FFEccHills2Goals:

Path: FormationFlying/Transformation

% Compute geometric goals given Hills frame state and orbit info

   Since version 7.
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   Form:
   [g,D] = FFEccHills2Goals( e, nu, xH, n );
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   ------
   Inputs
   ------
   e                (1)   Eccentricity
   nu               (1)   True anomaly [rad]
   xH              (6,1)  Hills frame state at nu (time-domain)
   n                (1)   Mean orbit rate [rad/s] (optional)
                           * uses time-derivatives if provided
                           * uses nu-derivatives if NOT provided

   -------
   Outputs
   -------
   g                (.)   Data structure of geometric goals
   D               (6,1)  Integration constants for trajectory
   dH               (1)   Integration constant found by setting H = 0 at nu

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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 (c) 2004 Princeton Satellite Systems, Inc. 
   All rights reserved.
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Children:

FormationFlying: EccDynamics/FFEccDH
FormationFlying: EccDynamics/FFEccGoals
FormationFlying: EccDynamics/FFEccProp
FormationFlying: EccDynamics/FFEccRMat
FormationFlying: EccDynamics/FFEccXExt
FormationFlying: EccDynamics/FFEccYExt
FormationFlying: EccDynamics/FFEccZExt
EccDynamics: Derivatives/FFEccDDX
EccDynamics: Derivatives/FFEccDDY
EccDynamics: Derivatives/FFEccDDZ
EccDynamics: Derivatives/FFEccDX
EccDynamics: Derivatives/FFEccDY
EccDynamics: Derivatives/FFEccDZ
FormationFlying: Utility/NuDot
FormationFlying: Utility/Time2NuDomain
FormationFlying: Visual/FFEccAnalyzeShape
Math: Linear/Mag
Math: Solvers/NewtRaph
Math: Trigonometry/WrapPhase

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