Continuous-Thrust Analytical State Propagation and Optimal Orbit Transfer Near Libration Points in CR3BP

Analytical state propagation under arbitrary continuous thrust acceleration near libration points in the circular restricted three-body problem is presented. The orbit motion is described by using the linear dynamical model relative to the libration points. A Fourier-series-form thrust acceleration is used to approximate the real one that is in an arbitrary form. Based on the thrust series approximation, the analytical propagation of orbit state is obtained by using the linear system theory. In addition, the fuel-optimal orbit transfer problem between libration point orbits is considered, and a nonlinear programming problem is established via the presented analytical state propagation to rapidly find the optimal solution. Several numerical examples of Lissajous and Halo orbits are given to validate the accuracy of the derived continuous-thrust analytical state propagation and the feasibility of the presented orbit transfer approach between libration point orbits.