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
--------------------------------------------------------------------------
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
Back to the Orbit Module page