FFEccHills2Goals:
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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
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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
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Outputs
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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/FFEccGoals
FormationFlying: EccDynamics/FFEccProp
FormationFlying: EccDynamics/FFEccRMat
FormationFlying: EccDynamics/FFEccXExt
FormationFlying: EccDynamics/FFEccYExt
FormationFlying: EccDynamics/FFEccZExt
FormationFlying: Utility/Time2NuDomain
Math: Trigonometry/WrapPhase
