MDO approach for a two-stage microlauncher

Abstract

The paper focuses on the multidisciplinary optimisation and preliminary design of a two-stage microlauncher capable of inserting a small 50 kg payload into Low Earth Orbit. The microlauncher is obtained using a MDO approach, where the lightest configuration capable of reaching the target orbit is considered to be optimal. For this paper, the propulsion system of the microlauncher is based on a non-cryogenic bipropellant combination.

Keywords

• microlauncher
• MDO
• liquid propellant