a hybrid chemical/electric propulsion orbital transfer vehicle was studied for a coplanar transfer from low Earth orbit to geosynchronous orbit. The goal of this study was to develop a strategy combining the two propulsion Systems to reduce total radiation loads on the spacecraft and to provide attractive total trip times. Propulsion Systems were sized based on current technology storable bipropellants for the chemical stage; three separate Electric propulsion systems were considered for the low-thrust portion of the mission.
展开▼
