How to calculate semiMajorAxis and trueAnomaly from TLE file

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

Answer 1

[Sam Chak]

Hi @Raghav Rathi

Use the tleread() command.

Otherwise, you can also manually extract the info as detailed here:

https://www.mathworks.com/help/aerotbx/ug/satelliteScenario-key-concepts.html#mw_e08739b4-c5da-4983-898b-56e18cc71f87

After that, apply the equations that you learned in Orbital Mechanics to determine the Semi-major axis.

[Raghav Rathi]

Hi @Sam Chak

Thanks for your reply, but tleread() is pretty much the same as orbitalElements() in terms of output.

When you create a satelliteScenario() using a TLE file, it also generates the orbit of the satellite.

For instance below is an example created using TLE file.

Since it can create the orbit of the satellite, I was wondering if there was a way to get the information about the semi major axis through a matlab function, as most of the information that is needed for the calculation is present.