机读格式显示(MARC)
- 000 01996nam 2200349 a 4500
- 008 091217s1983 ne a b 000 0 eng d
- 100 1_ |a Linden, H.H. van der.
- 245 10 |a New analytical methods for the prediction of fatigue crack growth under realistic loading / |c by H.H. van der Linden, A.U. de Koning and C.J. Lof.
- 260 __ |a [Amsterdam : |n NLR,] |c 1983.
- 300 __ |a 23 p. : |b ill. ; |c 26 cm.
- 490 0_ |a NLR MP ; |v 82055 U
- 500 __ |a This report has been prepared for publication in special issue of the International Journal of Vehicle Design.
- 500 __ |a This issue is entitled "Application of new techniques for analysis and design of aircraft structures."
- 500 __ |a The investigations mentioned in this paper have been carried out under contract with the Netherlands Agency for Aerospace Programs (NIVR)
- 500 __ |a Contract numbers 1777, 1822, 1823 and 1776.
- 504 __ |a Includes bibliographical references.
- 520 _ |a After a discussion of some aspects of aircraft design philosophy and the fatigue phenomenon, two analytical techniques for prediction of crack growth rates are described. The first method includes a model for prediction of fatigue crack growth in aluminium alloy sheet specimens subjected to service loading conditions. The second method involves the application of linear elastic fracture mechanics to three dimensional crack growth prediction under constant amplitude loading. Predictions are compared with experimental results.
- 650 _0 |a Airframes |x Fatigue.
- 700 1_ |a Koning, A.U. de.
- 830 _0 |a Nationaal Lucht- en Ruimtevaartlaboratorium ; |v MP 82055 U.
- 905 __ |a CAU |f V215/LHH |b E0218106
- 907 __ |a CAU |f V215/LHH |b E0218106
- 999 __ |t A |A gxr |a 20091217 10:06:18 |I gxr |i 20091217 10:53:14 |G gxr |g 20100302 10:25:1