Performance comparison of reusable launch vehicles

Abstract

A parameterised generic launch vehicle design is subjected to performance evaluation using the ORBITER model which is capable of optimising both the design and trajectory of the vehicle. The launcher initial mass, flight path angle, velocity and altitude are varied around design points of existing vehicle concepts to investigate the subsequent effect on performance for payload delivery into a 90km by 200km orbit. The performance results suggest that SSTO systems are unfeasible, delivering marginal positive payload performance only when externally accelerated to high speed using a sled mechanism. The optimal vehicle type from a purely performance perspective is deemed to be the TSTO vertically launched configuration.