| Three-body libration points are valuable space resources, which have aroused great interest and intent ever since this century began. With domestic research having just been started up, this thesis focused mainly on the design method of libration periodic orbits and related invariant manifolds.First, Circular Restricted Three-Body Problem (CR3BP) was formulated and made dimensionless for convenience. Important concepts such as Jacobi integral, zero-velocity surface and libration points were deduced from the dynamics and their physical meaning were discussed, providing the preliminary knowledge for trajectory design.Then, the stability of the five libration points was analyzed in depth. Solutions to the first-order and third-order approximations were given respectively, with an analysis of accuracy of the latter. An iterative method for solving the exact periodic solution was introduced and applied to the computation of periodic orbits in the Earth-Moon system. Results confirmed its validity.Further more, invariant manifolds, which closely related to the periodic orbits, were discussed and its numerical obtaining method was given as well. Meanwhile, Lambert's arc in CR3BP was brought out with an effective iterative algorithm. Based on these two types of trajectories, a transfer design method was proposed. This method consists of two parts, one-impulse and two-impulse instance, depending on the distance between the manifolds and primaries. As typical examples, transfers in the Earth-Moon system were implemented using this method.Finally, as a synthesized application of periodic orbits, invariant manifolds and three-body Lambert's arc, a flight trajectory accomplishing a two-goal mission was designed, which consists of sun observation and comet encountering.To sum up, this thesis put most emphasis on libration point periodic orbits and invariant manifolds, and obtained some meaningful results. What has been achieved could serve as a good reference for further research.
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