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The orbital elements $\omega$, $i$ and $\Omega$ are Euler angles in the sequence $(3, 1, 3)$. The easiest way to transform them is to convert them to a representation that's easier to manipulate, e.g. unit quaternions or a matrix, apply the required transformation then convert back to Euler angles. A useful guide to converting between the systems is given by ...


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You could convert the orbital elements into x,y,z and $ \dot{x}, \dot{y}, \dot{z}$ and then calculate a whole orbit. A source for converting orbital elements into cartesian coordinates is here.


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