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.



   for a demo

   Since version 10.
   [xECI,vECI,m] = TransformEMBRToECI( xEMBR, jD )

   jD            (1,:)       Julian date (days)
   rEMBR         (3,:)       Position vector in EMBR frame          
   vEMBR         (3,:)       Velocity vector in EMBR frame          
   rECI          (6,:)       Position vector in ECI frame
   vECI          (6,:)       Velocity vector in ECI frame
   m              {:}        Rotation matrix



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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