  The perturbative integral method was applied to quantify the contribution of
external forces during a specific interval of time in trajectories of
spacecraft around asteroids and under the Luni-solar influence. However, this
method has not been used to quantify the contributions of drag in aerocapture
and aerobraking. For this reason, the planet Mars is selected to apply this
method during an aerogravity-assisted maneuver. Several trajectories are
analyzed, making use of a drag device with area to mass ratios varying from 0.0
to 20.0 m2/kg, simulating solar sails or de-orbit devices. The mathematical
model is based in the restricted three-body problem. The use of this maneuver
makes it possible to obtain the variations of energy in the trajectory,
replacing expensive maneuvers based on fuel consumption. To observe the effects
of the maneuvers, different values of pericenter velocity and altitude were
selected for prograde and retrograde orbits. The innovation of this research is
the application of an integral method to quantify the delta-V of the aero
gravity maneuver, comparing the cost of the maneuver with the traditional
methods of space propulsion. The results allow the identification of orbits
with conditions to capture, and the perturbative maps show the velocity
variations.
