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Path: SpacecraftEstimation/AttitudeEstimation
% An attitude determination system using a sun and earth vector. -------------------------------------------------------------------------- Form: [q, b, p] = SunEarthAttDet( angInc, q, dT, b, p, Q, r, qBToS, sensorData, catalog, fScale ) -------------------------------------------------------------------------- ------ Inputs ------ angInc (n,1) Angular increments q (4,1) Attitude quaternion dT (1,1) Time step b (3,1) Bias p (6,6) State covariance matrix Q (6,6) State noise covariance r (1,1) Measurement noise qBToS (4,1) Quaternion from body to sensor axes sensorData (m,3) Vector of [intensity,xloc,yloc] catalog (3,p) Catalog of unit vectors fScale Sensor scale factor ------- Outputs ------- q (4,1) Attitude quaternion b (3,1) Bias p (6,6) State covariance matrix --------------------------------------------------------------------------
Common: Quaternion/QFromDQ SpacecraftEstimation: AttitudeEstimation/EKFSSG SpacecraftEstimation: AttitudeEstimation/Measurements SpacecraftEstimation: StellarAttDet/AttProp SpacecraftEstimation: StellarAttDet/DSTM
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