Arbitrary perturbations #36
Description
Celestial Perturbations
The best way to handle this is probably by a "Pertubations" struct which supports J_n of different bodies (probably just stick to J2 to start with) and which other bodies to consider during the orbit. I think that this should only be added in Func() of Mission. Possibly, this could support three bodies initially and determine which body to consider based on the distance to each. We would also log which body is now being considered the third body.
Arbitrary Pertubations
For Stat OD, I'll need to add in random perturbations on specific orbital elements (specifically, HW1 requires a 1km delta on the first component of the position and a 10m/s delta on the first component of the velocity. Seems like this will also require #42. Although, for this, I could also convert the orbit to an RV, then perform the ECI perturbation, and convert this back to Keplerian OE.
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