Design and optimization of Earth-Moon L1 low-energy transfer orbit
Aiming at the low-energy transfer problem between the periodic orbit of the cislunar space libration point and near-Earth orbit,a design method of 4-impulses low-energy transfer orbit from Earth-Moon L1(EML1)point Halo orbit to geostationary Earth orbit(GEO)is proposed.Based on the design of 3-impulses transfer orbit which applies disturbed manifold and Lambert arc,the 4-impulses low-energy transfer orbit is designed by analyzing the relationship between the change of Jacobi constant and the velocity increment.Numerical simulation results show that the 4-impulse optimization model is more efficient than 3-impulse model and a better transfer scheme can be obtained,which effectively solves the problem of obtaining poor optimization results due to large search space and numerous extreme values in the optimization process.The proposed design method can be used to study the transfer between other periodic orbit families of EML1 and various near-Earth orbits as well.
cislunar spacelibration pointperiodic orbitinvariant manifoldlow-energy transfer orbit
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