Path: FormationFlying/Utility
% Convert a relative state from the time-domain to the nu-domain.
This changes only the relative velocity portion (elements 4 thru 6) of
the state vector.
For this conversion, the velocity terms are divided by the
time-derivative of the true anomaly (nu).
Since version 7.
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Form:
x = Time2NuDomain( x, n, e, nu )
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Inputs
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x (6,1) Relative State in time-domain, 6x1 vector,
[position;velocity]
n (1) Mean orbit rate [rad/s]
e (1) Eccentricity
nu (1) True anomaly [rad]
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Outputs
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x (6,1) Relative State in nu-domain, 6x1 vector,
[position;velocity]
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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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FormationFlying: Utility/NuDot
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