Path: SpacecraftEstimation/OrbitEstimation
% Range and range rate to an Earth target.
Includes Earth rotational rate.
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Form:
[y, rT] = MeasEarthTarget( x, d )
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Inputs
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x (3,1) Position of spacecraft (km)
d (.) Data structure
.jD0 (1,1) Julian date
.omegaSkew (3,3) Skew symmetric matrix for earth rate
.t (1,1) Time (s)
.rEF (3,1) Earth fixed target location
.noise1Sigma (2,1) [range;range rate] 1 sigma (km,km/s)
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Outputs
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y (2,1) [range;range rate]
rT (3,1) Target on Earth in ECI frame (km)
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SC: Ephem/EOfE SC: Ephem/EarthRot SC: Ephem/GMSTime SC: Ephem/MSidDay SC: Ephem/NutDelta SC: Ephem/ObOfE Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2000 Common: Time/JD2T Common: Time/JDToMidnight Math: Linear/Mag Math: Linear/Skew Math: Linear/Unit Math: MathUtils/R2P5 Math: Trigonometry/CosD Math: Trigonometry/SinD
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