Prompt Content
Set up a Python-based simulation environment that accurately models the orbital dynamics of both the chaser (refueling) and target (GEO) spacecraft. Specifically, implement relative motion equations (e.g., Clohessy-Wiltshire) for proximity operations. How will you account for Earth's oblateness (J2 effect) and other perturbations relevant to GEO? Outline the state vectors and coordinate frames you'll use.
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