Path: SCPro/DynamicalModels
% Compute the eigenvalues for a gravity gradient stabilized spacecraft. We assume it is in the LVLH orientation. -------------------------------------------------------------------------- Form: [e, a] = GravityGradientEigenvalues( inr, r, v, mu ) -------------------------------------------------------------------------- ------ Inputs ------ inr (3,3) Inertia matrix r (3,1) r in ECI v (3,1) v in ECI mu (1,1) Gravitational Parameter ------- Outputs ------- e (6,1) Eigenvalues a (6,6) State matrix --------------------------------------------------------------------------
AC: ACData/ACTConstants AerospaceUtils: Coord/OmegaLVLH AerospaceUtils: Coord/QLVLH SC: Disturbances/GravityGradientFromR SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/CellToMat Common: General/DeleteCell Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Quaternion/Mat2Q Common: Quaternion/QForm Common: Quaternion/Sa2Q Math: Analysis/Jacobian Math: Linear/Cross Math: Linear/Mag Math: Linear/Skew Math: Linear/Unit
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