This is the first of two example problems that simulate a rocket nozzle:
The example problem presented here simulates thermal stresses during the manufacturing (fabrication) stage of the nozzle.
The second example, Rocket Nozzle Extension Simulation: Operation, simulates thermal stresses induced during the operation of the nozzle.
While both examples are based on the same geometry, the assumptions used are different, therefore leading to different meshes and different element types.
This example problem demonstrates how current structural-shell element technology can accurately model the orthotropic thermal expansion in curved-shell structures. Section offsets are applied when connecting shell elements to shell elements, or shell elements to other element types. An appropriate results-storage option is selected for postprocessing the layered-element solution.