Analyze of multistage transfer orbit to reach the GEO orbit in a rotational symmetric gravitational field
Abstract
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.
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