FFEccProp:

Path: FormationFlying/EccDynamics

% Compute Hills frame state at nu given integ. constants and eccentricity.

   Since version 7.
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   Form:
   xH = FFEccProp( D, nu, e, dH )
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   ------
   Inputs
   ------
   D               (6,1)  Integration constants computed from i.c.'s
   nu              (1,n)  True anomaly [rad]
   e                (1)   Eccentricity
   dH               (1)   Integration constant found by setting H = 0 at nu0
                          (Optional. If not provided, it will be computed
                          using the first nu supplied)
   -------
   Outputs
   -------
   xH              (6,n)  Hills frame state at nu. Velocity terms
                             are expressed as derivatives with respect to
                             true anomaly, rather than time.

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   References: Inalhan, Tillerson, How, "Relative Dynamics and Control of
   Spacecraft Formations in Eccentric Orbits", Journal of Guidance,
   Control & Dynamics, Vol.25, No.1, Jan-Feb 2002.
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	  Copyright 2004 Princeton Satellite Systems, Inc.
   All rights reserved.
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Children:

FormationFlying: EccDynamics/FFEccDH
FormationFlying: EccDynamics/FFEccRMat

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