Abstract
The purpose of this paper is to present some aspects regarding the mathematical model and technical solutions for small multistage launcher for used for scientific measurements. The 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 Navigation and Control relations, all of this adapted to 6DOF 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.
Published Version
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