深宇宙探査のための地球往復軌道の特性解析

摘要

Most of planetary exploration missions with low thrust propulsion in Japan need EDVEGA (Electric Delta-V Earth Gravity Assist). This technique is a kind of earth swing-by after earth return trajectory with electric propulsion. The periods basically used in EDVEGA are one year or 1.4 years which are the periods of ballistic earth return trajectory regardless of earth escape velocity. In this study, low thrust earth return trajectory is optimized for total amount of acceleration with a return period. Then this study shows that the optimum earth return trajectory includes 1.0 or 1.4 year ballistic earth return trajectory and analyzes the characteristic of Earth return trajectory.