Small Orbital Launcher, Performance Evaluation

Teodor Viorel Chelaru; Adrian Chelaru

doi:10.4028/www.scientific.net/AMM.841.278

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 841Small Orbital Launcher, Performance Evaluation

Small Orbital Launcher, Performance Evaluation

Abstract:

The purpose of this paper is to present some aspects regarding the computational model and performance evaluation for three stages launch vehicle (LV) used to inject into circular orbit a small size payload. The computational model consists in numerical simulation of LV evolution for imposed start conditions and optimisation of flight parameter in order to obtain injection into circular orbit. The launcher model presented will be with three degrees of freedom (3DOF) and variable mass. The results analysed will be the flight parameters and the ballistic performances. The discussions area will focus around the technical possibility to evaluate the performance of a small multi-stage launcher using the developed model. From a technical point of view, the paper is focused on ESA project “Study – concept, to achieve a Small Orbital Launcher through zonal cooperation – SOL” finalised in 2015

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Periodical:

Applied Mechanics and Materials (Volume 841)

Pages:

278-285

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.841.278

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Online since:

June 2016

Authors:

Teodor Viorel Chelaru, Adrian Chelaru*

Keywords:

Mathematical Model, Performance, Simulation, Small Orbital Launcher

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References

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