Optimal Jupiter Capture Trajectory Design under Constraints

This paper presents a three-maneuver capture strategy for Jupiter capture orbit under multiple constraints. The method divides the capture process into three phases: hyperbolic trajectory insertion, intermediate orbit adjustment, and final insertion. First, the optimal Earth-Jupiter launch windows were identified, with the hyperbolic excess velocity vector transformed into Jupiter's equatorial frame as the capture constraint. The orientation constraint of the target orbits is also considered. Second, three impulse maneuvers are implemented to connect the hyperbolic trajectory and the target orbit. The energy-optimal trajectories are obtained. The influence of perijove altitude, orbital inclination, and argument of periapsis on capture velocity increment are analyzed. Finally, the optimal impulse trajectory is transferred to the finite-thrust capture trajectory with the thrust constrain. The direct collocation method is applied to obtain the optimal thrust direction during the three segments. The proposed integrated method could provide reference for future Jupiter exploration mission design.