ABSTRACT
High-orbit satellites with larger antennae as loads require large station-keeping velocity increments and rational propulsion systems. We compared the bipropellant propulsion system, hybrid propulsion system and ion bipropellant system in terms of system weight, configuration layout difficulty, and so on. The weight of the hybrid propulsion system is the lowest on the premise of the same velocity increment within a given weight range. Compared with the extant platform, the modification to a hybrid propulsion system is minor and the complexity is relatively low; plume effect and jet contamination of the arc-jet thruster are lower than others, and the thrust and station-keeping efficiency of hybrid propulsion systems with an arc-jet thruster are higher. In conclusion, compared with other systems, the hybrid propulsion system can better meet the requirements of high-orbit satellites with large antennae.
