Feasibility of TSTO LOX-HC-Micro-Launcher operated from Europe Study on sensibility aspects for propulsion systems for ESA-ESTEC

Abstract

This report summarizes the work performed by DLR SART in the frame an ESA funded study. The objective of this study was to investigate the feasibility of providing a European launch service to SSO for a total cost target of 10 Million US$ (a 20% deviation is acceptable). The nominal mission of this micro-launcher is to launch a 400 kg payload to a 700 km circular orbit. This launch vehicle in the class of a Falcon 1E should be produced in Europe and use LOx-Hydrocarbon as propellant. Liquid methane has been considered in combination with liquid oxygen. The launch site is supposed to be placed in Scotland. Three different concepts have been proposed. All of them are TSTO (two stages to orbit). The reference concept is a C37-C6, using a large gas generator engine in the first stage and a smaller gas generator engine in the upper stage. The two alternative concepts are using a cluster of small engines in the first stage and one of these engines with a larger nozzle for the upper stage. A C40-C6 concept with 10 engines in the first stage is compared to a C38-C6 with 11 engines. For all concepts a preliminary design of the system and the main subsystems has been performed: structure, engines, propellant feed system has been performed. Following the technical design and analyses a cost analysis is performed to determine the development cost and whether the launch service cost target could be achieved.