Convert TLE to Keplerian Elements in Scilab (CelestLab Tutorial)TLE2Keplerian 1

Описание: In this quick tutorial, I show you how to go from a classic Two-Line Element (TLE) set to the 6 Keplerian/orbital elements using Scilab and CelestLab.

How to load a TLE into Scilab
How to use the CelestLab function to convert a TLE to orbital elements
Which 6 Keplerian elements you get:
semi-major axis
eccentricity
inclination
argument of perigee
RAAN (right ascension of the ascending node)
mean anomaly → and how to turn it into true anomaly

Script (commented):
clear
//TLE: ISS
str = [..
"1 25544U 98067A 16072.60311259 .00012306 00000-0 19343-3 0 9998";
"2 25544 51.6438 179.7093 0001431 279.1916 222.9068 15.54042739989958"];

tle = CL_tle_parse(str);
// cjd in TREF, mean_kep relative to ECI
[mean_kep, cjd] = CL_tle_getElem(tle, "kep")

Mean_Anomaly = mean_kep(6);
Exc = mean_kep(2);

//Convert Mean Anomaly to True Anomaly
T_Anomaly = CL_kp_M2v(Exc, Mean_Anomaly);

Mean_Kep = (mean_kep(1), Exc, mean_kep(3), mean_kep(4), mean_kep(5), T_Anomaly)

Timestamps:
0:00 Intro
0:25 TLE format
1:10 Scilab + CelestLab setup
2:05 Converting TLE → Keplerian
3:10 Mean anomaly → true anomaly
4:00 Final vector

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#scilab #celestlab #TLE #orbitalmechanics #astrodynamics #spaceengineering #satellitetracking #keplerianelements #spacetutorial #spacecomputing #ISS #STKalternative #spacesoftware #orbitdetermination