Path: FormationFlying/EccDynamics
% Integration constants for eccentric relative motion
Compute integration constants for homogeneous solution to LTV diff eqs of
relative orbit motion.
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Form:
[D,dH,R] = FFEccIntConst( xH0, nu0, e );
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Inputs
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xH0 (6,1) Initial state in Hills frame. Velocity terms
are expressed as derivatives with respect to
true anomaly, rather than time.
nu0 (1) True anomaly (at initial state) [rad]
e (1) Eccentricity
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Outputs
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D (6,1) Vector of integration constants
dH (1) Integration constant found by setting H = 0 at nu0
R (6,6) State transition matrix
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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: EccDynamics/FFEccRMat
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