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
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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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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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