Trajectory Design of Solar Ring Mission Based on Libration Point Trajectory of Three-body System

Solar observations in space are the key means to understand the origin of solar cycles, solar eruptions, and extreme weather events. In order to observe the Sun from the ecliptic plane at 360 degrees, scientists have proposed a 3D solar exploration mission. Aiming at the “Solar Ring” mission, a deployment method of “Solar Ring” orbit based on the low-energy trajectories associated with the libration point of the three-body system is proposed. Using the amplitude and off-orbit points of Sun-Earth L1/L2 Halo orbits as design parameters, the transfer time and deep-space maneuver as the cost function, the mission trajectories are constructed and optimized with the invariant manifolds of three-body system and contour maps. A global analysis of mission cost and the corresponding design variables is carried out. Simulation results show that the orbit deployment cannot satisfy the shortest transfer time and the smallest deep-space maneuver at the same time. The optimal transfer time solution under the orbit maneuver constraint is obtained, and a plan for launching and deploying orbits is designed based on the way of one rocket two spacecraft with the rocket of Long Match 3A.