Validation of trajectories

While the three-body problem is a good model for rapid prototyping traje-cotries and building intuition, higher fidelity models are necessary to evalu-ate the feasibility of these trajectories in real world scenarios. Firstly, these trajectories must be optimized in a full ephmeris model with additional per-turbations such as solar radiation pressure (SRP) and J2 perper-turbations for the Earth, Jupiter etc. Secondly, these trajectories must be evaluated in a flight ready mission analysis tool like NASA GSFC’s General Mission Anal-ysis Tool (GMAT) [33]. GMAT is a space mission design software system that includes high-fidelity space system models, local optimization and tar-geting capabilities, as well as user features like the fully-featured interactive Graphical User Interface (GUI) with customizable plots, reports and data products. Having the ability to port trajectories to GMAT is an important feature that will validate the trajectories generated in simpler models.

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