Path: LunarMissions/LunarMission
% Computes parameters for a lunar orbit insertion. Computes the total velocity change, the vector direction for the burn and the duration of the burn. This always burns in the direction of the velocity error. You should approach the moon in the right direction so that the resulting orbit is achieved. If your input is elements dR must be part of the orbit track otherwise it won't work. The moon relative position must be at the point in the orbit specified by the mean anomaly. Type LunarOrbitInsertion for a demo. -------------------------------------------------------------------------- Form: [deltaV, uECI, tBurn] = LunarOrbitInsertion( hLunarOrbit, dR, dV, mI, uE, thrust ) -------------------------------------------------------------------------- ------ Inputs ------ hLunarOrbit (1,:) Perigee altitude or lunar orbital elements dR (3,1) Relative position vector at start (km) dV (3,1) Relative velocity vector at start (km/s) mI (1,1) Initial mass (kg) uE (1,1) Exhaust velocity (m/s) thrust (1,1) Thrust (N) ------- Outputs ------- deltaV (1,1) Velocity change (km/s) uECI (3,1) Vector for burn tBurn (1,1) Burn duration (sec) --------------------------------------------------------------------------