Searched for: subject%3A%22carbon%22
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document
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
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't Hart, W.G.J. (author), Jacobs, F.A. (author), Nassette, J.H. (author)
report 1975
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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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van der Assem, D. (author), Daniels, D.H.W. (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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'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
document
Bartelds, G. (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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van den Assem, D. (author), Daniels, D.H.W. (author)
report 1978
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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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Gottschal, J.C. (author), Pol, A. (author), Kuenen, J.G. (author)
journal article 1981
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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
document
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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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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Suylen, G.M.H. (author), Kuenen, J.G. (author)
journal article 1986
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Holthuijzen, Y.A. (author), Van Dissel Emiliani, F.M.F. (author), Kuenen, J.G. (author), Konings, W.N. (author)
journal article 1987
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Van Schie, B.J. (author), Pronk, J.T. (author), Hellingwerf, K.J. (author), Van Dijken, J.P. (author), Kuenen, J.G. (author)
journal article 1987
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Van den Noort, M.A. (author), Van der Put, P.J.J.M. (author), Schoonman, J. (author)
journal article 1988
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't Hart, W.G.J. (author)
The damage development In notched (± 45, 0„, 90, 0-) carbon-epoxy coupon specimens tested under different loading conditions was determined. Constant amplitude tests at R = -1 and R = 0.1 as well as flight simulation tests were performed to establish those stress values for which no damage growth occurs.
report 1988
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van der Hoeven, W. (author)
report 1988
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