TransformSEMRToECI:

Path: Orbit/OrbitCoord

% Transform Sun-Earth-Moon rotating (SEMR) state to ECI 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. 

--------------------------------------------------------------------------
   Form:
   [rECI,vECI,m] = TransformSEMRToECI( jD, rSEMR, vSEMR )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   jD            (1,:)    Julian date (days)
   rSEMR         (3,:)    Position vector in SEMR frame          
   vSEMR         (3,:)    Velocity vector in SEMR frame 

   -------
   Outputs
   -------
   rECI          (3,:)    Position vector in ECI frame
   vECI          (3,:)    Velocity vector in ECI frame
   m              {:}     Rotation matrix

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

Children:

AC: ACData/ACTConstants
SC: Ephem/CEcl2Eq
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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