FFEccGoals:

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   Compute integration constants and initial state given the geometric goals.

   Since version 7.
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   Form:
   [D,xH0] = FFEccGoals( e, goals );                             % (2 inputs)
                 -or-
   [D,xH0] = FFEccGoals( e, y0, xMax, nu_xMax, zMax, nu_zMax );  % (6 inputs)
                 -or-
   [D,xH0] = FFEccGoals( e, y0, x, y, nu_xy,   zMax, nu_zMax );  % (7 inputs)
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   ------
   Inputs
   ------
   e                (1)   Eccentricity
   goals            (.)   Geometric goal data structure
                             * Two different sets of in-plane parameters supported
                                - { y0, xMax, nu_xMax }
                                - { y0, x, y, nu_xy   }
                             * Two different sets of out-of-plane parameters supported

           -or-
   
   e                (1)   Eccentricity
   y0               (1)   Along-track offset [km]
   xMax             (1)   Maximum radial offset [km]
   nu_xMax          (1)   True anomaly where maximum radial offset occurs [rad]
   zMax             (1)   Maximum cross-track amplitude [km]
   nu_xMax          (1)   True anomaly where maximum cross-track amplitude occurs [rad]

           -or-
   
   e                (1)   Eccentricity
   y0               (1)   Along-track offset [km]
   x                (1)   Radial position at true anomaly "nu_xy"      [km]
   y                (1)   Along-track position at true anomaly "nu_xy" [km]
   nu_xy            (1)   True anomaly where  position occurs     [rad]
   zMax             (1)   Maximum cross-track amplitude [km]
   nu_xMax          (1)   True anomaly where maximum cross-track amplitude occurs [rad]

   -------
   Outputs
   -------
   D               (6,1)  Integration constants computed from i.c.'s
   xH0             (6,1)  Hills frame state at nu = 0

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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/FFEccProp
FormationFlying: EccDynamics/FFEccRMat
FormationFlying: EccDynamics/FFEccYExt
Math: Linear/Mag
Math: Trigonometry/WrapPhase