Path: LunarMissions/LunarEphemeris
% Lunar fixed to ECI transformation -------------------------------------------------------------------------- Form: xECI = LFToECI(xLF,jD) -------------------------------------------------------------------------- ------- Inputs ------- xLF (6,1) State vector [r;v] (km,km/s) jD (1,1) Julian date ------- Outputs ------- xECI (6,1) State vector [r;v] (km,km/s) --------------------------------------------------------------------------
LunarMissions: LunarEphemeris/MoonRot Math: Linear/Cross
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