Path: FormationFlying/EccDynamics
% Compute integration constant dH for homogeneous solution to LTV diff eqs
of relative orbit motion.
Since version 7.
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Form:
dH = FFEccDH( nu0, e );
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Inputs
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nu0 (1,N) True anomaly (at initial state) [rad]
e (1) Eccentricity
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Outputs
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dH (1,N) Integration constant found by setting H = 0 at nu0
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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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