In the present work, a series of unstiffened, thin-walled (radius to thickness ratio, R/t = 216), aluminum cylindrical shells, containing centralized cracks at angles to the shell generators ranging from 0 degree to 90 degree at an interval of 15 degree and of various crack length, are internally pressurized in order to determine the effect of crack length and crack angle on the failure mechanism of the shells. Curves of the maximum pressure leading to global failure of the shells as a function of crack angle for two different crack lengths is presented and compared against similar data obtained by Starnes and Rose for theta=0. The present experimental data can be used to find a governing predictive crack growth criterion as a function of crack angle, which can be used in commercial finite element codes for predicting the failure of more complex structures like transport fuselage shell structures. As a part of the work, an initial comparison between an analysis based on linear elastic fracture mechanics and the experimental data is made. For cracks which are inclined with respect to the applied stress, both the opening (tensile) mode I stress intensity factor and the sliding (shear) mode II stress intensity factor are significant. These depend on the angle of the crack with respect to the applied load. Fairly good agreement between analysis and experiment is obtained if adjusted values of KI(c) and KII(c) are used along with the assumption that crack growth is governed by a quadratic failure criterion.
Damage tolerance of cracked cylindrical shells under internal pressure
2000
12 Seiten, 10 Quellen
Aufsatz (Konferenz)
Englisch
Damage tolerance of cracked cylindrical shells under internal pressure
Tema Archiv | 2001
|AIAA-2001-1485 Damage Tolerance of Cracked Cylindrical Shells under Internal Pressure
British Library Conference Proceedings | 2001
|