  Placing satellites in geostationary obital (GEO) is propellant exigeant. It
requires large propellant consumption that will take a large part of the total
mass. Hence the interest is reduce the mass of propellant loaded both in the
rocket and the satellite. Both for improving selection of transfer orbits and
propellant.
  In this paper we give a reiew of analysis of launching of satellite to GEO
using multistage transfer orbit in order to reduce the mass of propellant.
Making this analysis complete, the effect of the general relativity regarding
elliptical transfer orbit and its potensial utilization will be briefly
reviewed.
