SEMIToSEMR:

Path: Orbit/OrbitCoord

% Transform pos. and vel. from inertial heliocentric frame to
   Sun-Earth/Moon barycentered rotating frame.
   
   The SEMR coordinate frame has xy in the ecliptic plane.
     +x points at the earth along the Sun-Earth line. 
     +z normal to the ecliptic plane
     +y completes the right-handed system. 

   Uses an analytic formula for the ecliptic longitude to define the
   rotation in the xy plane. Uses a constant value of the Earth rotation
   rate around the sun to transform the velocity.

   Since version 10.
--------------------------------------------------------------------------
   Form:
   [rSEMR,vSEMR,m] = SEMIToSEMR( jD, rSEMI, vSEMI )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   jD            (1,:)       Julian date (days)
   rSEMI         (3,:)       Position vector in SEMI frame          
   vSEMI         (3,:)       Velocity vector in SEMI frame          

   -------
   Outputs
   -------
   rSEMR         (6,:)       Position vector in SEMR frame
   vSEMR         (6,:)       Velocity vector in SEMR frame
   m              {:}        Rotation matrix

--------------------------------------------------------------------------

Children:

Common: Database/Constant

Back to the Orbit Module page