Hi,
I am trying to add satelltie to satellite scenario by following the documentaion.
The general way is to simply use the TLE file
sat1 = satellite(sc,tleFile,"Name","Sat1")
If I want to find the Keplerian elements the function orbitalElements(sat1) can give eccentricity, inclination, rightAscensionOfAscendingNode and argumentOfPeriapsis. But how does MATLAB computes semiMajorAxis and trueAnomaly?
Any help is appreicated.
Thank youHi,
I am trying to add satelltie to satellite scenario by following the documentaion.
The general way is to simply use the TLE file
sat1 = satellite(sc,tleFile,"Name","Sat1")
If I want to find the Keplerian elements the function orbitalElements(sat1) can give eccentricity, inclination, rightAscensionOfAscendingNode and argumentOfPeriapsis. But how does MATLAB computes semiMajorAxis and trueAnomaly?
Any help is appreicated.
Thank you Hi,
I am trying to add satelltie to satellite scenario by following the documentaion.
The general way is to simply use the TLE file
sat1 = satellite(sc,tleFile,"Name","Sat1")
If I want to find the Keplerian elements the function orbitalElements(sat1) can give eccentricity, inclination, rightAscensionOfAscendingNode and argumentOfPeriapsis. But how does MATLAB computes semiMajorAxis and trueAnomaly?
Any help is appreicated.
Thank you matlab, communication MATLAB Answers — New Questions

​