TransformECIToSEMR:

Path: Orbit/OrbitCoord

% Transform ECI pos. and vel. to Sun-Earth-Moon rotating (SEMR) frame.
   
   The SEMR coordinate frame is +x pointing at the earth along
   the sun-earth line. +z normal to the sun-earth plane
   and +y completing the set. Uses CEcl2Eq. 

   Type

   TransformECIToSEMR

   for a demo

   Since version 10.
--------------------------------------------------------------------------
   Form:
   [rSEMR,vSEMR,m] = TransformECIToSEMR( jD, rECI, vECI )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   rECI          (6,:)       Position vector in ECI frame
   vECI          (6,:)       Velocity vector in ECI frame
   jD            (1,:)       Julian date (days)
   -------
   Outputs
   -------
   rSEMR         (6,:)       Position vector in SEMR frame          
   vSEMR         (6,:)       Velocity vector in SEMR frame          
   m              {:}        Rotation matrix

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

Children:

Common: Database/Constant
Common: Graphics/Plot3D
Common: Time/JD2000
SC: Ephem/CEcl2Eq

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