Path: FormationFlying/EccDynamics
% 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
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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]
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Outputs
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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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FormationFlying: EccDynamics/FFEccDH FormationFlying: EccDynamics/FFEccProp FormationFlying: EccDynamics/FFEccRMat FormationFlying: EccDynamics/FFEccYExt EccDynamics: Derivatives/FFEccDDY EccDynamics: Derivatives/FFEccDY FormationFlying: Visual/FFEccAnalyzeShape Math: Linear/Mag Math: Solvers/NewtRaph Math: Trigonometry/WrapPhase
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