Searched for: %2520
(1 - 20 of 23)

Pages

List view
Grid view
document
ten Have, A.A. (author), Nederveen, A. (author), de Jonge, J.B. (author), van Leeuwen, H.P. (author)
This memorandum presents results of crack propagation tests on notched Alclad 2024-T351 sheet specimens. Two thicknesses were investigated (2 mm and 8 mm), as well as various spectrum modifications and the effect of clustering of severe flights within the test load sequence.
report 1982
document
de Jonge, J.B. (author), Nederveen, A. (author), ten Have, A.A. (author)
In international collaboration, two standardized fatigue test load sequences for helicopter components, HELIX and FELIX, have recently been established. The present report describes tests on notched Titanium Alloy specimens to evaluate the properties of the FELIX standard. Tests included Constauit Amplitude, block programme and FELIX-flight...
report 1982
document
Nederveen, A. (author), de Jong, J.B. (author)
The influence of the approximation of the lower end of the load spectrum was investigated by comparative tests using the Basic F-27 test programme and an extended version, containing three times more cycles per flight. Crack growth was studied on notched sheet specimens made of Alclad 202U-T3 and Alclad TOT5-T6. Fatigue life tests were done on...
report 1981
document
'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
document
Nederveen, A. (author), de Jonge, J.B. (author), Tromp, P.J. (author)
The effects of systematic variations in mean stress level and in spectrum and ground load severity of a flight simulation test programme have been investigated on riveted specimens (fatigue life) and sheet specimens with central saw cut (crack growth). The fatigue life and crack propagation life in Alclad 202U-T3 compared with Alclad TOT5-T6...
report 1980
document
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
document
de Jonge, J.B. (author), Nederveen, A. (author), Tromp, P.J. (author)
Fatigue tests under flight simulation loading were done on simple notched 2024-T3 Alclad sheet specimens. Reduction of the gust load amplitudes resulted in an increase of crack initiation life but hardly influenced crack propagation. Reduction of the overall stress level increased both initiation and crack propagation life. The observed...
report 1978
document
Nederveen, A. (author), van Leeuwen, H.P. (author)
Pin-loaded loosely fitting aluminium alloy lugs have been tested in fatigue. Ihe fatigue tests comprised constant amplitude tests at a common mean stress, as well as simplified service simulation tests involving a square wave main load with a high-frequency lowamplitude sinusoidal load superimposed. A variety of anti-fret coatings were compared...
report 1975
document
Nederveen, A. (author), van Leeuwen, H.P. (author)
Pin-loaded loosely fitting aluminium alloy lugs have been tested in fatigue. Ihe fatigue tests comprised constant amplitude tests at a common mean stress, as well as simplified service simulation tests involving a square wave main load with a high-frequency low-amplitude sinusoidal load superimposed. A variety of anti-fret coatings were compared...
report 1975
document
't Hart, W.G.J. (author), Nederveen, A. (author), Stoffels, E. (author), Tromp, J. (author)
Residual strength tests have been performed on 610 mm wide centre cracked panels. During the tests, stable crack growth was filmed and crack opening displacements were measured. Fracture toughness was determined using the method of Feddersen. Flight simulation fatigue tests were carried out to investigate the crack propagation properties. A...
report 1975
document
'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
document
van Dijk, G.M. (author), Nederveen, A. (author)
Fatigue tests were performed on notched 7075-T6 specimens according to the F-104 G wing root bending-load conditions. The program included both artificial and actually recorded loading sequences. Primarily the test program was initiated to provide an experimental fatigue performance index for the particular F-104 G usage with the Royal...
report 1975
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
document
Bartelds, G. (author), Nederveen, A. (author)
Sandwich panels provided with a central saw cut in one face layer were fatigue tested to study crack growth up to a predetermined length. Static residual strength was determined subsequently. Crack growth rates and residual strength are compared with similar data for face sheet material. An increased resistance against both stable fatigue crack...
report 1973
document
Bartelds, G. (author), Nederveen, A. (author)
A series of full depth honeycomb panels containing one craoked face sheet were tested to failure in bending. Failure was due to either craok extension in damaged face layer or buckling of compressive facing; the last mode occurred even when the compressed face layer was undamaged. No significant difference in residual strength in bending towards...
report 1973
document
van Leeuwen, H.P. (author), Nederveen, A. (author), Ruiter, H.H. (author)
Pin loaded lugs in 2024 T3 have been fatigued under a load compounded from a low frequency load with crenelated wave form and a high frequenoy sinusoidal load. The effects of tightness of fit, clamping pressure and lubrication have been investigated.
report 1973
document
Broek, D. (author), Hartman, A. (author), Nederveen, A. (author)
A few preliminary tests on 2024-T3 material were carried out allowing electron fractographical examination of the fracture features of fatigue crack growth in vacuum. Fatigue striations were generally not formed in vacuum: the fracture surface consists of irregular fine slip steps and coarse slip steps which show a certain periodicity. The...
report 1971
document
Hartman, A. (author), Jacobs, F.A. (author), Nederveen, A. (author), de Rijk, P. (author)
The investigation on the propagation of fatigue cracks in aluminium alloy sheet under fluctuating tension comprised four parts. (1) Tests to determine the combined effects of the humidity of the air and the lead frequency (clad 2024-T3 and 7075-T6). (2) Tests to determine the effect of water. (3) Tests to determine the effect of wetting with a...
report 1967
document
Schijve, J. (author), Broek, D. (author), de Rijk, P. (author), Nederveen, A. (author), Sevenhuysen, P.J. (author)
Fatigue tests were carried out on full-scale tension skins of a wing center section of 7075-T6 material. Variable-amplitude tests were carried out with the following load sequences: (a) random load, (b) program load, (c) random load with GTAC (ground-to-air cycles) and (d) program load with GTAC. Constant-amplitude tests were carried out with...
report 1965
document
Broek, D. (author), Nederveen, A. (author)
Residual strength tests with a duration ranging from 30 minutes to about 0.4 seconds were carried out on 2024-T3 alclad sheet specimens containing a central transverse saw cut. It turned out that the stress to initiate slow crack growth decreased at increasing loading rate, but in the range of loading rates tested the residual strength did not...
report 1965
Searched for: %2520
(1 - 20 of 23)

Pages

List view
Grid view