CL_fr_G502J2000Mat — Gamma50 (Veis) to EME2000 (J2000) matrix
M=CL_fr_G502J2000Mat(cjd,[,ut1_utc[,xp,yp[,dPsi,dEps[,conv]]]])
Gamma50 (Veis) (Veis frame at date) is defined as:
- origin at the center of the Earth
- plan OXY is the true equatorial plan of the date
- OX axis goes through the Veis equinox of the date
- OZ axis goes through the true celestial pole of the date
- OY completes the orthonormal frame
To convert a vector vect_J2000 to vect_G50, you need to use the (hyper)matrix M' : vect_G50 = M' * vect_J2000
CNES Julian Day (+ut/24). Date of the Gamma50 (Veis) frame. (1xN)
(optional) ut1-utc [seconds] (default is 0) (1xN)
(optional) x polar coordinate [radians] (default is 0) (1xN)
(optional) y polar coordinate [radians] (default is 0) (1xN)
(optional) Nutation corrections [radians] (default is 0) (1xN)
(optional) Nutation corrections [radians] (default is 0) (1xN)
(optional) Convention IERS. Only iers 1996 (Lieske/Wahr) is implemented (default is "iers_1996")
GAMMA50 to J2000 matrix (3x3xN)
//conversion of 3 coordinates //tpv: time, position and velocity tpv = [3952930.5 3127929.25 4128420.75 -6244.61914 3103.701904 3619.265381]'; tpv(:,2) = [3945680.5 3125978.25 5687420.75 -6654.61914 4563.701904 3123.265381]'; cjd = 20870+125/86400; position_veis = tpv(1:3,:); velocity_veis = tpv(4:6,:); M = CL_fr_G502J2000Mat(cjd); position_J2000 = M*position_veis; velocity_J2000 = M*velocity_veis; coord_J2000 = [position_J2000;velocity_J2000]; See 'CelestLab > Demos > ORBIT_PROPERTIES > beta_sun' for more examples