Path: FormationFlying/EccDynamics
% Linearized relative motion in an eccentric reference orbit Compute the continous A,B matrices for linearized relative motion in an eccentric reference orbit. Discretizes with a zero-order hold if dT provided. xDot = a*x + b*u -------------------------------------------------------------------------- Form: [a,b] = FFEccLinOrb( n, nu, e, dT ); -------------------------------------------------------------------------- ------ Inputs ------ n (1) Mean orbit rate [rad/s] nu (1) True anomaly [rad] e (1) Eccentricity dT (1) Time-step for discretization (optional) ------- Outputs ------- a (6,6) Plant matrix b (6,3) Input matrix -------------------------------------------------------------------------- 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. --------------------------------------------------------------------------
FormationFlying: Utility/NuDot Common: Control/C2DZOH
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