How to convert ECI coordinates with given sidereal time to ECEF coordinates ?

Hey, I have an understanding problem with a project I am doing for my electrical engineering studies. I have to calculate the position of a receiver (of satellite signals) on the earth. For that, one part of the project is to convert ECI coordinates into ECEF coordinates. I have given the position and velocity of the satellite in the ECI-system as well as the sidereal time for each position (ca.15 min of recording in seconds, for each second position vector,velocity vector and sidereal time of the satellite are known). The Julian Date is also given. How do I convert these satellite positions + velocity in an ECEF-system?

I know that i can use the rotation matrix to rotate the ECI-system to the ECEF-system. I wanted to use the formula of GMST(as in the picture) to find out the angle between the ECI and ECEF system, so i can use that angle in my rotation matrix. The problem is, i dont know how to use the given sidereal time for each position in that equation...

I really hope someone can help me with my problem, it would be a great x-mas present!!

[Alexander Thorne]

Hi Alex, Alex here

What is the 'd' in your equation to calculate 'Y'? If you could refer me to your source or answer I would really appreciate it.

Answer 1

[Meysam Mahooti]

https://www.mathworks.com/matlabcentral/fileexchange/61957-eci2ecef-ecef2eci-transformations

Answer 2

[Amy]

Hi Alexander,

The Aerospace Toolbox has a function dcmeci2ecef that will return the 3x3 transformation matrix.

I also see that there's a File Exchange function that may work for you (and could even be helpful just as reference)

[Alexander S.]

Thanks for your answer Amy! I found out that the given sidereal time is exactly what i was looking for. Or i could use the given JD to find out the time 't' that's given in the function.