Comparative Analysisof Structure RX 3228nozzle With The RX 3240 Nozzle Material S45C

In May 2008 was conducted static test of RX 3228 rocket and in July 2013 the static test done again RX 3240 with different nozzle form and dimensions based on ease of graphit contour manufacture. Although the results of the second static test nozzle has done pretty well, but still needed design improvementfor a lighter and easier installation process.
Assumptions made on both the nozzle is the same, where the side entrance, just accept it as part of the pressure load is protected with graphite, while divergent part that no graphite, just accept the burden of temperature, so that the analysis conducted by the adjusted load received the nozzle structure. Obtained from the simulation of the load stress occurs in the second part of the nozzle with a safety factor of convergent part due to the influence of pressure loads 4 in 2008 and safety factor 3.5 in 2013, while the diverging section that receives factor of safety with thermal loads 1.7 RX 3228 in 2008 and 1.1 for 2013 RX3240 , so that the largest stress corresponding dimensions made rocket was due to the divergent part of the effect of temperatures