Design and Analysis of Direct Abort Orbits in the Earth-Moon Transfer Phase of Crewed Lunar Exploration Missions

A direct abort orbit design method is presented for missions in the Earth-Moon transfer phase of crewed lunar exploration missions. First, according to demand an emergency rescue phase, two schemes are introduced. Then, a serial proposed high-fidelity orbit. An analytical model established calculation initial values, and optimization performed determine single-impulse hybrid process generate two-impulse The results simulation examples verify validity feasibility method. Finally, extensive simulations carried out analyze characteristics impulse return time reveal general rules orbits. research conclusions can provide reference future