Application of Advanced Materials in a Composite Rocket Nozzle

Rocket nozzles which utilize an internal protective layer have been studied using both 1-D and 2-D thermostructural analyses. Parametric results have been generated for a wide range of material properties and engine operating conditions. A 2-D stress analysis has been completed for a nozzle exposed to oxygen/hydrogen combustion products using a 2.54 mm protective layer made of silicon carbide (SiC). While the SiC material appears to be capable of handling the stresses in this application, some alternate cooling of the gases would be required to insure thermal integrity of the protective layer.