Oribital elements from ECI to ECEF

Hello,

I have 6 orbital elements in ECI frame, but I need them to be in Earth fixed (ECEF).

Is there any MATLAB function available to get position, velocity vectors from 6 orbital elements and connvert them to ECEF position and velocity vectors?

Thanks in advance

Answer 1

[ScottB]

There is eci2ecef:

Position, velocity, and acceleration vectors in Earth-centered Earth-fixed (ECEF) coordinate system - MATLAB eci2ecef (mathworks.com)