Comparative flight strategies for ascent from Martian surface to orbiter rendezvous

Flight maneuvers and strategies to transport a vehicle from the Martian surface to orbiter rendezvous are analyzed to determine the most fuel-efficient method. Both endo- and exo-atmospheric flight strategies are considered for orbiter rendezvous into parking orbits of arbitrary inclination. It is found that optimal mass efficiency is achieved where the orbiter inclination is equal to or exceeds the latitude of the launch site. It is shown that high aerodynamic lifting capability improves performance for low circular orbit (LCO) rendezvous. It is suggested that the synergetic ballistic-projecting technique is best for optimal LCO rendezvous and that the all-thrust technique with plane change at apoapsis is best for optimal high elliptical orbit rendezvous.