated on evaluating two aspects of the test method: The SCC initiation criterion (2 % load decrease). The possibility of...report 1997
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Wanhill, R.J.H. (author)The opportunities for sustained load fracture control in spacecraft are indicated. Emphasis is given to verification by small-scale laboratory testing.report 1989
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Schra, L. (author), Wanhill, R.J.H. (author)Flight simulation fatigue growth tests were done on 1.6 mm thick sheets of the damage tolerant aluminium-lithium (Al-Li) alloys 2091-T84 and 8090-T81 in comparison with the industry standard conventional damage tolerant alloy 2024-T3. The flight simulation load spectrum, the gust spectrum MINITWIST, was used in four versions: untruncated,...report 1991
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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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Wanhill, R.J.H. (author)This report contains the overhead sheets of a short course on fatigue and fracture of aerospace aluminium alloys, plus an annex in the form of a review paper.report 1994
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Wanhill, R.J.H. (author), Looije, C.E.W. (author)The constant amplitude and flight simulation (TURBISTAN) fatigue crack growth behaviour of Ti-6A1-4V fan disc forgings tested in the AGARD engine disc cooperative test programme was investigated by fractographic and microstructural analysis. The crack growth curve shapes and fractographic characteristics were similar. Transitions in the fatigue...report 1991
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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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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), Schra, L. (author)An investigation was made of the effect of starter notch geometry on flight simulation fatigue crack growth in three damage tolerant aluminium sheet alloys, 2024-T3, 2091-T84 and 8090-T81. Changing the starter notch geometry resulted in significant differences in initial nonstabilized fatigue crack growth behaviour. However, there was only a...report 1995
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Wanhill, R.J.H. (author), Koolloos, M.F.J. (author)Aircraft structures are susceptible to fatigue and corrosion damage, notably at joints. There may be interactions between fatigue and corrosion, especially as aircraft age. Longitudinal lap splices from several types of transport aircraft pressure cabins were disassembled and investigated for Multiple Site Damage (MSD) fatigue cracking and...report 2000
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Wanhill, R.J.H. (author), Galatolo, R. (author), Looije, C.E.W. (author)The constant amplitude fatigue crack growth behaviour of a conventionally (alpha ß) solution treated and aged Ti-6A1-4V fan disc forging was examined by fractographlc and microstructural analysis. The crack growth process was complex with many Interrelated fracture features. A transition in the fatigue crack growth curve correlated with a change...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)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), Schra, L. (author), 't Hart, W.G.J. (author)New impetus to continued use of alximinium alloys in major structural areas of aircraft has been given by the development of aluminium-lithium alloys. However, qualification of these new materials for service requires extensive testing and evaluation, preferably in international cooperative programmes. The evaluation of aluminium-lithium alloys...report 1989
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Wanhill, R.J.H. (author)Sustained load fracture control is a problem of particular importance for manned spacecraft and orbital stations, owing to the long design lives and limited opportunities for repair. The current ESA approach Is based on screening out materials shown to be susceptible to stress corrosion cracking (SCC) from smooth specimen tests. This approach...report 1991
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Wanhill, R.J.H. (author)Flight simulation fatigu-e crack propagation tests were carried out on 2024-T3, 7475-T761 and mill annealed Ti-6A1-4V sheet in thicknesses up to 3 miri and representative for transport aircraft lower wing skin stiffened panels of end load capacities 1.5 and 3 MN/m. The performance of 2024-T3 was much superior, owing mainly to greater retardation...report 1977
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Wanhill, R.J.H. (author)Flight simulation fatigue crack growth tests are necessary for verification of aircraft damage tolerance analyses and crack growth prediction methods, and also for comparing candidate materials for aircraft structural applications. However, such tests involve complicating issues that have emerged from many investigations on aluminium alloys...report 1993
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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), Mom, A.J.A. (author), Hersbach, H.J.C. (author), Kool, G.A. (author), Boogers, J.A.M. (author)The NLR has two high velocity burner rigs for oxidation and hot corrosion testing. A large, custom-built rig was commissioned in 1977 to enable actual components to be tested. A smaller rig for specimen testing was purchased in 1986. Experience with these rigs over the last decade is reviewed.report 1989
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- Wanhill, R.J.H. (author) report 1993