SeqBatchLSQOD:

Path: SpacecraftEstimation/OrbitEstimation

% Perform sequential batch least-squares method for orbit determination.

   Since version 8.
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   Form:
   [x0,P0,dx0] = SeqBatchLSQOD( x0G, zMNew, WNew, d, opts );
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   Inputs
   ------
   dx0           (6,1)    Last computed differential correction term.
   P0Inv         (6,6)    Inverse of P0, last computed covariance matrix.
   x0            (6,1)    Last computed solution for epoch state x0.
   zMNew         (N,1)    Vector of new measurements.
   WNew         (6N,6N)   Diagonal weighting matrix for new measurements. 
                             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:

Math: Analysis/Jacobian

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