How to work with TEME reference frame using Aerospace Toolbox functions?

I am looking for a feature, setting or command in MATLAB that allows converting coordinate systems given an input or desired output in the TEME (True Equator, Mean Equinox) reference frame rather than in ICRF (International Celestial Reference Frame) or ITRF (International Terrestrial Reference Frame), based on the knowledge of the MATLAB functions “ecef2eci” and “eci2ecef.”

Answer 1

[MathWorks Support Team]

Although there is currently no MATLAB function that directly transforms between TEME and ICRF, the Aerospace Toolbox functions “siderealTime” and “deltaUT1” can be used to perform the desired transformations. These functions are based on the equation to transform from TEME to PEF (Pseudo Earth Fixed) reference frame. Since polar motion accounts for the difference between PEF and ITRF, by neglecting polar motion in the “ecef2eci” function, you can perform the transformation from PEF reference frame to ICRF.

Please refer to the following documentation pages for more details. 

For the “siderealTime” function:

https://www.mathworks.com/help/releases/R2023a/aerotbx/ug/siderealtime.html

For the “deltaUT1” function:

https://www.mathworks.com/help/releases/R2023a/aerotbx/ug/deltaut1.html