Path: Orbit/OrbitControl
% Compute control acceleration for low thrust orbit raising The control has four discrete modes: mode 0 is semi-major axis raising. mode 1 is ascending node. mode 2 is inclination. mode 3 is zero acceleration. The mode sequence is suitable if your semi-major axis is increasing and inclination is increasing. The angular width is the allowable control region around the optimal true anomaly, which is pi/2 and 3*pi/2 for longitude of the ascending node and 0 and pi for inclination. -------------------------------------------------------------------------- Form: [a,mode,el] = LowThrustControl( x, mode, elTarget, aMag, tol, angWidth ) -------------------------------------------------------------------------- ------ Inputs ------ x (6,1) [r;v] mode (1,1) Mode index, 0, 1, 2, or 3 elTarget (1,6) Elements target [a i W w e M] aMag (1,1) Acceleration magnitude tol (1,1) Maneuver tolerance angWidth (1,1) Width of angles for maneuvers (rad) ------- Outputs ------- a (3,1) Acceleration vector mode (1,1) Mode index el (1,6) Current elements computed from x --------------------------------------------------------------------------
SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/RV2El Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/Cross Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit
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