  The Gravity Assisted Maneuver has been applied in lots of space missions, to
change the spacecraft heliocentric velocity vector and the geometry of the
orbit, after the close approach to a celestial body, saving propellant
consumption. It is possible to take advantage of additional forces to improve
the maneuver, like the forces generated by the spacecraft-atmosphere
interaction and/or propulsion systems; reducing the time of flight and the need
for multiple passages around secondary bodies. However, these applications
require improvements in critical subsystems, which are necessary to accomplish
the mission. In this paper, a few combinations of the Gravity-Assist were
classified, including maneuvers with thrust and aerodynamic forces; presenting
the advantages and limitations of these variations. There are analyzed the
effects of implementing low Lift-to-Drag ratios at high altitudes for
Aero-gravity Assist maneuvers, with and without propulsion. The maneuvers were
simulated for Venus and Mars, due to their relevance in interplanetary
missions, the interest in exploration, and the knowledge about their
atmospheres. The Aero-gravity Assist maneuver with low Lift-to-Drag ratios at
high altitudes shows an increase of more than 10{\deg} in the turn angle for
Venus and 2.5{\deg} for Mars. The maneuvers increase the energy gains by more
than 15% when compared to the Gravity-Assist. From the Technology Readiness
Levels, it was observed that the current level of development of the space
technology makes feasible the application of Aero-gravity Assisted Maneuvers at
high altitudes in short term.
