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- De Borst, R. (author) journal article 1987
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Moss, A.C. (author), 't Hart, W.G.J. (author)This investigation examined carbon/epoxy and aramide/epoxy composites in interlaminar shear and in open-hole tensile tests at 90 to the unidirectional fibre orientation. Epoxy resin was also tested under tension. Photomicroscopy and the S.E.M. were used to study the fracture surfaces. Wet tests were performed to investigate the influence of...report 1986
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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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Komorowski, J.P. (author)This report is the first in a series of literature reviews in which hygrothermal effects on aerospace composite materials (CM) are examined. This first report (Part I) deals primarily with fundamental aspects of the diffusion of moisture into, and from, composite materials. The effects of temperature under both steady state and transient...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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de Jonge, J.B. (author)The report starts with a general review of the loading of transport aircraft fuselages and the consequent fuselage skin stresses Taking the F-28 fuselage as an example, the potential weight savings that can be obtained by using ARALL as skin material are assessed. The report ends with conclusions and recommendationsreport 1982
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't Hart, W.G.J. (author)An experimental investigation was performed to examine the effect of low energy impact damage on tension-compression fatigue properties of sandwich panels. The specimens consisted of a 9 mm thick Nomex honeycomb and face sheets of (0,± 45) and (± 45,0) Carbon/epoxy. Drop weight impact was applied to create internal laminate damage. In order to...report 1981
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de Graaf, E.A.B. (author), Rienks, K.J. (author), van Dreumel, W.H.M. (author)The present report describes the X-ray radiography and subsequent destructive investigation according to metallographic techniques of specimens that were taken from experimental mixed—laminate test panels. Clues for the interpretation of radiopraphs of carbon fibre reinforced composites are given.report 1980
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- van den Assem, D. (author), Daniels, D.H.W. (author) report 1978
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Wanhill, R.J.H. (author)Flight simulation fatigue crack propagation tests with gust spectrum loading were carried out on 2024-T3/carbon-epoxy, 7475-T76l/carbon-epoxy and Ti-6Al-4V/carbon-epoxy laminates with nominal weight savings of -30% as compared to equivalent 2024-T3 panels. The performance of the 2024-T3/carbon-epoxy laminates was much superior to those of the...report 1978
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- Bartelds, G. (author) report 1978
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't Hart, W.G.J. (author)Residual strength tests have been carried out on various Kevlar 49-Carbon epoxy laminate configurations consisting of a carbon/epoxy core with face sheets of Kevlar 49 fabric. The influence of fatigue loading of notched specimens on the residual strength was investigated.report 1978
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- 't Hart, W.G.J. (author) report 1977
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Wanhill, R.J.H. (author)Plight simulation fatigue crack propagation tests with gust spectrum loading were carried out on 2024-T3/carbon-epoxy, 7475-T761/carbon-epoxy and Ti-6Al-4V/carbon-epoxy laminates with nominal weight savings of 30% as compared to equivalent 2024-T3 panels. The performance of the 2024-T3/ carbon-epoxy laminates was much superior to those of the...report 1977
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- van der Assem, D. (author), Daniels, D.H.W. (author) report 1977
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't Hart, W.G.J. (author)Fatigue tests on unidirectional Ca/ep composite material have been performed to investigate whether previous fatigue loading did influence the residual static strength. Residual strength tests were carried out on (0, ± 45)2s and (± 45)2s laminates, while for the (O, ± 45)2s laminate the influence of previous tensile fatigue loading on the...report 1977
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Vlieger, H. (author)Residual strength tests were carried out on center-cracked panels with a 2024-T3 or 7075-T6 skin and provided with eccentric stiffeners of practical design. The stiffeners were riveted to the skin. The material of the stiffeners was 7075-T6. In some cases the stiffeners were combined with Ti-alloy crack stoppers. On the basis of the test results...report 1976
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't Hart, W.G.J. (author)A microscopic study has been performed on carbon composite fracture surfaces, using the Scanning Electron Microscope (SEM). It appears that the SEM is a useful tool to examine the fracture surface characteristics of composite materials failing under different loading conditions.report 1976
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- 't Hart, W.G.J. (author), Jacobs, F.A. (author), Nassette, J.H. (author) report 1975
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Bartelds, G. (author), Nederveen, A. (author)Aluminium sandwich paaiels provided with carbon-epoxy uniaxial reinforcing strips were fatigued and subsequently tested for residual strength, Although both analysis ajid fatigue tests indicate that the crack tip zone is affected onlywhen the zone is in the immediate vicinity of a stiffener the reinforcement considerably increases crack...report 1974