Path: SC/Ephem
% Generate the sun vector in the earth-centered inertial frame.
Low precision formula. Will output the distance to the sun from the
earth if two output arguments are given.
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Form:
[u, r] = SunV1( jD, rSc )
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Inputs
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jD (1,:) Julian date
rSc (3,:) Spacecraft vector in the ECI frame (km)
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Outputs
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u (3,:) Unit sun vector (vector TO the sun)
r (1,:) Distance from origin to sun (km)
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References: The 1993 Astronomical Almanac, U.S. Government
Printing Office, p. C24.
The 2015 Astronomical Almanac, p. C5
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Common: Time/DTSToDTA Common: Time/Date2JD Math: Linear/Mag Math: Linear/Unit Math: Trigonometry/CosD Math: Trigonometry/SinD
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