Path: FormationFlying/EccDynamics
% Compute Hills frame state at nu given integ. constants and eccentricity.
Since version 7.
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Form:
xH = FFEccProp( D, nu, e, dH )
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Inputs
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D (6,1) Integration constants computed from i.c.'s
nu (1,n) True anomaly [rad]
e (1) Eccentricity
dH (1) Integration constant found by setting H = 0 at nu0
(Optional. If not provided, it will be computed
using the first nu supplied)
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Outputs
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xH (6,n) Hills frame state at nu. Velocity terms
are expressed as derivatives with respect to
true anomaly, rather than time.
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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/FFEccRMat
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