Implementation of the SGP4 from the NORAD SPACETRACK REPORT NO. 3. Turns input data from satellite into a graph representation of where over the earth it is located.
Calculate where an Earth-orbiting satellite is and where it will be. Takes into account Earth's non-perfect shape & how it affects gravity, atmospheric drag and lunar & solar gravity.
The X, Y and Z are in ECI format, which can't be displayed on a 2D graph. Also takes into account how the globe is converted into a imperfect 2D map.
They are converted ECI -> ECEF -> Geodetic
- Input into the field a valid TLE.
- Set the tracking time period.
- Update graph
- Adjust the minutes since start timer to see the orbit
Test case from SPACETRACK REPORT NO. 3 with inputs and outputs, used to validate SGP4 part of implementation.
Two-line element set (TLE)
SGP4 (SGP4)
1 88888U 80081S 80275.98708465 .00073094 13844-3 66816-4 0 6
2 88888 72.8435 115.9689 0086731 52.6988 110.5714 16.05824718105