TEME

spacekernel.frames.TEME = <spacekernel.frames.frames._TEME object>

True Equator Mean Equinox Frame (TEME).

The TEME frame is widely used in conjunction with SGP4/SDP4 orbit propagators, especially for TLE-based satellite tracking. This class provides precise transformation from TEME to ITRF, compliant with the conventions and formulas from the AIAA Spacetrack Report and Vallado.

See also

ITRF

International Terrestrial Reference Frame

Frame

Base class for reference frames

Notes

• Implements TEME → ITRF transformation using conventions from:

  • AIAA-2006-6753, “Revisiting Spacetrack Report #3” (Appendix C)

  • Vallado, D.A., “Fundamentals of Astrodynamics and Applications”, 4th Ed.

• Transformation applies polar motion, GMST82 rotation, and sidereal time corrections.

Summary

_TEME.to_ITRF(self, time, r_TEME, v_TEME)

Transform position and velocity from TEME to ITRF.

Methods

_TEME.to_ITRF(self, time: DatetimeLike, r_TEME: ndarray[double], v_TEME: ndarray[double]) → tuple[ndarray, 2]

Transform position and velocity from TEME to ITRF.

Parameters:

timeDatetimeLike

Time(s) for which the transformation is computed.

r_TEMEndarray of shape (N, 3)

Position vectors in the TEME frame.

v_TEMEndarray of shape (N, 3)

Velocity vectors in the TEME frame.

Returns:

r_ITRFndarray of shape (N, 3)

Transformed position vectors in the ITRF frame.

v_ITRFndarray of shape (N, 3)

Transformed velocity vectors in the ITRF frame.

Notes

This method calls the low-level Cython implementation c_to_ITRF.