Name

CL_fr_teme2J2000Mat — TEME to J2000 matrix

Calling Sequence

   M=CL_fr_teme2J2000Mat(cjdutc[,ut1_utc[,dPsi,dEps[,conv]]])
   
   

Description

  • Computes the frame transfer matrix from TEME (true equator and mean equinox) to EME2000 (J2000) frame.
  • To convert a vector vect_TEME to vect_J2000, you need to use the (hyper)matrix M : vect_J2000 = M * vect_TEME

    To convert a vector vect_J2000 to vect_TEME, you need to use the (hyper)matrix M' : vect_TEME = M' * vect_J2000

  • Last update : 27/6/2008

Parameters

cjdutc:

CNES Julian Date (1950) in TUC time (1xN)

ut1_utc :

(optional) ut1-utc [seconds] (default is 0) (1xN)

dPsi :

(optional) Nutation corrections [radians] (default is 0) (1xN)

dEps :

(optional) Nutation corrections [radians] (default is 0) (1xN)

conv :

(optional) Convention IERS. Only iers 1996 (Lieske/Wahr) is implemented (default is "iers_1996")

M:

TEME to EME2000 matrix (3x3xN)

Authors

CNES - DCT/SB

Bibliography

1 IERS Conventions (1996), Dennis D. McCarthy

2 Explanatory Supplement to the Astronomical Almanac, Seidelman (1992)

3 Vallado, D.A., J.H. Seago, "The coordinate frames of the US Space Objects Catalogs", AIAA 2000-4025

See also

CL_mod_precessionMatrix, CL_mod_nutationMatrix, CL_mod_equinoxesEquation, CL_fr_ter2J2000Mat, CL_fr_H0n2J2000Mat

Examples

cart_teme = [1 2 3 4 5 6]'
pos_teme = cart_teme(1:3)
vel_teme = cart_teme(4:6)
M = CL_fr_teme2J2000Mat(20557+70254/86400.0)
pos_j2000 = M*pos_teme
vel_j2000 = M*vel_teme
cart_j2000 = [pos_j2000;vel_j2000]