$LastChangedDate: 27-Juil-2011 $

# CL_fr_H0n2J2000Mat

H0-n to EME2000 (J2000) transformation matrix

## Calling Sequence

       M=CL_fr_H0n2J2000Mat(lon,cjd,[,ut1_utc[,xp,yp[,dPsi,dEps[,conv]]]])

## Description

- Computes the frame transformation matrix M from H0-n to EME2000.

  By convention, multiplying M by coordinates relative to H0-n yields coordinates relative to EME2000.

- See Reference Frames for more details on the definition of reference frames.

## Parameters

lon:

  east longitude that defines the X axis of the H0-n frame [rad]

cjd:

  modified julian day from 1950.0 (UTC). Reference time for H0-n frame. (1xN)

ut1_utc :

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

xp :

  (optional) x polar coordinate [radians] (default is 0) (1xN)

yp :

  (optional) y polar coordinate [radians] (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:

  H0-n to EME200 transformation matrix (3x3xN)

## Authors

- CNES - DCT/SB

## See also

- CL_fr_ter2J2000Mat

- CL_fr_G502terMat

## Examples

    // Conversion of 3 coordinates of Arianne5 ATV launch
    launch_date = CL_dat_cal2cjd(2006,4,14,19,13,43);
    pos_H31 = [3952930.5 ; 3127929.25 ; 4128420.75];
    pos_K22 = [-3755942.75 ; -3308836.25 ; -4361083.5 ];
    pos_H41 = [-1877905.62 ; -3909427.35 ; -5026024.14 ];
    vel_H31 = [-6244.61914 ; 3103.701904 ; 3619.265381];
    vel_K22 = [6356.73584 ; -2869.25708 ; -3293.44238];
    vel_H41 = [7427.6591 ; -1541.7598 ; -1576.4651];
    pos_H03 = [pos_H31 pos_K22 pos_H41] ;
    vel_H03 = [vel_H31 vel_K22 vel_H41];
    // Launch pad ELA3 at the French Guayana Space Centre
    CSG = [CL_deg2rad(-52.768602),CL_deg2rad(5.240322),-4.215];
    M = CL_fr_H0n2J2000Mat(CSG(1),launch_date);
    pos_J2000 = M*pos_H03;
    vel_J2000 = M*vel_H03;