I already asked here about how to calculate orbits of satellites programmatically then plot them on 2d plane, but my question was too broad.
I'm still on my journey to understand & pull such software out ; I learned that Orbital state vectors are the way to start plotting a certain celestial object's orbit, but I don't quite understand the parameters of the vector.
Needing R (position) & V (velocity) & T (time),
Since V can be fetched from dividing the differentiation of R/T.
But R is composed of (x,y,z), how can I calculate it with respect to the frame of reference (earth-centered equatorial system) ?
Am I moving on the right track ?