Convert TLE to Keplerian Elements in Scilab (CelestLab Tutorial)TLE2Keplerian 1 скачать в хорошем качестве

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

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 If you find this useful, drop a like and subscribe for more aerospace videos. #scilab #celestlab #TLE #orbitalmechanics #astrodynamics #spaceengineering #satellitetracking #keplerianelements #spacetutorial #spacecomputing #ISS #STKalternative #spacesoftware #orbitdetermination