Untersuchungen der Nutzlastkapazität der Trägerrakete "Sojus/ST" für den Startplatz Kourou

Abstract

This study regards the payload-capacity of the Russian liquid-fuel Launcher "Sojuz/ST" from the launchpad Kourou as a medium-class launcher. Based on published technical data, the "Sojuz/ST" is simulated in geometry and mass estimation, propulsion, and trajectory analysis, including stage re-entry after engine cut-off. Several variations of the upper stages are considered: Variations of Block I with and without the "Fregat"-stage or as an alternative a hypothetical cryogenic upper stage. Reference-mission is an elliptical GTO and also an ascent to circular SSO. The achieved results allow to evaluate the possibilities to use this vehicle as a potential replacement for the Ariane 4.