Mission Design for Multi-Target Jupiter System Exploration and Ring Sample Return Using Gravity Assists

This paper presents a trajectory design framework for a multi-target exploration mission within the Jovian system, incorporating the Gossamer ring sample return and Jovian moon exploration. First, the interplanetary transfer from Earth to Jupiter is analyzed using Tisserand diagrams to screen gravity assist sequences, with further optimization conducted via the MGA method. The EVEEJ (Earth-Venus-Earth-Earth-Jupiter) sequence is identified as the optimal transfer path. Next, the spacecraft crosses Jupiter's Gossamer ring twice during the close Jupiter flyby, enabling dust sample collection using aerogel-based capture technology. The main probe carrying the return capsule transfers into the Earth-bound trajectory using the JEEME (Jupiter-Earth-Earth-Mars-Earth) return sequence. Furthermore, a sub-probe is deployed in the Jovian system to conduct extended scientific investigations. An intra-Jupiter system exploration orbit is designed, including Jupiter capture, intra-system gravity assist transfers, and Callisto orbit insertion. The detailed mission profile is designed and analyzed. The sample return mission requires a total velocity increment of 0.3329 km/s with a duration of 14.8 years, and the total ΔV for the intra-system mission is 1.8212 km/s over 818 days, which is available based on the current spacecraft capability. The proposed scheme demonstrates a balanced approach between engineering feasibility and scientific value, offering a viable solution for complex outer planetary missions.