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. Since version 10. -------------------------------------------------------------------------- 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 --------------------------------------------------------------------------
Common: Database/Constant SC: Ephem/CEcl2Eq
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