Abstract
The problem of optimizing the fuel consumption needed for orbital maneuvers is investigated. The normal to the orbit components of the atmospheric drag and lift forces are obtained. The temporal variations in the inclination using Lagrange planetary equation are derived, then are integrated over one revolution. A numerical example is given. The velocity variations required to perform the propulsive maneuvers due to engines on board the satellite are calculated. The performance gain using aerodynamic forces combined with propulsive ones is achieved. The comparison between the totally propulsive maneuvers and partly propulsive with atmospheric maneuvers are illustrated and discussed.