Path: SpacecraftEstimation/OrbitEstimation
% Generate the range/range rate measurement matrix and the estimated measurement.
This gives the measurements in the form
y = meas0 + H*dX
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Form:
[meas0, h] = HRangeMeasurement( x, d )
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Inputs
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x (m,:) State estimate [Position;Velocity;clock bias;clock drift;...]
d (n) Measurement data structure
.rSourceECI (3,1) Position of source (ECI)
.vSourceECI (3,1) Velocity of source (ECI)
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Outputs
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meas0 (2*n,1) [range;range rate]
h (2*n,m) H matrix [Hrange;HRange rate]
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Math: Linear/Dot Math: Linear/Mag
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