J2Prop:

Path: Orbit/OrbitMechanics

% Propagate an ECI state into the future with the J2 perturbation.
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   Form:
   x = J2Prop( x0, jD, time, gM, options );
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   ------
   Inputs
   ------
   x0              (6,1) Initial state [km; km/s]
   jD               (1)  Initial Julian Date [JD]
   time            (1,:) Time vector [sec]
   gM               (.)  Gravity Model
   options         (1,5) Zonal, Tesseral, Sun, Moon, Drag
   showWaitBar      (1)  Flag. Set to 1 to show wait bar. Default 0.

   -------
   Outputs
   -------
   x               (6,:) Time history of ECI states [km; km/s]

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Children:

Math: Integration/RK4
Orbit: GravityModels/LoadGravityModel
Orbit: RHSOrbit/FOrbHF

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