Path: SC/Dynamics
% 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 --------------------------------------------------------------------------
AerospaceUtils: Coord/OmegaLVLH AerospaceUtils: Coord/QLVLH SC: Disturbances/GravityGradientFromR Common: Quaternion/QForm Common: Quaternion/Sa2Q Math: Analysis/Jacobian Math: Linear/Cross Math: Linear/Skew
Back to the SC Module page