FFEccYExt:

Path: FormationFlying/EccDynamics

% Compute extreme y-values and associated true anomalies for given relative motion.

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   Form:
   [y,nu] = FFEccYExt( e, D, dH, epsilon, nMax )
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   ------
   Inputs
   ------
   e                (1)   Eccentricity
   D               (6,1)  Integration constants computed from i.c.'s
   dH               (1)   Integration constant found by setting H = 0 at nu0
   epsilon          (1)   Angular tolerance [rad]
   nMax             (1)   Maximum number of iterations

   -------
   Outputs
   -------
   y               (1,#)  Extreme values of along-track offsets [km]
   nu              (1,#)  True anomaly where extreme along-track offsets occur [rad]

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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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   Since version 7.
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Children:

FormationFlying: EccDynamics/FFEccDH
FormationFlying: EccDynamics/FFEccGoals
FormationFlying: EccDynamics/FFEccProp
FormationFlying: EccDynamics/FFEccRMat
EccDynamics: Derivatives/FFEccDDY
EccDynamics: Derivatives/FFEccDY
FormationFlying: Visual/FFEccAnalyzeShape
Math: Linear/Mag
Math: Solvers/NewtRaph
Math: Trigonometry/WrapPhase

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