Path: FormationFlying/EccDynamics
% Computes the relative state trajectory in an eccentric reference orbit. A discretized state space model of Gauss' variational equations is used, which is defined by the reference orbital elements. The "GVEDynamics" function is called to get the continuous matrices, and the discretization is done using "C2DZOH.m". Since version 7. -------------------------------------------------------------------------- Form: [dEl,M] = DiscreteGVE( el, dEl0, aC, t ) -------------------------------------------------------------------------- ------ Inputs ------ el (1,6) Reference orbital elements [a,i,W,w,e,M] dEl0 (1,6) Initial relative state aC (3,n) Commanded accelerations [km/s/s] t (1,n+1) Time vector (final time corresponds to final state) ------- Outputs ------- dEl (n+1,6) State trajectory of the satellite in Hill's frame M (n+1,1) Mean anomaly over time t --------------------------------------------------------------------------
Orbit: OrbitMechanics/GVEDynamics SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: BasicOrbit/OrbRate SC: BasicOrbit/Period 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
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