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ecc-geo = geocentric orbital eccentricity of the spacecraft(non-dimensional)incl-geo (deg) = geocentric orbital inclination of the spacecraft in degreesargper-geo (deg) = geocentric argument of perigee of the spacecraft in degreesraan-geo (deg) = geocentric right ascension of the ascending node of the spacecraft indegreestanom-geo (deg) = geocentric true anomaly of the spacecraft in degreessma-sel (km) = selocentric semimajor axis of the spacecraft in kilometersecc-sel = selocentric orbital eccentricity of the spacecraft(non-dimensional)incl-sel (deg) = selocentric orbital inclination of the spacecraft in degreesargper-sel (deg) = selocentric argument of perigee of the spacecraft in degreesraan-sel (deg) = selocentric right ascension of the ascending node of the spacecraft indegreestanom-sel (deg) = selocentric true anomaly of the spacecraft in degreesThe geocentric coordinates of the spacecraft and the TLI delta-v components are with respect to theEarth mean equator and equinox of J2000 (EME2000) coordinate system. The selenocentric coordinatesare with respect to the mean lunar equator and IAU node of epoch coordinate system.page 32