Mathematical model for small launcher, performances evaluation

The paper presents some aspects regarding the mathematical model and performance evaluation for a four stages small launcher. This work uses two separate models dedicated for each flight phase. For the ascending phase, we will use a three degrees of freedom model in quasi-velocity frame. For the orbital phase, we will use a Gauss perturbing model. The results analyzed will be in quasi-velocity frame but also some orbital parameters will be presented. Using these models, the small launcher performances will be evaluated. The novelty of the paper consists in orbital injection approach, with optimal maneuver description.