Large quantities of nonmetallic composites such as G-10CR and G-11CR are currently under study as possible materials for magnetic fusion energy structures at low temperatures. Here we report on the thermal mechanical response of cracked G-10CR glass/epoxy laminates. A composite material under generalized plane strain is assumed. Fourier transforms are used to reduce the problem to the solution of a pair of dual integral equations. The solution of the dual integral equations is expressed in terms of a Fredholm integral equation of the second kind. Numerical results on the thermal stress intensity factor and the influence of the crack on mechanical properties at different temperatures are obtained and presented in graphic form.