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SUPPORT SITE |
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Path: SpacecraftEstimation/StellarAttDet
% A stellar attitude determination system.
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Form:
[q, b, p] = StellarAttDetEKF( angInc, q, dT, b, p, Q, r, qBToS,
starDataMeas, starData, fScale )
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Inputs
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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
starDataMeas (3,m) Vector of [intensity;xloc;yloc]
starData (1,1) Star Data
.starMatrix (4,n) Star catalog containing n stars stored as [intensity;u]
.starID (1,m) Identified stars
fScale Sensor scale factor
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Outputs
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q (4,1) Attitude quaternion
b (3,1) Bias
p (6,6) State covariance matrix
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Common: Quaternion/QFromDQ SpacecraftEstimation: AttitudeEstimation/EKFSSG SpacecraftEstimation: StellarAttDet/AttProp SpacecraftEstimation: StellarAttDet/DSTM SpacecraftEstimation: StellarAttDet/StarMeasurement
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