SunEarthAttDet:

Path: SpacecraftEstimation/AttitudeEstimation

% An attitude determination system using a sun and earth vector.
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   Form:
   [q, b, p] = SunEarthAttDet( angInc, q, dT, b, p, Q, r, qBToS, sensorData, catalog, fScale )
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   ------
   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

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Children:

SC: Sensor/U2Pix
SpacecraftEstimation: AttitudeEstimation/EKFSSG
SpacecraftEstimation: AttitudeEstimation/Measurements
SpacecraftEstimation: StellarAttDet/AttProp
SpacecraftEstimation: StellarAttDet/DSTM
Common: General/DeBlankLT
Common: General/DispWithTitle
Common: Graphics/NewFig
Common: Graphics/PltStyle
Common: Graphics/TitleS
Common: Graphics/XLabelS
Common: Graphics/YLabelS
Common: Graphics/ZLabelS
Common: Quaternion/Q2Mat
Common: Quaternion/QForm
Common: Quaternion/QFromDQ
Common: Quaternion/QMult
Common: Quaternion/QUnit
Math: Linear/DupVect
Math: Linear/Mag
Math: Linear/Skew
Math: Linear/SkewSymm

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