Simulate an orbit with orbital elements
As it happens, I was writing code for the exact same transformation last night using this memo as a reference. I haven't yet tested my implementation but the document is quite clear about what each step is doing, which pleased me greatly.

You'll have to understand the terminology to some degree; "epoch" means a reference time for which you have the orbital elements, and "considered epoch" means the time at which you're evaluating the position, for example. Other points requiring caution: the equations inconsistently drop subscripts; the use of the Newton-Raphson solver isn't particularly clear (i.e. how many times should it run)? Make sure you get the units right also.