Path: Orbit/OrbitManeuver
% Computes the delta-V to lower apogee. Generates the time to the maneuver which is done at perigee. It is assumed that the maneuver is an impulse. Type OrbMnvrLowerApogee for a circularization demo. -------------------------------------------------------------------------- Form: [deltaV, tToM] = OrbMnvrLowerApogee( el0, rAF, mu ) -------------------------------------------------------------------------- ------ Inputs ------ elI (1,6) Initial elements [a i W w e M] rAF (1,1) Final apogee mu (1,1) Gravitational parameter (Earth is the default) ------- Outputs ------- deltaV (1,1) Delta-V tOM (1,1) Time of maneuver --------------------------------------------------------------------------