Algorithm design of spacecraft trajectory correction in de-orbit maneuver by ‎feedback linearization method

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