ELECTRIC PROPULSION FOR ORBITAL TRANSFER

Abstract

This chapter focuses on a study that was carried out in 1967 for the European launcher development organization. It discusses the possible performance of the systems for orbital transfer. The particular orbital transfer maneuver is that of transferring a payload from a low altitude parking orbit into a synchronous orbit. A circular parking orbit of 350 km height has been used and it is assumed that a payload of 1000 kg is injected into this orbit by a chemically propelled launch vehicle. This low orbit capability is approximately that of the Europa I launch vehicle and the synchronous payload capabilities might be considered to be achievable by the Europa I vehicle with the appropriate electrically propelled transfer stage. The application of electric propulsion to the transfer of payloads from low orbit to synchronous orbit is feasible in principle. The development of such orbital transfer systems, which can also be used for deep space probes, should be of interest to countries and inter-national organizations that have a limited launcher potential.