Earth-Moon space station orbit design based on three-body problem
To meet the needs of constructing future Earth-Moon space station,the orbit selection and transfer trajectory design of the station has been implemented.Based on the Earth-Moon space peri-odic orbits,the southern L2 near-rectilinear halo orbit(NRHO)is selected as the target orbit by comprehensively considering the orbit configuration and stability.Considering the high stability of NRHO and the difficulty to transfer,the optimal transfer from the lunar transfer orbit to NRHO is de-signed based on the three-body Lambert algorithm through the lunar gravity assist.To overcome the defect that NRHO has no obvious manifold structure,the theory of the principal stretching direction in phase space based on the Cauchy-Green tensor is proposed to obtain the most effective impulse ex-erting direction,and then the low-energy transfer trajectory is derived by patching the Lambert seg-ment with the inverse integral trajectory along the principal stretching direction.The research results indicate that the lunar gravity assist transfer can be used as an ideal orbit for manned transfer,and the low-energy transfer trajectory using the Lambert patching method can effectively shorten the transfer time and provide a reference for the cargo spacecraft to the space station.
Earth-Moon space stationnear-rectilinear halo orbitprincipal stretching directionthree-body Lambert algorithm
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