Lunar orbit rendezvous phasing design for Chang’e-5 Mission

To achieve the mission of Chang’e-5 lunar orbit rendezvous，a new 4-impulsive rendezvous phasing scheme is proposed. By using the radial control variable，the argument of latitude of each impulse is constrained，so as to satisfy the constraint of tracking condition. For the new 4-impulse scheme，a new initial guess method is proposed by using the near-circular orbit deviation equation. A high-fidelity numerical solution is constructed using the differential correction algorithm，and the corresponding analytical state transition matrix is derived. The design consideration and results of the key parameters of Chang’e-5 lunar orbit rendezvous mission are discussed. The optimization design model of rendezvous guidance constraint with the constraint of tracking condition is established. The optimal argument of latitude in each impulse is obtained by solving the optimization problem. The global characteristics of constrained optimization problems are also revealed. The operation results of Chang’e-5 show that the proposed strategy can guarantee the constraint of tracking condition，satisfying the flight mission requirements. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.