BatchLSQOD:

Path: SpacecraftEstimation/OrbitEstimation

% Perform batch least-squares method for orbit determination.

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   Form:
   [x0,P0,dx0] = BatchLSQOD( x0G, zM, W, d, opts );
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   ------
   Inputs
   ------
   x0G           (6,1)    Guess for epoch state x0, ECI position (km) and
                             velocity (km/s) vector.
   zM            (N,1)    Vector of measurements.
   W            (6N,6N)   Diagonal weighting matrix. Should be inverse of
                          measurement variances.
   d              (.)     Data structure for observation function. Fields:
                   .name    (:)      Name of observation function.
                   .mu      (1)      Value for gravitational parameter mu
                   .dT      (1)      Desired time step for orbit propagation [sec]
                   .obsTime (1,nObs) Observation times [sec] (MET)
                   .rGS     (1,nObs) ECI position of ground station at observation times
                   .vGS     (1,nObs) ECI position of ground station at observation times
                   .accTime (1,nC)   Time vector of applied accelerations [sec] (MET)
                   .acc     (1,nC)   Applied acceleration vector (3x1) [km/s/s]

   opts           (.)     Data structure of options for this algorithm.
                   .tol     (1)      Tolerance for size of dx0 (differential corrector)
                   .maxIter (1)      Maximum allowed iterations

   -------
   Outputs
   -------
   x0            (6,1)  Solution for epoch state x0.
   P0            (6,6)  Covariance matrix.
   dx0           (6,1)  Last differential correction term.

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Children:

Common: General/DeleteSuffix
Math: Analysis/Jacobian
Math: Linear/Mag

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