Path: Orbit/OrbitCoord
% Transform from Sun-Earth/Moon rotating to inertial frame
Transform pos. and vel. from Sun-Earth/Moon barycentered rotating frame to
inertial heliocentric frame.
The SEMR coordinate frame has xy in the ecliptic plane.
+x points at the earth along the Sun-Earth line.
+z normal to the ecliptic plane
+y completes the right-handed system.
Uses an analytic formula for the ecliptic longitude to define the
rotation in the xy plane. Uses a constant value of the Earth rotation
rate around the sun to transform the velocity.
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Form:
[rSEMI,vSEMI,m] = SEMRToSEMI( jD, rSEMR, vSEMR )
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Inputs
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jD (1,:) Julian date (days)
rSEMR (6,:) Position vector in SEMR frame
vSEMR (6,:) Velocity vector in SEMR frame
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Outputs
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rSEMI (3,:) Position vector in SEMI frame
vSEMI (3,:) Velocity vector in SEMI frame
m {:} Rotation matrix
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AC: ACData/ACTConstants Orbit: OrbitCoord/SEMIToSEMR SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/xSplashSmall Common: Database/Constant Common: General/DeleteCell Common: Time/DTSToDTA Common: Time/Date2JD
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