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
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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]
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Outputs
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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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Math: Integration/RK4
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