Path: SpacecraftEstimation/OrbitEstimation
% Perform batch least-squares method for orbit determination.
--------------------------------------------------------------------------
Form:
[x0,P0,dx0] = BatchLSQOD( x0G, zM, W, d, opts );
--------------------------------------------------------------------------
------
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.
--------------------------------------------------------------------------
Common: General/DeleteSuffix Math: Analysis/Jacobian Math: Linear/Mag
Back to the SpacecraftEstimation Module page