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   Converts angles in the orbit plane to right ascension and declination
   in the ECI frame.
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   Form:
   [rA, dec] = AB2RADec( i, L, w, alpha, beta )
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   Inputs
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   i                     Inclination
   L                     Longitude of the ascending node
   w                     Argument of perigee
   alpha                 Angle of the vector with respect to perigee
   beta                  Angle of the vector with respect to the orbit plane

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   Outputs
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   rA                    Right ascension in the ECI frame
   dec                   Declination of the ECI fram

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