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