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.
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Form:
[rSEMR,vSEMR,m] = TransformECIToSEMR( jD, rECI, vECI )
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Inputs
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rECI (6,:) Position vector in ECI frame
vECI (6,:) Velocity vector in ECI frame
jD (1,:) Julian date (days)
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Outputs
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rSEMR (6,:) Position vector in SEMR frame
vSEMR (6,:) Velocity vector in SEMR frame
m {:} Rotation matrix
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AC: ACData/ACTConstants SC: BasicOrbit/RVFromKepler SC: Ephem/CEcl2Eq SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/CellToMat Common: General/DeBlankLT Common: General/DeleteCell Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Time/JD2000
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