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SUPPORT SITE |
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SUPPORT SITE |
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Path: Orbit/Visualization
% Plot an orbit track in the 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.
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Forms:
EarthMoonRotFrame( r, jD, scale, lagrange, lunarCone )
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Inputs
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r (3,:) ECI position vectors (km) or
(1,6) elements
jD (:) Julian dates
scale (1,2) Planet scale (optional, default is [1 1])
lagrange (1,1) If entered draw lagrange points
lunarCone (1,3) [lat, lon, angle]
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Outputs
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none
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AerospaceUtils: Coord/LatLonToR Common: ComponentModels/Cone Common: Database/Constant Common: Graphics/Axis3D Common: Graphics/Map Common: Graphics/NewFig Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Time/JD2000 Math: Linear/Cross Math: Linear/Unit Orbit: OrbitCoord/RPRA2AE Orbit: OrbitMechanics/RVOrbGen SC: Ephem/LagrangePointsL1ToL5 SC: Ephem/MoonEl SC: Ephem/MoonV1
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