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 --------------------------------------------------------------------------
FormationFlying: EccDynamics/FFEccLinOrb FormationFlying: Utility/NuDot SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M Common: CommonData/SwooshWatermark Common: Control/C2DZOH Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/DupVect Math: Trigonometry/UnwrapPhase
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