Path: CubeSat/Visualization
% Plot the orbital state in 3D with an Earth map.
Note that the location relative to the map is only accurate for
Earth-fixed frame input. Enter time and Julian date to compute the
Earth-fixed positions from ECI data automatically.
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Form:
[h, l] = PlotOrbit( rEF )
[h, l] = PlotOrbit( rECI, t, jD0 )
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Inputs
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r (3,m) Position vectors (km)
or
{n} Cell array of position matrices for multiple satellites
t (1,:) Time array (sec)
jD0 (1,1) Epoch Julian date
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Output
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h (1,1) Figure handle
l (1,n) Handle to orbit lines
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See also: LoadEarthMap
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AerospaceUtils: Coord/ECIToEF AerospaceUtils: Coord/LLAToECEF Orbit: OrbitMechanics/Period SC: Ephem/SunV1 SC: Ephem/TerminatorLine SC: Visualization/LoadEarthMap Common: Graphics/AssignColors Common: Time/Date2JD Common: Time/JD2T
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