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SUPPORT SITE |
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Path: Orbit/OrbitCoord
% Compute the transformation matrix that rotates ECEF to ECI coordinates.
Assumes spherical Earth.
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Form:
M = ECEFToECI( gMT );
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Inputs
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gMT (1,1) Greenwich mean time (radians)
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Outputs
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M (3,3) ECEF to ECI rotation matrix
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