Abstract
Stress intensity factors are obtained by means of a finite element code for the problem of a two-layered plane strain cylinder with a cracked inner bore under internal pressure loading. This problem has application to solid propellant rocket motors with the necessary viscoelastic calculations being constructed from a knowledge of elastic stress intensity factors. Solutions were obtained for two cylinder geometries and a range of crack sizes, using the energy release rate with crack extension calculated by the finite-element code. This procedure showed good comparison with check problems and is quite insensitive to element mesh size. The stress intensity factor results are unusual in that a maximum was reached at an intermediate crack size. A simple approximate formula for K 1 is presented that compares well with the numerical results and reduces to certain limit cases available in the literature.
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