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Path: SpacecraftEstimation/StellarAttDet
% Quaternion state transition matrix Generates the state transition matrix to propagate a quaternion one step assuming that the angular velocity is constant. ------------------------------------------------------------------------ Form: phi = STM( w, dT ) ------------------------------------------------------------------------ ------ Inputs ------ w (3,1) Angular rate dT (1,1) Time change ------- Outputs ------- phi (4,4) State transition matrix ------------------------------------------------------------------------
Math: Linear/Mag Math: Linear/SkewSymm
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