Calculus model in quasi - velocity frame for small launcher, technical solution

Abstract

The purpose of this paper is to present some aspects regarding the calculus model and technical solutions for small multistage launcher for used testing the spatial equipment and scientific measurements. The calculus model consists in numerical simulation of launcher evolution for different start conditions. The launcher model presented will be with six degrees of freedom (6DOF) with dynamical translational equations written in quasi-velocity frame. Model includes aerodynamics terms in polynomial form, the thrust terms and guidance relations all of this adapted for the 6 DOF
model. The results analysed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize this small multi-stage launcher, by using hybrid engine technology for uppers stage including for Reaction Control System.