RHSEarthOrbitUKF:

Path: SpacecraftEstimation/DemoFuns

% Point mass gravity model.
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   Form:
   d    = RHSEarthOrbitUKF;
   xDot = RHSEarthOrbitUKF( x, t, d ) 
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   ------
   Inputs
   ------
   x             (6,1)  State vector [r;v]
   t             (1,1)  Time (unused)
   d              (.)   Data structure
                        .mu (1,1) Gravitational constant (default earth)
                        .a  (3,1) Acceleration vector in ECI Frame

   -------
   Outputs
   -------
   x             (6,1)  State vector derivative d[r;v]/dt

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Children:

Math: Linear/Mag

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