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The paper purpose is to dignify some aspects regarding the calculus model and technical solutions for small multistage suborbital launchers used to test spatial equipment and scientific measurements. The calculus methodology consists in numerical simulation of launcher evolution for different start conditions. The rocket model presented will be with six DOF and variable mass. The results analyzed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize small suborbital multistage launchers recycling military rocket engines.