In this paper, the purpose is spacecraft trajectory design and correction in de-orbit maneuver. According to the systematic requirements, this maneuver is required for a real project and its parameters and values have been set by its system engineering team. In order to achieve the desired maneuver, propulsion system must produce the velocity change vector. In practice, due to the unsatisfactory performance and uncertainties in the propulsion system, ideal velocity change vector may not be realized. Consequently, spacecraft deviates from the desired de-orbit trajectory and it is possible the spacecraft mission fails. So as to avoid this problem and compensate the created deviation, a controller based on Cowell’s formulation and using feedback linearization method is designed and its performance, after generating and loading desired de-orbit trajectory in the control law (using the orbital elements), will be examined during a de-orbit maneuver. In this article, for a considered impulsive de-orbit maneuver, velocity change vector and its execution time which are necessary for transfer from initial orbit to the de-orbit trajectory, are calculated. The simulation results indicate that, due to technical constraints and the capacity of the propulsion system, the maximum error of de-boost impulse value and orientation which the controller can compensate are 15% and 20% respectively.
)