Path: SC/Ephem
% Computes the matrix that transforms from ECI to areographic axes.
If two arguments are entered it will add secular components.
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Form:
g = MarsRot( jD, useSec )
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Inputs
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jD Julian Date
useSec Add secular variations
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Outputs
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g ECI To Areographic matrix
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References: Escobal, P. R., Methods of Orbit Determination, Krieger,
pp. 419-421.
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Common: Time/DTAToDTS Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2Date Math: MathUtils/R2P5
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