Since the beginning of the practice of rocketry, many students found hard challenges in the production of the set of parts from the prototype, since bigger the overall length of the rocket greater the degree of hardship. This goes from the nose of the projectile to his recovery system. The self-made motor rocket is the part of any projectile that needs a good planning time. This is because the shape and the propellant grain are two variables that require a lot of attention in the production, since they can make the launch ideal or they can cause rough errors in the results of the launch. In this article, we propose the assembly of a script for the design of rocket motors, linking the influence of thermal sciences (thermodynamics and flow of compressible fluids) to the dimensions of the future motor, since even Sutton (2017) mentions which the basic principles are essentially those of mechanics, thermodynamics and chemistry. This program will be based on the SRM table, proposed by Richard Nakka, softwares as GDR Propep, to aid the measurent of the grain propellant dosage, as well as tool such as SolidWorks to illustrate representations of rocket motors
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