Calculate the positions of a rocket travelling between the Earth and Moon using the Runge-Kutta method for solving differential equations of motion. Trajectories are defined in list format. The first list item is a string defining the starting location of the rocket. Current options are:
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'L1' - Langrangian Point 1
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'L2' - Langrangian Point 2
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'Earth_Orbit' - Orbit above the Earth
The second list item is a list defining time array index values at which to apply a boost.
The third list item is a list defining boost magnitudes.
Example trajectories include:
'Approximate Free Return'
'Lagrangian Point 1'
'Lagrangian Point 2'
