PlotSEMTraj:

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.
-------------------------------------------------------------------------------
   Forms:
   h = PlotSEMTraj( r, frame, jD )
-------------------------------------------------------------------------------

   ------
   Inputs
   ------
   r                (3,:) position vectors (km)
   frame            (1,1) frame of r
                          'SEMRND', 'SEMR', 'ECI'
   jD               (:)   Julian dates

   -------
   Outputs
   -------
   h                (1,1) Figure handle                  

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Children:

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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