FFIntegrate:

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   Integrate two neighboring orbits, with applied relative accelerations

   Since version 7.
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   Form:
   [xRef,xRel,xH] = FFIntegrate( xRef0, xRel0, time, aH );
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   Inputs
   ------
   xRef0           (6,1)  Initial ECI position & velocity of reference sat
   xRel0           (6,1)  Initial ECI position & velocity of relative sat
   time            (1,N)  Time vector (seconds)
   aH              (3,N)  Relative accel. in Hill's frame over time [km/s/s]

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   Outputs
   -------
   xRef            (6,N)  Integrated ECI position and velocity of reference
   xRel            (6,N)  Integrated ECI position and velocity of relative
   xH              (6,N)  Relative Hill's frame position and velocity

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	  Copyright 2004 Princeton Satellite Systems, Inc.
    All rights reserved.
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Children:

FormationFlying: Coord/GetHillsMats
FormationFlying: Transformation/ECI2Hills
Math: Integration/RK4TI
Math: Linear/Mag