Path: SpacecraftEstimation/OrbitEstimation
% Generate the ECI coordinates of an Earth-fixed position at a given time
Type GroundStation for a demo.
Since version 8.
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Usage:
[r, v] = GroundStation( t, omega, rEF );
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Inputs
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t (1) Mean sidereal time (sec)
omega (1) Planet angular rate (rad/s)
rEF (3,1) Earth-fixed position (km)
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Outputs
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r (3,1) Earth-Centered Inertial position (km)
v (3,1) Earth-Centered Inertial velocity (km/s)
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Math: Linear/Cross
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