***** File CR_EPHEM.TXT EPHEMERIS The geocentric ephemeris for 0h UT each day has been calculated by the Astrometry Network from the following set of osculating orbital elements (Astrometry Network orbit no. 20). Full planetary and nongravitational perturbations have been taken into account at each time step in the ephemeris computations. The angular elements are referred to the ecliptic plane and the equinox of 1950.0. Epoch 2445740.50000 = 1984 Feb 10.00000 ET Perihelion Time, T 2445750.67068 = 1984 Feb 20.17068 ET Perihelion Distance, q .7345238 AU Eccentricity, e .9191917 Arg. of Perihelion 195.85424 deg Long. of Ascending Node 250.19118 deg Inclination, i 29.10277 deg Explanation of Symbols J.D. = Julian Date (U.T.) R.A. 1950.0 Dec. = Geocentric right ascension and declination referred to the mean equator and equinox of 1950.0. Light time corrections have been applied Delta = Geocentric distance of object in AU Deldot = Geocentric velocity of object in km/s r = Heliocentric distance of object in AU rdot = Heliocentric velocity of object in km/s Theta = Sun-Earth-Object angle in degrees Beta = Sun-Object-Earth angle in degrees Moon = Object-Earth-Moon angle in degrees PsAng = Position angle of extended radius vector in degrees PsAMV = Position angle of minus velocity vector in degrees Ephemeris computations by Comet and Asteroid Ephemeris Team MS 301-150G Jet Propulsion Laboratory Pasadena, CA 91109