During an interplanetary mission, the vehicle is subject to the attraction of all the bodies of the solar system. In order to simplify the scenario definition, the trajectory is split into heliocentric and planetocentric phases, based on the concept of sphere of influence. This allows us to decompose the interplanetary path as a succession of two‐body problems. This patched conic modeling highlights the phenomenon of gravity assist during fly‐bys, which modifies the spacecraft trajectory in the heliocentric frame without propelled maneuvers. It allows us to easily define preliminary mission scenarios with multiple fly‐bys before moving on to detailed simulations.
Interplanetary Trajectory
Space Trajectories ; 383-410
2024-12-24
28 pages
Article/Chapter (Book)
Electronic Resource
English
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