Path: FormationFlying/EccDynamics
% Computes the relative state trajectory in an eccentric reference orbit. A discretized state space model of Hills equations is used, which is defined by the mean orbit rate (n), eccentricity (e), and true anomaly history. The "FFEccLinOrb" function is called, and the discretization is done using "C2DZOH.m". Since version 7. -------------------------------------------------------------------------- Form: [xS,nu] = FFEccDiscreteHills( e, n, x0, nu0, aC, t ) -------------------------------------------------------------------------- ------ Inputs ------ e (1) Eccentricity n (1) Mean orbit rate (rad/sec) x0 (6,1) Initial relative state nu0 (1) Initial true anomaly aC (3,n) Commanded accelerations t (1,n+1) Time vector (final time corresponds to final state) ------- Outputs ------- xS (6,n+1) State trajectory of the satellite in Hill's frame --------------------------------------------------------------------------