SEMRToSEMI:

Path: Orbit/OrbitCoord

% Transform from Sun-Earth/Moon rotating to inertial frame
 Transform pos. and vel. from Sun-Earth/Moon barycentered rotating frame to
 inertial heliocentric 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.
--------------------------------------------------------------------------
   Form:
   [rSEMI,vSEMI,m] = SEMRToSEMI( jD, rSEMR, vSEMR )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   jD            (1,:)       Julian date (days)
   rSEMR         (6,:)       Position vector in SEMR frame
   vSEMR         (6,:)       Velocity vector in SEMR frame

   -------
   Outputs
   -------
   rSEMI         (3,:)       Position vector in SEMI frame          
   vSEMI         (3,:)       Velocity vector in SEMI frame          
   m              {:}        Rotation matrix

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

Children:

AC: ACData/ACTConstants
Orbit: OrbitCoord/SEMIToSEMR
SC: SCData/sCTConstants
Common: CommonData/Constants
Common: CommonData/xSplashSmall
Common: Database/Constant
Common: General/DeleteCell
Common: Time/DTSToDTA
Common: Time/Date2JD

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