CL_fr_H0n2J2000Mat — H0-n to EME2000 matrix
M=CL_fr_H0n2J2000Mat(lon,cjd,[,ut1_utc[,xp,yp[,dPsi,dEps[,conv]]]])
H0-n is a planetocentric inertial frame defined as:
- origin at the center of the planet
- plan OXY is the planet equator plan
- OZ axis goes through the planet North pole
- OX axis is directed according to the direction of the meridian longitude defined by a given longitude (lon), with respect to the meridian of origin of the planet (at a given date)
- OY completes the orthonormal frame
To convert a vector vect_J2000 to vect_H0n, you need to use the (hyper)matrix M' : vect_H0n = M' * vect_J2000
east longitude of X axis of H0-n frame with respect to the meridian of origin of the planet[rad]
CNES Julian Day (+ut/24). Date of the H0-n 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")
H0-n to EME200 matrix (3x3xN)
//conversion of 3 coordinates of Arianne5 ATV launch launch_date = CL_dat_cal2cjd(2006,4,14,19,13,43); H31= [3952930.5 3127929.25 4128420.75 -6244.61914 3103.701904 3619.265381]'; K22 = [-3755942.75 -3308836.25 -4361083.5 6356.73584 -2869.25708 -3293.44238]'; H41 = [-1877905.62 -3909427.35 -5026024.14 7427.6591 -1541.7598 -1576.4651]'; coord_H03 = [H31 K22 H41]; position_H03 = coord_H03(1:3,:); velocity_H03 = coord_H03(4:6,:); // Launch pad ELA3 at the French Guayana Space Centre (CSG) with reference to WGS72 - {8} CSG = [CL_deg2rad(-52.7686020300),CL_deg2rad(5.2403222778),-4.215] [deg], latitude of launch pad ELA3 at the French Guayana Space Centre (CSG) with reference to WGS72 - {8} M = CL_fr_H0n2J2000Mat(CSG(1),launch_date); position_J2000 = M*position_H03; velocity_J2000 = M*velocity_H03; coord_J2000 = [position_J2000;velocity_J2000];