PropEph:

Path: Orbit/OrbitMechanics

% Propagates the ephemeris one step.

   Since version 1.
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   Form:
   [el, jd, uSun, uMoon, uNadir, radiusEarth] = PropEph( elStart, jd, dT, mu )
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   ------
   Inputs
   ------
   elStart      (1,6)     Initial Keplerian orbital elements [a,i,W,w,e,M] (angles in rad)
   jd                     Julian date (days)
   dT           (:)       Time step (sec)
   mu                     Gravitational parameter for the earth

   -------
   Outputs
   -------
   el           (6,:)     Keplerian orbital elements
   jd                     Julian date (days)
   uSun         (3,:)     Sun unit vector
   uMoon        (3,:)     Moon unit vector
   uNadir       (3,:)     Earth unit vector
   radiusEarth  (:)       Earth angular radius (rad)

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Children:

Common: Graphics/Plot2D
Math: Linear/DupVect
Math: Linear/Mag
Math: Linear/Unit
SC: BasicOrbit/El2RV
SC: Ephem/MoonV2
SC: Ephem/SunV1

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