Closed-form 2-D solutions for the displacements, strains, and stresses in curved, laminated orthotropic beams subjected to shear loads, moments, and temperature changes are developed. The solutions are exact and therefore equally applicable to sandwich structures as well as to ordinary laminates. The displacement solutions include rigid-body terms that are used to predict the contribution to spring-in of curved composite laminates due to differential thermal expansion in the radial and circumferential directions. Sample calculations for graphite/epoxy face-skinned aluminum honeycomb curved beams clearly predict anticipated failure modes.