Set to true to suppress the use and availability of the ICRF, and preserve the computation of the celestial reference frame as was done in versions of ODTK prior to version 6. When true, the Mean Equator Mean Equinox (MEME) of J2000 is used as the inertial reference frame for the Earth and the Sun for the purpose of trajectory generation and observation modeling. In this mode, the ICRF is unavailable and transformations from the MEME of J2000 frame to the Earth fixed frame use the IAU 1976 theory of precession and IAU 1980 theory of nutation. Any references to the ICRF frame will be automatically changed to use J2000 instead. When applied to orbit states, the state is transformed; when applied to maneuver states, the state is untouched and only the frame name is changed.
When set to false, the ICRF is used as the inertial reference frame for the Earth and the Sun for the purpose of trajectory generation and observation modeling. In this mode, transformations from the ICRF to the Earth fixed frame use the IAU 2000 combined theory of precession and nutation. Transformations between the ICRF and the MEME of J2000 frame are performed using the Earth pseudo-fixed frame (pole wander is not applied) as the intermediary frame.
Note: When ICRF is the default inertial frame, ephemeris files from the simulator, filter and smoother will be written in this frame. These files will be stamped as stk.v.9.0 files and will only be readable by STK v9 and later. If you are creating ephemeris files for use in a version of STK prior to v9, set SuppressICRF to true.