I'm relatively new to orbital mechanics and I know there are a ton of resources and similar questions on the web, but I can't seem to get a straight answer/guidance from any of them.
I have a set of data regarding any particular satellite which consists of the following:
- Mean motion
- Mean anomaly
- Argument of perigee
- Right Ascension of Ascending Node (RAAN) AKA Longitude of Ascending Node
This data is extracted using PyEphem library. What I would like to calculate is the longitude, latitude and altitude of the satellite at any given time. I know what each parameter means but I don't know how they relate to my unknowns.
I tried reading papers, tried several simulations and checked out lots of articles about Keplerian elements conversion but I still can't figure out how to connect the dots. The main resources I have been studying are:
and I also read most of the related questions on this website. Would it be easier if I used real-time tracking data instead of using TLE to predict my unknown?
Thanks in advance!