Drag coefficient modelling in the context of small launcher optimisation

The purpose of this paper is to present a fast mathematical model that can be used to quickly asses the drag coefficient for generic launcher configurations. The tool developed based on this mathematical model can be used separately or it can be integrated in a multidisciplinary optimisation algorithm for a preliminary microlauncher design

MDO approach for a two-stage microlauncher

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

Small Innovative Launcher for Europe: Achievement of the H2020 Project SMILE

Today's market for small satellites is expanding, but there is little availability of affordable launches. Launch costs of around €50,000 per kg are required to compete with ride-shares. Hence, production and operation costs are considered essential. Fourteen European companies and institutes have joined forces in a Horizon2020 project called "SMall Innovative Launcher for Europe" (SMILE). The project aims at designing a launcher for satellites of about 50 kg and a European launch facility in northern Norway. Critical technologies on propulsion, avionics, and manufacturing of cost-effective solutions are developed in order to increase the readiness level of a future European launcher