I want to find the transformation matrix that converts an ECI frame at some time 't' (lets say t = 1st January 2020) to J2000 ECI frame (that is ECI frame at noon of 1st January 2000). From what I understand, Axial Precession and Nutation will contribute significantly to the desired Transformation Matrix which will be used to convert the position and velocity vectors of a satellite from current ECI frame to J2000 frame.


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