Path: Orbit/Visualization
% Plot an orbit track in the Sun/Earth-Moon Rotating System.
The input vectors are in the ECI frame. Has a built-in demo for an orbit
with an apogee of 400,000 km, a perigee of 7000 km, and a duration of 5 days.
Type PlotSEMTraj for a demo.
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Forms:
h = PlotSEMTraj( r, frame, jD )
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Inputs
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r (3,:) position vectors (km)
frame (1,1) frame of r
'SEMRND', 'SEMR', 'ECI'
jD (:) Julian dates
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Outputs
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h (1,1) Figure handle
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AC: ACData/ACTConstants Orbit: ThreeBody/CRTBPRHS SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/DeleteCell Common: General/Watermark Common: Graphics/NewFig
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