A trade-off methodology for micro-launchers

Abstract The trend of cost-effective access to space and satellite technologies’ evolution is increasing the small market. However, payloads usually ride as piggyback, being a secondary passenger vector, with very low flexibility in target orbit launch schedule. micro-launchers are designed answer needs missions, payload capacity up 350 kg Low Earth Orbit, aiming turn-over time competitive prices. This paper explains work performed by Politecnico di Torino support ESA–ESTEC activities on micro-launchers. aim provide preliminary guidelines for choosing evaluating new innovative micro-launcher flight vehicle engineering processes. A trade-off methodology proposed defined based Analytically Hierarchical Process (AHP). considers, among other features, profile, maximum payload, physical characteristics. To analysis, software tool built automatic generation aerodynamics propulsion parameters needed completion designs, enabling performance estimation. launcher’s models, an analysis take-off sites orbits, also produced. allows definition maps where graphed function altitude inclination. set exploiting different technologies assessed case study.