OrbitODGenObs:

Path: SpacecraftEstimation/OrbitEstimation

% Generates a set of observations given an initial orbit state

   Since version 8.
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   Form:
   [z,xS,time] = OrbitODGenObs( x0, d );
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   ------
   Inputs
   ------
   x0            (6,1)    Initial orbit state (ECI position; ECI velocity)
   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 prop. [sec]
                   .obsTime (1,nObs) Observation times [sec] (MET)
                   .rGS     (1,nObs) ECI pos. of grnd. stn. at obs. times
                   .vGS     (1,nObs) ECI pos. of grnd. stn. at obs. times
                   .accTime (1,nC)   Times of applied accels. [sec] (MET)
                   .acc     (3,nC)   Applied accel. vector (3x1) [km/s/s]

   -------
   Outputs
   -------
   z             (M,1)  Vector of range and range rate observations 
                          (M = 2*nObs)
   xS            (6,N)  Predicted time history of orbit state at 
                          all obs. times and control times (N = nC+nObs)
   time          (1,N)  Time vector associated with xS history.

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Children:

Math: Integration/RK4

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