ICNPAA 2010: Mathematical Problems in
Engineering, Aerospace and Sciences

In several missions it is necessary to perform orbital maneuvers. Aeroassisted maneuvers using atmospheric forces can be used to change the trajectory and velocity of a spacecraft. Several studies in this area have indicated that a significant fuel reduction can be achieved using aeroassisted maneuvers rather than fully propulsive maneuvers. Therefore, this allows an increase in the payload capacity of the vehicle. A spacecraft equipped with controllable aerodynamic plates have the ability to change their projected area and hence the aerodynamic forces suffered. In this context, the studies about the feasibility and efficiency of the spacecraft control system are very important. Therefore, this paper presents a simulation model which considers a closed-loop control system used to control the angle of attack of the aerodynamic plates during aeroassisted maneuver in the upper atmosphere. The proposed technique was validated through numerical simulations. The results showed the difference between the proposed maneuver and a propulsive one.