Rocket motor design is based on the use of maximum capability of each component. To fully realize this goal in the case of rocket nozzle,, a more precise structural analysis has to be performed. The finite element method provides one of the powerful and commonly used techniques for such type of analysis. In this work, the stress analysis on rocket nozzle is investigated. A finite element computer program was implemented for stress analysis of axisymmetric structures. The program would assist in therrno-structural verification of rocket nozzles made of composite materials with non-linear thermal and mechanical properties. For a case study on a submerged nozzle, exploration of critical loading zones was made possible, by the analysis of results from running this program. The efficiency of the program had been proved by the good agreement with results obtained from theory and other validated codes.