This course starts by introducing some basic concepts of the Keplerian approach, emphasizing its effectiveness and its limits. Then, an overview is given of non‐Keplerian mission scenarios involving a single attractor, including low‐thrust propelled trajectories and displaced non‐Keplerian orbits. Subsequently, a second attractor is included in the analysis, leading to the formulation of the circular restricted three‐body problem (CR3BP). The latter model is analyzed in detail, focusing on the determination of equilibrium points and on orbits around those points (Lyapunov, Lissajous, Halo). The final part involves the description of a typical mission in the context of the CR3BP. |
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