Path: LunarMissions/LunarCoord
% 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.
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Form:
[rECI,vECI,m] = TransformSEMRToECI( jD, rSEMR, vSEMR )
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Inputs
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jD (1,:) Julian date (days)
rSEMR (3,:) Position vector in SEMR frame
vSEMR (3,:) Velocity vector in SEMR frame
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Outputs
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rECI (3,:) Position vector in ECI frame
vECI (3,:) Velocity vector in ECI frame
m {:} Rotation matrix
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SC: Ephem/CEcl2Eq Common: Database/Constant Common: Time/Date2JD
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