Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite

Abstract

Full electric propulsion system becomes popular recently and getting more common in the communication satellite industry. Full electric or hybrid propulsion selection causes results in significant reduction in satellite propellant mass. Conventional full chemical satellite propellant mass is roughly 2/3 of launch mass so this huge reduction in propellant mass changes satellite design and preferences. Depending on satellite size and launch vehicle performance, full electric satellite requires 3-4 times less propellant compared to full chemical satellite and 1-2 times less propellant compared to the hybrid system. Satellite launch mass can be reduced by 40% for full electric propulsion and 15% for hybrid propulsion hence launch cost can be decreased by 40% and 15 % with the benefit of reducing propellant mass. It is possible to extend satellite communication capacity average 30 transponders for full electric and average 10 transponders for a hybrid system by using the benefit of propellant mass reduction. It takes 4-8 months to reach geostationary orbit for full electric satellite but in a chemical propulsion satellite, it takes a few days. Satellite subjects to additional radiation due to this long trip and hence additional aging. Expected revenue loss is another issue and conventional insurance policy needs an amendment to be in line with electric propulsion technology. The development of full electric satellite lowers the cost per transponder significantly.