Path: Orbit/OrbitCoord
% Transform pos. and vel. from Earth Moon barycenter rotating frame to ECI
The EMBR coordinate frame is +x pointing at the earth along
the earth-moon line. +z normal to the earth moon plane
and +y completing the set. Uses MoonV1. Computes the plane
by looking at the moon vector at jD(k) and then 1 day later.
Type
TransformEMBRToECI
for a demo
Since version 10.
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Form:
[xECI,vECI,m] = TransformEMBRToECI( xEMBR, jD )
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Inputs
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jD (1,:) Julian date (days)
rEMBR (3,:) Position vector in EMBR frame
vEMBR (3,:) Velocity vector in EMBR frame
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Outputs
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rECI (6,:) Position vector in ECI frame
vECI (6,:) Velocity vector in ECI frame
m {:} Rotation matrix
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AC: ACData/ACTConstants Orbit: OrbitCoord/BarycenterEarthMoon Orbit: OrbitCoord/ECIToEarthMoonRot Orbit: ThreeBody/CRTBPRHS SC: BasicOrbit/RVFromKepler SC: Ephem/MoonV1 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/DTSToDTA Common: Time/Date2JD Common: Time/JD2000 Math: Linear/Cross Math: Linear/Mag Math: Linear/Unit Math: Trigonometry/CosD Math: Trigonometry/SinD
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