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de Jonge, J.B. (author)The present course book has been prepared as lecture notes for a summer course given at the Technical University of Bandung (ITB) in the summer of 1984. This course took place within the framework of the TTA-79 Technical Assistance Project as agreed between the Governments of Indonesia and the Netherlands. The subjects of the course are listed...report 1984
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Noback, R. (author)Historical reviews of the discrete gust and the continious gust concept, in relation to the present requirements, are given in this report. A comparison is made between the discrete gust method and the power spectral density method on the basis of simple airplane models. No direct relation between the two methods exists. The main cause of the...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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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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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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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
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de Koning, A.U. (author), van der Linden, H.H. (author)A model for the prediction of growth rates of fatigue cracks in aluminium alloys subjected to service loading conditions is presented. The model is based on an approximate description of the crack opening behaviour and was applied successfully in an analysis of effects of crack growth acceleration and retardation observed experimentally under...report 1981
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van der Hoeven, W. (author), Schra, L. (author)The influence of sheet thickness (2 mm and 10 mm) and the influence of laminating (5x2 ram) on the fatigue crack growth properties of the aluminium alloy AL 7010-T 73651 were investigated. Both constant amplitude loading and flight simulation loading were applied. All 2 mm and 10 mm thick sheets were machined from a 150 mm thick plate, i.e....report 1981
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Noback, R. (author), Blaauboer, C. (author)Design loads for nonlinear aircraft, i.e. aircraft with gust alleviation system or yaw dampler, cannot be established with the Power Spectral Density method. The only method available is by means of computer simvilation. Methods to approximate load exceedance curves of nonlinear aircraft are proposed in this report. For the derivation of the...report 1980
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't Hart, W.G.J. (author), Schra, L. (author)The Al-Zn-Mg-Cu alloy 7050 produced by Alcoa is a typical plate and forging alloy because of its low quench sensitivity. In order to compare this alloy with the earlier tested plate alloy 7010 an experimental programme was performed involving tensile, fracture toughness, and fatigue testing. In addition stress corrosion crack initiation and...report 1980
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'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
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Erkelens, L.J.J. (author), Simons, J.L. (author)This report deals with determining a hypothetic control system which provides improved rigid body and structural mode damping of a flexible aircraft in order to improve the riding qualities and to minimize the wing bending moment during flights in turbulence. The equations of motion used in the computations are related to a high' performance...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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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
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de Jonge, J.B. (author)Due to the development of servo hydraulic fatigue testing machines, fatigue tests under realistic loading conditions have become possible. In these tests, standardized load sequences can be applied. The paper describes the main properties of such sequences, including TWIST and FALSTAFF. Various examples of application of these sequences are...report 1980
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van der Linden, H.H. (author)The report describes a joint Garteur activity in the field of the prediction of crack propagation under variable amplitude loading. Existing crack propagation models or models under development will be checked with NLR crack propagation data of 202U-T3 Alclad 2 mm sheet material under F-27 Spectrum flight simulation loading. After completion of...report 1979
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de Koning, A.U. (author)In the present report a simple analytical model for the "behaviour of a centrally cracked strip is proposed. Formulae for computation of compliance, crack opening displacement and effective crack extension force are derived. The model is based on the classical solution for a crack infinite sheet under uniaxial tension. The effect of finite...report 1979
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Schijve, J. (author)Paper presented at the 16th ICAP Conference, Brussels, 14 and 15 May 1979.report 1979
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't Hart, W.G.J. (author), Schra, L. (author)An experimental investigation.was performed on 80 mm thick plate material of 7OIO-T7651 and 7OIO-T73651 developed by Alcan Industries Ltd in U.K. The testing programme involved: tensile tests, fracture toughness, stress corrosion and fatigue tests. For comparison a similar investigation vas carried out on 7075-T7351 Alcoa plate material.report 1979
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de Jonge, J.B. (author)The paper starts with a general discussion on various aspects of life re-assessment. Specific attention is paid to the possibility of re-assesgrnent by means of comparative fatigue tests on specimens. As an illustration of this method, the paper gives a description of the life-re-assessment procedures applied by the Royal Netherlands Airforce...report 1979